Orion / EM-1
Orion / EM-1 (Exploration Mission-1)
Orion EM-1, previously known as SLS-1 (Space Launch System-1) is NASA's first planned flight of the Space Launch System and the second uncrewed test flight of the Orion MPCV (Multi-Purpose Crew Vehicle). NASA, ESA, European and US Industry have teamed to develop the ORION spacecraft.
Under an agreement between NASA and ESA, ratified in December 2012, NASA's new Orion vehicle for human space exploration missions includes the ESM (European Service Module), based upon the design and experience of ESA's ATV (Automated Transfer Vehicle), the supply craft for the ISS (International Space Station).
ESA's industrial prime contractor for ATV, Airbus Defence and Space of Bremen, Germany, is leading a European industrial consortium, developing this vehicle on behalf of ESA and working closely with NASA's Orion US industrial prime contractor Lockheed Martin Space Systems.
Orion is the spacecraft that NASA intends to use to send humans and cargo into space beyond low earth orbit and to return them safely to Earth. It is being developed for crewed missions to cislunar space, asteroids, and then to Mars. The capsule is also planned as a backup vehicle for missions to the ISS (International Space Station). It will be launched by the NASA-developed SLS (Space Launch System) in 2019. 1) 2)
The first test flight of Orion was successfully completed in December 2014 with a Delta IV launch vehicle that launched the Orion Crew Module into a high elliptical orbit to demonstrate high-speed atmospheric Earth re-entry. This flight test did not include the ESM.
It is planned such that the Orion EM-1 flies a mission profile similar to what might be used in a future asteroid redirect mission. The un-crewed Orion travels to a lunar DRO (Distant Retrograde Orbit) mission (Figure 2), then returns on a trajectory calculated to achieve a high speed atmospheric entry on the order of ~11 km/s to demonstrate the performance and effectiveness of the Orion TPS (Thermal Protection System), as well as relevant environments prior to the first manned launch of the system. The total mission duration is 25 days (6 at destination). This will be the first flight of the ESM.
Orion EM-2 is planned as a Crewed High Lunar Orbit mission no later than the end of 2021. It is planned to spend several days in lunar orbit before performing a TEI (Trans-Earth Injection) burn to begin the return to Earth. The total mission duration is expected to be 14 days maximum (4 at destination).
Table 2: Overview of Orion ESM Design Reference Missions
Figure 1: Artist's rendition of the Orion EM-1 spacecraft in lunar orbit (image credit: NASA, ESA)
Figure 2: Orion EM-1 (Exploration Mission-1) design reference (image credit: NASA)
The Orion Vehicle
• CM (Crew Module)
• ESM (European Service Module)
• CMA (Crew Module Adapter)
• SA (Spacecraft Adapter)
• SAJ (Spacecraft Adapter Jettisoned Fairings)
• LAS (Launch Abort System)
The Service Module (SM) refers to the combined CMA + ESM + SA + SAJ.
The Crew Module and ESM (European Service Module), also referred to as SM, are physically interfacing via an interface ring called the CMA (Crew Module Adapter). The ESM is attached to the CMA for the duration of the mission. Just prior to the Earth's orbit entry, the CMA separates from the CM for CMA/ESM disposal and the CM performs final reentry and landing operations.
NASA is responsible for development of the CM, CMA, SA, SAJ, and LAS elements of the Orion spacecraft. The CMA provides the structural, mechanical, electrical, and fluid interface between the CM and ESM. In addition, the CMA houses communication equipment, sublimators for thermal heat rejection, and power and data control/interface electronics. The SM is enclosed by three spacecraft adapter fairing panels (SAJ) which provide a partial load path from the CMA to SA but also protect the solar arrays, radiators, and thrusters from launch and ascent loads. The fairings will be jettisoned during the ascent phase or following main engine cut-off of the launch vehicle.
The SA (Spacecraft Adapter) provides the interface to the launch vehicle during launch. During launch and ascent, the ESM and SA will be enclosed by the SAJ. The SA attaches to the aft end of the ESM to the Launch Vehicle and includes the structural interface, separation mechanisms, and umbilical connectors for communication between the launch vehicle and the Orion Spacecraft. At launch vehicle burnout, the Orion Spacecraft separates from the SA at the ESM/SA separation plane.
Figure 3: Overview of the Orion spacecraft architecture (image credit: NASA, ESA)
Figure 4: Orion schematic layout (image credit: NASA)
Orion EM-1 CM (Crew Module)
The milestones for the Orion EM-1 mirror the path taken by the Orion EFT-1 (Exploration Flight Test-1) spacecraft. However, the Orion EM-1 will sport a number of improvements based on the experiences of the December 2014 test flight. NASA is beefing up the critical TPS (Thermal Protection System) that will protect astronauts from the searing heats experienced during reentry as the human rated vehicle plunges through the Earth's atmosphere after returning from ambitious expeditions to the Moon and beyond.
Based in part on lessons learned from EFT-1, engineers are refining Orion's heat shield to enhance the design, ease manufacturing procedures and significantly strengthen is heat resistant capabilities for the far more challenging space environments and missions that lie ahead later this decade and planned further out in the future as part of NASA's agency-wide ‘Journey to Mars' initiative to send humans to the Red Planet in the 2030s.
On all future flights starting with EM-1 (Exploration Mission-1), the Orion crew module must withstand the higher temperatures and speeds experienced during return from more distant destinations such as the Moon, near-Earth Asteroids and Mars. Orion's TPS is comprised of the 5 m diameter main heat shield covering the rounded base of the capsule as well as the grid of back shell tiles bonded around the vehicle from top to bottom. 6)
Starting with EM-1, engineers will bond Orion's thermal protection system back shell tiles with a silver, metallic-based thermal control coating. The coating is designed to keep Orion's back shell in a temperature range from approximately -65 to 290ºC prior to entry and afford protection against electrical surface charges in space and during reentry.
The pressure vessel is the primary structure of Orion's crew module and is made of seven large aluminum pieces that must be welded together in detailed fashion. The first weld connected the tunnel to the forward bulkhead, which is at the top of the spacecraft and houses many of Orion's critical systems, such as the parachutes that deploy during reentry. Orion's tunnel, with a docking hatch, will allow crews to move between the crew module and other spacecraft. 7)
Orion's pressure vessel is composed of seven large pieces of aluminum, three of which are the cone panels. The pressure vessel holds the atmosphere astronauts will breathe against the vacuum of deep space, forming the crew compartment. The three panels together form the angled mid-section around the crew module where the windows and hatch are located. While technicians have been joining other elements of the structure together since early September, the cone panels have presented a unique challenge for NASA and Lockheed Martin, the agency's prime contractor for Orion. Engineers who have sought to reduce the crew module's overall weight have encountered and overcome technical challenges. 8)
The lessons learned from the EFT-1 mission are being applied to the EM-1 (Exploration Mission-1) and EM-2 flight test configurations to optimize a system design that can smoothly transition into production.
Ten of the most important lessons from EFT-1 focused on the ability to evaluate the design with actual flight performance. This was critical for the remaining design process as NASA continues to develop the most advanced Human rated spacecraft ever built. The following are the top ten lessons learned from this test flight: 9)
1) Some deep space designs are classic for a reason: Every aspect of Orion's design is driven by crew safety. Over 50 years of NASA's investment learning the ins and outs of human spaceflight has provided direction for meeting deep space requirements. An example is LAS (Launch Abort System). About 6 minutes into launch, the LAS is jettisoned to save mass for the journey to deep space destinations. While other system configurations exist, design trade studies repeatedly highlighted the advantage of not carrying extra weight past the time it is needed. So because the Orion LAS supports missions to deep space, mass is king and any extra weight is an extreme hindrance to those missions. By shedding the Orion LAS early, this mass isn't a burden to the vehicle for the entire mission, and other Orion systems are able to provide the abort function for the remainder of ascent to orbit.
2) Crew safety is built in, not bolted on: The EFT-1 tested and verified systems that are built "into the bones" of the spacecraft from the very beginning. This means not just the heat shield or the flight computers are designed for the rigors of deep space, but everything included in the fundamental systems and structure of the spacecraft are designed and built to specifications set forth by NASA. Every system design has a deep space requirement it is being built to right now: Orion's seats are being designed to help prevent loss of consciousness as astronauts experience up to 5 G's during high-velocity re-entries, the cooling system keeps the crew cabin about 25ºC despite its heat shield being heated to 2,200ºC during reentry, the built in stowage lockers are designed to double as a safe-haven during dangerous solar activity, the life support system allows for exercise since deep space missions require much longer stays in zero gravity, computers and avionics are designed to self-correct in case there is a failure and you're months from home, and the crew module tiles are designed to protect from multiple micro-meteoroid strikes since the number of strikes will increase during missions that last months instead of days.
3) Reusability must be tied to reality: Part of flying for the first time in space is being able to make informed decisions about what we can realistically reuse following a deep space mission. After evaluating areas of water intrusion and corrosion, we've come to expect that many components in the crew module, especially inside the pressurized volume, or the hull where the crew sits, can be reused for later flights—components such as the computers, avionics and electrical distribution for example. The structure itself is more difficult to predict for reuse base on the unpredictable landing loads it might experience from a long journey from deep space with unpredictable landing sea conditions. The program is looking at options for reuse based on actual landing load data provided.
4) Designs mature as we Learn: Significant design changes are being made to optimize the EM vehicles. Thefuture design and analysis efforts will be simplified (Figure 5), overall mass has gone down, and recurring costs for production will be lowered. Establishing a common design philosophy has prevented a large number of engineering revisions and hardware changes. The Orion design is now incorporating lessons from EFT-1 and updated requirements for the crewed EM-2 mission.
Figure 5: Some highlights of the numerous design changes made as a result of the EFT-1 flight (image credit: NASA, Lockheed Martin)
5) Test like you fly to ensure success: After extensive testing on the ground in "Flight Like" scenarios EFT-1 successfully tested Orion in real flight environments, which could not be duplicated in ground simulations. The systems were subjected to the most critical crew safety requirement with the same rigors they will see when carrying humans. Systems verified included: thermal protection system, hardware separation events and the parachute system. This was a 100% mission success. 87 EFT-1 flight test objectives were identified in the early phases of the test development program. These objectives included verification of Orion's subsystems ability to launch, control its trajectory with OFI (Operational Flight Instrumentation), complete all separation events, reenter the Earth's atmosphere at 32, 200 km/hr and 2200ºC, land accurately in the Pacific Ocean and be recovered without damage. 81 of the 87 FTOs (Flight Test Objectives) were fully satisfied with six being partially met. Four of the seven FTO's were related to suspect DFI (Developmental Flight Instrumentation) performance. Two FTO's related to the Crew Module Up-righting System were partially met, and one FTO related to structural measurements was partially met.
6) Organize for focus: Organizationally, Lockheed Martin and NASA agreed assigning a "mission director" to each test flight would allow program focus on the near term test milestones while maintaining a parallel program focus on the remaining DDT&E (Design, Development, Test, and Evaluation) efforts. EFT-1 was the first mission where this was implemented and proved to ensure the test was completed on time and within budget. This effort also saved over one year of development time for EM-1 by performing this in parallel versus chronologically.
7) Processes and reviews tailored: Since its inception the Orion program has spent significant time focusing on defining an efficient set of requirements to enable the design of Orion as well as optimize the concept of operations for a recurring program rhythm. In an effort to remain flexible the program continues to evolve the requirements based on lessons learned. On EFT-1 the program used a consolidated requirements document approach that was successful in limiting the number of requirements, individual requirements documents, and tiers of requirements documents. The team is using the success of this approach to streamline the EM requirements where possible. Requirements verifications were completed later than planned, partly because the verification work did not carry the same urgency as other launch campaign tasks. The team is looking at a more structured "waterfall" approach to prevent lower level verifications from conflicting with launch campaign activities.
8) Flexibility to accommodate change: Several program planning improvements were accomplished during the course of the program leading up to EFT-1. Improving the Orion IMS ( Integrated Master Schedule) by integrating the NASA "non-Prime" elements improved the continuity of the entire schedule past vehicle delivery. Through Monthly Orion Program Performance Review meetings, the assessments team continued to monitor the contractor performance. Data input for these reviews consisted of Integrated Master Schedule updates, CPRs (Cost Performance Reports), Financial Management Reports (533 inputs), contractor supplemental financial and schedule data, and through participation in the subsystem IPT (Integrated Product Team) meetings. The assessments team integrated these data each month to update the assessment and forecast for the EFT-1 launch date and financial position enabling program management to make rapid decisions.
9) Partnerships ensure Communication: After the President's proposed cancellation of the Constellation program, NASA and Lockheed Martin recognized reductions needed to occur both on the government side and within Industry to keep the program intact. NASA identified all work within their scope as "Non-Prime" and all work within Industry as "Prime". NASA and Industry were challenged with a $738.9 M reduction in funding in 2010 and needed to re-plan the entire program in anticipation of this reduction. The cost reduction initiatives they initiated have come to be known as "The streamlining of Orion" and have been used as examples of how NASA and Industry can work together to become more efficient and affordable. The continued emphasis on meeting program objectives within the government's affordability range have resulted in a refined program plan that accomplishes all of its goals within the annual budget and without jeopardizing mission success. One example of this was the reduction of test flights from seven to four while maintaining the same requirements verifications.
10) Supply Chain must remain healthy: EFT-1 provided the Orion team the ability to exercise 80% of the supply chain that will be utilized for future production vehicles. This includes subcontractors currently spread across 42 states with 60,000 parts being received by NASA or its prime subcontractor in 3 major integration facilities. Throughout this endeavor the processes were validated, enhancements were made and opportunities for improvement identified. EFT-1 helped establish 6 key principles needed to ensure effective supply chain management:
• Centralized supply chain ownership/management offers advantages over IPT ownership
• Need for timely actionable information, including stable engineering design documentation, is mandatory
• Consistent, effective and constant communication is mandatory
• Management of the supplier certification and work load
• Manage with the tools, don't expect the tools to manage
• Work within the system.
In summary, NASA and Lockheed Martin are taking what we have learned from EFT-1 and years of government investments to make improvements, fly again, making improvements again, and developing a spacecraft that we can proudly stand behind and say we are confident in its abilities to take humans into deep space and bring them safely home.
Some examples of Orion design changes as a result of lessons learned from EFT-1 deals with the structure of the EM.
The Orion design for future Exploration Missions experienced many design optimizations as a result of the EFT-1 flight results. The following section highlights several changes to exemplify optimizations that was realized. Note: (For more information, the reader is referred to Ref. 9).
Structures: Reduced parts and weld assemblies required on the pressure vessel include:
- Reduction from 6 to 3 cone panels, and reduction of cone section welds from 12 to 3.
- Reduction from a 3 piece welded aft bulkhead design to a single spun-formed design.
- Change to an "Apollo-gusset" design in the aft-bay to help reduce the number of separable-parts, and combine structural elements (reduced thruster pod support structures and harness support structures, etc.).
Figure 6: A simplification and reduction of structural parts has been realized by the lessons from EFT-1 (image credit: NASA, Lockheed Martin)
Propulsion: Tubing subassemblies on EFT-1 were custom fit for propulsion system integration (e.g. fit-up tube assembly, cut, face, install heaters / temp sensors, reinstall, repeat as required). On EM-1 no trim to fit will be required on the vehicle. Tubing subassemblies will be delivered in their net shape and subassembly welds will be proof & leak tested prior to delivery.
PCAs (Pressure Control Assemblies) on EFT-1 required a custom fit for propulsion system integration (similar to Tubing subassemblies). On EM-1 there will be improved packaging and attachment methods including PCA welds proof & leak checked prior to delivery.
Propellant and Pressurant Tanks on EFT-1 were difficult to integrate and perform welding operations. The EM-1 design created a new inlet / outlet orientation to ease integration and welding operations.
RCS (Reaction Control System) thrusters on EFT-1 had support struts that have been simplified to a Pod design and attachment method eliminating all struts.
Figure 7: Left: EFT-1 Roll Left Thruster, Right: EM-1 Roll Left Thruster Pods (image credit: NASA, Lockheed Martin)
TPS (Thermal Protection Systems): The Heatshield Avcoat design improvement included changing from a monolithic, individual cell injection process to a "Block Avcoat" design where the heat shield blocks could be automated in production while increasing material properties performance. The use of thermal tape that was used on the EFT-1 heatshield (and similar to Apollo) was changed to use on all backshell and heatshield surfaces for all future Exploration Missions.
Micrometeoroid and Orbital Debris Performance: There are a number of lessons learned in the realm of MMOD (Micrometeoroid and Orbital Debris) environments and analyses, which are being examined and used to influence change for the EM and beyond missions. Chief among these lessons learned is that time spent in the high orbital debris flux altitude band, approximately 650 km to 1200 km, should be minimized. The MMOD analysis performed on EFT-1 was the first such analysis of a human-rated spacecraft above ISS ( International Space Station) altitudes since man-made orbital debris has become an issue, and found the risk at these altitudes (600 km – 1600 km) to be much higher than anticipated; Apollo was too early in spaceflight history for much OD (Orbital Debris) to have accumulated yet. Post-flight inspection of the EFT-1 capsule indicated that actual MMOD exposure may have been even higher than the analyses had assessed. Based on this lesson learned, the parking orbit of EM-1 has been reduced from 3.5 hours in a high-MMOD-risk orbit (2 orbits), to half that time (limited to 1 orbit) to reduce MMOD risk. And as EM-2 trajectory trades and analysis is ongoing, avoiding these altitudes has been accepted as a prerequisite in the EM-2 trajectories. Largely anchored on this finding, other lesson learned recommendations include: increasing MMOD protection in upper-stage and other critical hardware, re-assessing window damage cause and remediation, and continued post-flight inspections and MMOD environment recommended updates based on EM flights.
Radiation Summary: Orion is the first spacecraft that addresses crew radiation protection as an integral part of the vehicle design. We are using a state-of-the-art radiation analysis process to analyze the shielding provided by the vehicle and quantify the internal radiation environment. This analysis is based on the full fidelity Orion CAD model and space radiation environment models. Due to the EFT-1 trajectory passing through the very core of the van Allen proton belts, intravehicular radiation environment was equivalent to 4-6 weeks inside ISS (in terms of cumulative exposure). Thus EFT-1 presented a valuable opportunity to validate our analysis procedure and ultimately improve crew radiation protection for future manned missions. This opportunity was materialized by flying six RAMs (Radiation Area Monitors) on EFT-1. Radiation measurements were in very good agreement with pre-flight predictions, confirming the validity of the radiation analysis approach and providing confidence in our efforts to maintain crew radiation exposure ALARA (As Low as Reasonably Achievable) consistent with NASA requirements.
An important lesson learned for electronic components radiation hardening refers to the importance of considering time variability of the environments in the Single Event Effect rate calculations. The EFT-1 proton environment varied dramatically throughout the mission. Accounting for this time variation was an essential component in selecting the appropriate level of redundancy in critical systems such as the VMC/FCMs (Vehicle Management Computer / Flight Control Modules). This lesson continues to apply to Exploration Missions. Stochastically occurringSPEs ( Solar Particle Events) may cause significant temporary increase in the radiation environment, and critical systems need to design appropriately. A related lesson learned reflects the importance of assessing timing of critical mission events with respect to the radiation environment. Environment assessments performed for EFT-1 drove modification of the mission timeline such that Avionics intensive mission events be executed outside of the core of the van Allen belts. This too is a lesson learned relevant for future missions especially in off-nominal conditions that may expose the spacecraft to high radiation environments.
EM-2 (Exploration Mission-2): EM-2 will be a crewed test flight that will be launched on an SLS and enter lunar orbit in 2022 to verify the capability of Orion to successfully launch, perform a crewed mission, and return them safely to Earth. Figure 2 depicts one option for a lunar mission. The EM-2 configuration will consist of:
• A fully functional launch abort system
• A fully functional Crew Module that includes a crew of up to four and all Cis-Lunar life support systems
• A fully functional Service Module.
Figure 8: EM-2 Design Reference Mission (image credit: NASA)
Figure 9: Technicians with Lockheed Martin, NASA's prime contractor for Orion, are welding together the pieces of the spacecraft's pressure vessel at Michoud Assembly Center in New Orleans, LA (image credit: NASA)
ESM (European Service Module)
The ESM implements four major system functions to Orion (Ref. 1):
• provides thrust for orbital maneuvers and attitude control after upper stage/launch vehicle separation
• generates electrical power and distributes it to the ESM users and to the CM/CMA
• regulates heat for the life support and avionics equipment during the orbital phases of the mission
• stores and provides to the CMA/CM potable water, oxygen, and nitrogen.
In addition, it ensures structural spacecraft integrity during launch and in-orbit maneuvers. The ESM can also provide additional volume and other resources on select missions for accommodating science, engineering demonstrations, development test objectives, and deployment of lunar infrastructure equipment during the cruise and lunar orbit phases of lunar missions. This volume provides electrical power distribution, network access for command and control interfaces, and structures and mechanisms.
The architecture of the module has been developed based on the ATV spacecraft concept (five successful missions to the ISS),modified to cope with the different mission requirements and the man-rating approach for beyond LEO missions. 10)
Figure 10: Illustration of an ATV cargo freighter in flight with deployed solar arrays (image credit: ESA)
The resulting ESM architecture is depicted in Figure 11, for comparison. The architecture of the system and subsystems hereafter proposed is the reference design for the Lunar Sortie Mission. Changes in the architecture are expected for the other missions to tailor the configuration to mission needs, to remove unnecessary HW and to optimize the launch mass.
European Industrial Consortium: ESA entrusted the development of the ESM (European Service Module) to a consortium of European industries led by Airbus Defence and Space. The consortium of companies was selected to reuse the experience and industrial heritage of the very successful ATV (Automated Transfer Vehicle). Airbus Defence DS Germany as the Prime Contractor is responsible for all system-related work. This includes: 11)
- The overall Management of the contract
- The overall System Engineering activities
- The Management of the procurement activities
- The System Product Assurance and Safety activities
- The liaison with Lockheed-Martin (NASA prime contractor of the Orion vehicle).
Airbus DS, France is responsible for part of the system engineering, ground software, Helium pressurant tanks and simulation facility.
On Subsystem level, Airbus DS, Germany is responsible for the System Engineering, the Propulsion, Power and Avionics Subsystem Engineering as well as for GSE and AIT activities. The responsibility for the development of the other sub-systems or equipment has been distributed among European companies as follows:
TAS (Thales Alenia Space) Italy: the Structure, Thermal and Consumable Storage Subsystems, supported by the following level-2 subcontractors:
- RUAG, Switzerland: secondary structures
- SONACA, Belgium: tank bulkhead
- APCO, Switzerland: MDPS (Meteoroid and Debris Protection System)
- CRISA, Spain, TCU (Thermal Control Unit)
- Prototech, Norway: nitrogen filters
- MEWASA, Switzerland, Water tank bellows.
Dutch Space, The Netherlands: the SAW (Solar Array Wings), supported by the following level-2 subcontractors:
- SELEX SE, Italy for the Photo Voltaic Assemblies
- RUAG, Switzerland: deployment dampers.
Airbus DS, Germany: the propellant tanks, Propulsion Drive Electronic and reaction control thrusters.
RUAG, Switzerland: the SADA (Solar Array Drive Assembly) composed of the mechanism and electronic unit.
SELEX SE, Italy: the PCDU (Power Conditioning and Distribution Unit)
Thales Alenia Space, Belgium: PRU (Pressure Regulation Unit)
Antwerp Space, Belgium: the Electrical Ground Support Equipment Front Ends, supported by the following level-2 subcontractors :
- Clemessy, France
- Rovsing, Denmark.
APCO, Switzerland: Mechanical Ground Support Equipment.
Latelec, France: avionics and power harness
TESAT Germany and Alter, Spain: CPP (Centralized Parts Procurement) scheme for EEE (Electrical, Electronic and Electromechanical)-parts.
Equipment suppliers encompasses Vacco (US), Moog (US), Sofrance (F), Cobham (US), Vivace (US).
Figure 11: Illustration of the ESM (European Service Module) without radiators and MDPS, image credit: ESA, Airbus DS
Physical architecture: The ESM is a cylindrical unpressurized module which interfaces at its bottom to the SA and at its top to the CMA. The OMS-E (Orbital Maneuvering System -Engine), i.e. the main engine, protrudes into the SA. Equipment on the tank platform is also allowed to protrude into the CMA. The total height of the ESM is 4.0 m.
The cylindrical shape is defined by the external radiators which enclose the body of the ESM. The function of the radiators is twofold, i.e. to radiate heat, and to serve as the first barrier of the MDPS (Micrometeoroid and Debris Protection Subsystem ). Mounted to the back side of the radiators are Nextel and Kevlar blankets which serve as the second barrier. The externally mounted RCS (Reaction Control System) pods and SAWs (Solar Array Wings) must be designed such that these respect the Orion SAJ allowable envelope.
The internal accommodation of the ESM subsystem equipment is highly dependent to the primary structure architecture, based on seven separate bays for accommodation, six located circumferentially about the central bay. The pressurant tanks are accommodated in the center bay. The four largest bays are used for the accommodation of the propellant tanks which dominate the available volume. The remaining volume provides accommodation to the avionics equipment, CSS (Consumable Storage Subsystem) water tanks, harnessing and tubing.
The top surface of the ESM is dominated by the protruding tank domes for the propellant subsystems, one of the helium pressure tanks, the four tanks for Oxygen and Nitrogen, and the Flow Control Assembly for the active cooling subsystem. These elements protrude into the CMA, while maintaining a specific minimum distance to the CM Heat Shield. For these elements above the tank platform, the CMA provides the MDPS protection.
The lower surface is dominated by the OMS-E, which serves as the main engine of the ESM, and the eight auxiliary thrusters. Within the lower platform, a panel is incorporated through which the UPC (Unpressurized Cargo) is installed, and optionally ejected.
Table 3: ESM characteristics for Lunar Missions
Functional architecture: Orion functionalities are generally shared between ESM and CMA/CM. Functional Chains gather equipment of the ESM which participate to a same service provided by Orion for the accomplishment of its mission.
Figure 12 depicts the overall avionics subsystem architecture and interfaces. The interface to the SLS launcher is depicted on the left side of the drawing, and the CM and CMA (labeled as SM-CM I/F Adapter) are on the right side. The main link with Orion CM on-board computers is the ODN (On-board Data Network), based on a time-triggered Ethernet solution. This interface ensures the connection of all ESM avionics to the on-board computers and allows the ESM to receive commands and to deliver monitors.
Few discrete lines ensure the independent command of ESM power subsystem electronics, allow to acquire signals from 8 sun sensors used as back-up AOCS sensors and allow the transfer of data acquired from the development flight instrumentation.
The four SAWs (Solar Array Wings) ensure a maximum electrical power production of 11.2 kW, to cope with a CMA/CM power demand of maximum 7.3 kW to be respected with one wing failed.
Four power buses allow powering to / from the CMA/CM depending on mission phases. Additional and independent power lines are provided for the wireless cameras installed on top of SAWs.
Finally, a dedicated pass-through harness connects the CMA to the SA/SAJ and launcher to allow transfer of monitoring data and separation commands.
Figure 12: ESM functional architecture (image credit: ESA, Airbus DS)
The ESM provides translational and 3-axis attitude control for the spacecraft, stores consumables for the crew module and provides power via the solar arrays. The ESM is also being designed to carry cargo. The main subsystems of the ESM are: 12)
• Structure Subsystem
• TCS (Thermal Control Subsystem)
• CSS (Consumable Storage Subsystem)
• PSS (Propulsion Subsystem)
• EPS (Electrical Power Subsystem)
• Avionics Subsystem
Figure 13: Top view of the ESM and its elements (image credit: ESA, Airbus DS)
Figure 14: Illustration of the ESM architecture and principal layout of main elements (image credit: ESA, Airbus DS)
Structure subsystem: The ESM astructure consists of the following major elements:
• Primary structure
• Secondary structure
• MDPS (Meteoroid and Debris Protection).
The primary structure transmits the SLS launch loads to the upper composite composed of the CMA, the CM, and the LAS, then supports the upper composite aerodynamic and inertial loads as well as the ESM inertial loads generated by the ESM internal equipment. The design is based on a shared load path between the ESM and the external SAJ fairings. The objective is to minimize the loads applied on the ESM mechanical structure in order to optimize its mass which is propelled all along the mission, whilst the SAJ capability is sized to the extent possible by the main launch phase, since the SAJ mass is jettisoned early during the launch. The primary structure is composed of:
• 6 longerons (machined aluminum) linked to the CMA frame and six pyronuts that separate the ESM from the Spacecraft Adapter
• Tank bulkhead (machined aluminum) supporting the four propellant tanks, as well as the gas delivery CSS tanks, ensuring the main link between the CMA lower interface ring and the rest of ESM structure.
• "Radial" shear webs and internal "square" webs assembly (composite sandwich panels), housing most of the ESM equipment, including water tanks and SAW support frames and propulsion high pressure system. It forms the ESM core attached to the tank bulkhead, longerons and lower closeout panels. The main engine is attached to the central square tube panels via struts transmitting the thrust.
• Lower Platform (machined aluminum) on which the equipment is connected: OMS-E main engine, auxiliary thrusters supports, RCS pods supports, SAD (Solar Array Drive) mechanism, and PIE (Propulsion Isolation Equipment).
• MDPS covers and aft closure panels to protect the ESM from the MMOD (Micrometeoroid and Orbital Debris) environment.
The secondary structures support the ESM equipment carrying the inertial and dynamic loads of the equipment during launch and transmitting in-orbit thrust and inertial loads.
The MDPS is partly metallic and partly composed of Nextel reinforced MLI (Multi-Layered Insulation). Debris and meteoroid particles with velocities up to 24 km/s hit the outer wall, forming a cloud of lower energy particles which are then contained by the inner wall, preventing any penetration of the ESM.
Figure 15: Primary and secondary structures (image credit: ESA, Airbus DS)
TCS (Thermal Control Subsystem): The TCS includes an ATCS (Active Thermal Control Subystem), a PTCS (Passive thermal control Subsystem) and the TCU (Thermal Control Unit).
11) ATCS (Active Thermal Control Subystem): The ATCS is designed to collect the thermal loads from the CM and from the ESM powered equipment and to reject them toward the space radiative sink. The ATCS architecture is based on a Single-phase Fluid Loop Architecture using the HFE-7200 coolant to collect and to transfer the heat loads from both ESM avionics (via cold plates) and CM (via Inter-Loop Heat Exchanger) and to reject them through specific body mounted radiators. The ATCS is composed of two fully independent loops working simultaneously (hot redundancy approach). The schematic of the ATCS architecture is presented in Figure 16.
Each ATCS loop is composed by the following main components:
• 1 Radiator Assembly commonly used for both loops and composed of 4 full height radiators and 2 split radiators (with lower part not removable) mounted in serial configuration
• 1 CP (Cold Plate)
• 2 online APSBs (Absolute Pressure Sensor Blocks)
• 1 wet on-line TSB (Temperature Sensor Block)
• 1 FCA (Fluid Control Assembly) including redundant pumps with relevant passive accumulator and a TWMV (Three-Ways Modulating Valve)
• Hard/flex hoses, tees, couplings and restrictors.
Figure 16: Architecture of the ATCS (image credit: ESA, Airbus DS)
The FCA is controlled by the TCU to provide constant mass flow rate inside the loop. In particular two flow rate set points are foreseen, one for nominal operation and one for contingency (with only one loop operative). The FCA also includes the TWMV, controlling the temperature at the ESM-CMA interface.
The external surface of the radiator panels is coated with a specific paint characterized by the following thermal-optical characteristics:
• Alpha (α) = 0.2
• Emissivity (ε) = 0.8.
The Cold Plates are devoted to collect the entire thermal load from the ESM avionics boxes. Their design is constituted by a stainless steel channelling enclosed in an aluminum casting acting as a plate in direct contact with the thermally active unit. Different Cold plate sizes, to satisfy the different configuration needs, are foreseen.
Figure 17: Photo of a sample radiator panel (image credit: ESA, TAS)
12) PTCS (Passive Thermal Control Subsystem): The PTCS provides the thermal control of ESM hardware (propulsion, CSS, power and avionic items) and reduces the temperature gradients and minimize heat flows through the internal elements. The PTCS has two main components, heaters (with thermistors and wire heater) and insulation (MLI thermal blankets, including some specific high temperature MLI blankets, for thrusters and engine nozzle thermal impingement protection).
The MLI protects the internal parts against the external environment and heater lines compensate the heat leaks toward space. Different MLI typologies, in terms of composition, have been identified for the different applications on the ESM. The MLI composition mainly depends on exposure or not to the space, geometry & fixation interfaces and exposure to thrusters plume flux and nozzle radiation.
Two cold redundant heater lines managed by the TCU assure thermal control and temperature uniformity in the Orion internals and for the local thermal control of specific items. In addition, heater lines managed by thermostats and powered by the PCDU (Power Control and Distribution Unit) provide a further redundancy to the environmental control function.
13) TCU (Thermal Control Unit): The TCU is designed to ensure the management of the TCS and of the CSS.
For the ATCS, the TCU acquires the various parameters from the ATCS sensors, monitors and commands the ATCS valves, and issues commands to the FCA (Flow Control Assembly).
For the PTCS, the TCU commands the heater chains and monitors the thermistors. It operates according to activation and de-activation thresholds defined and modified by the CM on-board computers, while ensuring bus interface and power supply logic.
For the CSS (Consumables Storage Subsystem), the TCU commands the valves and monitors their position. It also monitors the pressure and temperature parameters in the subsystem to support the system FDIR (Failure Detection, Isolation and Recovery).
Figure 18: Layout of the TCS (Thermal Control Subsystem), image credit: ESA, Airbus DS
CSS (Consumable Storage Subsystem): The CSS provides potable water, oxygen and nitrogen to the CM. It can also provide water for the sublimator located in the CMA via a dedicated kit composed by its own tank assy and distribution system, to be installed optionally for specific missions. It consists of the following major elements:
• WDS (Water Delivery Subystem)
• GDS (Gas Delivery Subsystem)
The architecture of the WDS is composed of the following components:
• Water tanks (metal bellow technology)
• Water on/off valves, (isolation valves)
• Temperature and quantity sensors
• 2 distribution lines towards the CMA I/F to supply water for the different CM/CMA needs.
The architecture of the GDS is composed of the following components:
• Gas tanks
• Gas pressure regulators
• Gas on/off valves, (isolation valves)
• Gas relief valves
• Temperature and pressure sensors
• Hydrophobic filters upstream the water tanks
• Distribution lines towards the CMA I/F to supply oxygen and nitrogen
• Distribution lines towards CMA I/F for GDS filling on ground from the GSE.
In the case of a configuration with WSK (Water Sublimator Kit) a set of 3 additional water tanks is introduced and interconnected to the others tanks and lines of CSS.
Figure 19: Layout of the CSS (image credit: ESA, Airbus DS)
PSS (Propulsion Subsystem): The propulsion subsystem design has to cope with a complex mission scenario. It includes three different types of engines / thrusters. Each of these thrusters utilizes the same propellants: MON-3 (Mixed Oxides of Nitrogen) as oxidizer and MMH (Monomethylhydrazine) as fuel.
The single Main Engine, which is one of the Shuttle OMS-E engines (27.7 kN), is delivered by NASA as GFE (Government Furnished Equipment) and will be used during ascent abort and trans-earth injection maneuvers as well as orbit change maneuvers. This engine is gimballed with an amplitude of ± 7° around both axes (pitch and yaw). The actuation is performed by the TVC (Thrust Vector Control).
The 8 auxiliary thrusters which are similar to those used on ATV (490 N) are used during ascent abort and launcher separation together with the main engine. They are also used as backup to the main engine for trans-earth injection and for trajectory correction maneuvers.
The 24 RCS thrusters which are the same as used on ATV (220 N) provide the impulse necessary for attitude control, small maneuvers and forced translation during Rendezvous and Proximity operation. These thrusters are accommodated into six pods. Two pods are composed of four roll thrusters, placed along the ESM lateral surface under the CMA, while four other pods are composed of four thrusters, placed along the ESM lateral surface under the level of the first four pods. Each propellant type is stored in two propellant tanks, both sets of propellant tanks being arranged in a series configuration.
The propellant distribution comprises several electromechanical valves for propellant isolation and pressure transducers interconnected via pipes. The assembly ensures isolation of the engine / thrusters from the propellant tanks during launch, docked phase to the ISS and other mission events where it becomes necessary to isolate the engine / thrusters from the propellant storage. The propellant distribution network provides the connections between the propellant tanks and the isolation valves and then onwards to the thruster assemblies. Fill and Drain Valves and the related access lines are used during ground testing and for loading and unloading of the propellant and pressurized tanks. They are located in the CMA to enable access even after the SAJ around the service module has been installed.
The propulsion subsystem is controlled by the PDE (Propulsion Drive Electronics) which handles all nominal propulsion related commands issued by the CM and provides feedback via the CMA PDUs (Power Distribution Units) and the PDUs to the vehicle management computer interface and the ESM network. The PDE controls all thrusters, the TVC and the associated valves, instrumentation and leakage detection.
The PRU (Pressure Regulation Unit) controls and monitors the operation of the pressure regulation valves, based on set points defined and modified by the on-board computers. The EPR (Electronic Pressure Regulation) selected for ESM has the advantage to optimize the pressure of propellant and oxidizer according to the engine in operation, at the price of an increased development risk for this function.
The EPR of the propulsion system propellant is a new technology for the European industry. The ATV design featured a mechanical pressure regulation like the propulsion system of the Shuttle OMS-E engine. The electronic pressure regulation allows a better control of the pressure, hence the fuel and oxidizer consumption is enabling to reduce propellant margins and the overall mass at launch. Airbus DS decided to venture in that new technology as a result of a trade-off taking into account the positive results obtained by Lockheed-Martin in breadboard testing. However, in the development of a new technology there is always the risk of not being successful especially if the development time is constrained.
To mitigate the impact to the project in case of unsuccessful development, it was decided to ensure that reverting to mechanical pressure regulation would be possible with minimum schedule impact. NASA provided Shuttle mechanical pressure regulators and valves to VACCO, the original manufacturer and Airbus DS ordered tests to ensure the hardware would satisfy the performance required for the ESM. Breadboard testing of the electronic regulation performed in Europe up to now delivered promising results and the probability of having to revert to mechanical pressure regulation is becoming more remote.
Figure 20: Layout of the propulsion subsystem (image credit: ESA, Airbus DS)
EPS (Electrical Propulsion Subsystem): The EPS has the function to generate the power for all modules of Orion. It manages the power provided by its 4 SAW (Solar Array Wings). The PCDU (Power Control and Distribution Unit) provides the power I/F to the SAW and CMA, distributes electrical power to ESM users and protects the power lines.
The power generation part of the ESM EPS consists of four SAW units. Each wing is composed of three deployable CFRP (Carbon Fiber Reinforced Polymer) rigid panels covered with triple junction GaAs solar cells forming nine (9x) sections of solar cell strings. In nominal condition the SAW can supply a total 11.2 kW. Each SAW is linked to the ESM structure by a two degree of freedom SADA (Solar Array Drive Assembly). The SADA ensures the power and signal transfer from the SAW to the PCDU. It is composed of SADM (Solar Array Drive Mechanism) and a (SADE (Solar Array Drive). The SADM allows orienting the SAW in two independent axes. In the Sun-tracking mode the inner axis can swivel between -35º and +25º, while the outer axis has a continuous rotation capability (0º; +360º).
SADM of the ESM has a unique design incorporating a two axis gimbal. An inner axis provides rotation of the SAW about an axis perpendicular to the ESM longitudinal axis, and an outer axis which rotates the SAW about its own longitudinal axis. The two-axis capability is necessary for two reasons:
1) allow maximum sun tracking to meet the power requirements for particular vehicle attitudes of certain mission phases. Insufficient power is generated by the SAW with a single (roll) axis SADM not providing the avoidance capability of the shadowing effect of both the Orion vehicle on the SAW and the SAWs on each other
2) insure the structural integrity of the SAWs under injection maneuvers. For the trans-lunar injection performed with the upper stage of the Space Launch System rocket, actually the iCPS (interim Cryogenic Propulsion Stage), the arrays are canted backwards to sustain in deployed configuration the 1 g acceleration load. For the trans-earth injection performed with the ESM main engine, the acceleration is less severe and the arrays have to be canted forwards to prevent damages from the OMS-E engine plume while minimizing the load on the SAWs.
The SADM also allows repositioning (canting) of the SAW to reduce the loads on the SAW and SADM during the different Orion orbital maneuvers. At TLI (Trans-Lunar Injection), a 0.5 g acceleration is generated by the iCPS engine and at LOI (Lunar Orbit Insertion) and TEI (Trans-Earth Injection) a 0.3 g deceleration is generated by the OMS-E engine.
As shown in Figure 21, in order to reduce these loads to an acceptable level, the SAWs need to be repositioned by the SADM. In TLI, the SAWs are thus canted during the maneuver to inner axis = - 60º / outer axis = 0 º. In LOI/TEI, the SAWs are canted to inner axis = +55º / outer axis = 0º.
Figure 21: Orion vehicle with ESM SAW canting angles (-60º / 0º @ TLI, +55º / 0º @ LOI/TEI), image credit: ESA, Airbus DS
The EPS distributes the generated power to the CMA/CM through four independent 120 V busses. The power interfaces of the PCDU protect each unregulated bus from overload or short circuit failures on feeder busses outside the PCDU. They are implemented with power devices connected in parallel and independently operated for power flow from PCDU to CMA PDU, plus a number of power diodes for power flow from CMA PDU to PCDU.
Avionics Subsystem: The high-level management of the vehicle and its functions is performed at the level of the Orion on-board computers. The ESM is controlled and monitored by specific electronic controller units. All units are connected via the ODN (Onboard Data Network) to the CMA/CM. All vehicle control and management software resides in the CM computers. The ODN is a three plane TTGbE (Time Triggered Gigabit Ethernet),1000Base-CX, according to standard SAE AS6802.
The Time-Triggered Gigabit Ethernet ODN provides a set of time-triggered services implemented on top of standard IEEE802.3 Ethernet. It provides the capability for deterministic, synchronous, and congestion-free communication, unaffected by any asynchronous Ethernet traffic load. By implementing this standard in network devices (network switches and network interface cards), Ethernet becomes a deterministic network. This means that distributed applications with mixed time-criticality requirements (e.g., real-time command and control, audio, video, voice, data) can be integrated and coexist on one Ethernet network.
Each of the ESM controller units is connected via a SNIC (Standard integrity Network-Interface Card), according to Honeywell ICD8273722, to the LAN switch located in the CMA. The SNICs have three ports for two failure-tolerant communication on three network redundancy planes.
Development: The challenging schedule of the program, with the ESM delivery planned for early 2017 and the EM-1 launch planned for 2018, is influencing the way the ESM is verified. Qualification has often to run in parallel to EM-1 flight model manufacturing and integration, bringing risk to the program. This risk is carefully monitored and risk reduction strategies are in place to ensure the program can proceed smoothly. The ESM verification is mostly accomplished at module level. A limited number of verifications is planned on the EM-1 flight model.
- The system PDR (Preliminary Design Review) was successfully concluded in the summer 2014.
- The system CDR (Critical Design Review) is scheduled for the end of2015 and will conclude with the board in February 2016.
Table 4: Summary of key aspects for an international partnership in the Orion program
Development status of Orion EM-1 (Exploration Module-1) and ESM (European Service Module):
• March 28, 2019: ESA Director of Human and Robotic Exploration, David Parker, and Associate Administrator for NASA's Science Mission Directorate, Thomas Zurbuchen, signed a Statement of Intent to coordinate joint science research about the Moon and identify opportunities for lunar mission cooperation. 13)
- Signed during the National Academies' Space Science Week in Washington DC, the statement highlights a common interest in accessing the Moon, driven by scientific discovery and support for private-sector capabilities, and mission services on the lunar surface and in the vicinity of the Moon.
- "We are thrilled to be bringing European expertise to the table," said David, "and to work collaboratively to prepare the way to a sustainable presence on the Moon where nations and the private sector work together to deliver benefits for all the people of Earth."
Soon to the Moon
- The Moon has once again captured the attention of space agencies as an 'archive' of cosmic history and a cornerstone for planetary science. Water ice and other possible resources at the Moon offer the possibility of the Moon becoming a 'stepping stone' to the wider Solar System. The US Vice President Mike Pence directed NASA on March 26 to accelerate a human return to the Moon in the next five years.
- ESA's proposal to its Member States for the next period of its European Exploration Program includes continuing its involvement in endeavors in low Earth orbit as well as around and on the Moon and Mars. This will allow scientific research, development of key technologies and international cooperation – inspiring missions that expand humankind's presence beyond Earth.
- In going forward to the Moon, ESA and NASA are committed to sustainable lunar exploration made possible by cooperation – not only with space agencies but also with the private sector. New commercial capabilities offer new opportunities to explore – and to expand economic activity into deep space. Both agencies will continue to explore scientific collaboration on payloads and future missions to the Moon.
- Teaming up is nothing new for ESA and NASA, with both agencies working together on the International Space Station, robotic missions and more recently on the Orion spacecraft, the first spacecraft capable of delivering a crew to the Moon since 50 years.
- ESA is supplying the European Service Module for Orion, in an arrangement that stems from the International Space Station partnership. Based on ESA's proven Automated Transfer Vehicles for supplying the International Space Station, the module will provide everything to keep the astronauts alive, including oxygen, water, thermal control, electricity and propulsion.
- ESA looks forward in cooperation and collaboration to probe the mysteries of the Moon and to use insights found as a springboard towards humankind's future in deep space.
Figure 22: Thomas Zurbuchen, NASA's Associate Administrator for the Science Mission Directorate (left), and David Parker, ESA's Director of Human and Robotic Exploration, signing a Statement of Intent to coordinate joint science research about the Moon and identify cooperative lunar mission opportunities during the National Academies' Space Science Week in Washington, DC, USA, on 27 March 2019. The statement highlights a common interest in accessing the Moon driven by scientific discovery and support for private-sector capabilities and mission services on the surface and in the vicinity of the Moon (image credit: ESA, M. Tabache)
• November 7, 2018: European module arrives at Kennedy Space Center: After a 24-hour journey from Bremen, Germany with stops in Hamburg and Portsmouth, USA, the European Service Module landed yesterday at Kennedy Space Center in Florida. The Antonov An-124 aircraft landed on 6 November 2018 at 11:35 EST, local time. 14)
- The first service module is a key component that will see Orion around the Moon for Exploration Mission-1. It will make the powerful burns required to enter and exit lunar orbit as well as softer burns to allow for space maneuvering and course correction. After years of designing, building, and testing in Europe, the powerhouse that will propel NASA's Orion spacecraft to the Moon will soon be mated with the rest of the spacecraft to undergo final testing before flight.
- The European Service Module is a truly European endeavor. Primary components were built and integrated in Italy and Germany, with smaller components delivered from several European nations, including the solar arrays from the Netherlands.
- ESA's partnership with NASA takes this European effort to the global stage. For the first time, NASA will use a European-built system as a critical element to power an American spacecraft, extending the international cooperation of the International Space Station into deep space.
- The trust in European know-how is thanks to the successful Automated Transfer Vehicle (ATV) program that provided reliable cargo deliveries to the Space Station. ATV's engineering and operational legacy were crucial to developing the European Service Module, which some of its flight-proven hardware, such as the auxiliary thrusters and pressurization tanks.
Figure 23: Orion: an international collaboration. Orion is NASA's next spacecraft to send humans into space. It is designed to send astronauts farther into space than ever before, beyond the Moon to asteroids and even Mars. ESA has designed and is overseeing the development of Orion's service module, the part of the spacecraft that supplies air, electricity and propulsion. Much like a train engine pulls passenger carriages and supplies power, the European Service Module will take the Orion capsule to its destination and back (image credit: ESA, K. Oldenburg)
Legend to Figure 23: The Orion spacecraft is built by NASA with ESA providing the service module. The arrangement stems from the international partnership for the International Space Station. NASA's decision to cooperate with ESA on a critical element for the mission is a strong sign of trust and confidence in ESA's capabilities. More than 20 companies around Europe are now building the European Service Module as NASA works on Orion and the Space Launch System.
- Next steps: Next up for the ESM-1 (European Service Module-1) is unloading and unpacking. The unit will be checked for integrity after its transatlantic flight and then unloaded in the Operations & Checkout (O&C) building at Kennedy Space Center.
- Some parts of the ESM-1 have already been shipped by sea in two containers and are already awaiting the arrival of the larger air shipment. These include nozzle covers, heat shield, and insulation layers, among other components. The solar arrays will arrive in February 2019.
- Once in the O&C, the ESM-1 will be fitted to the Crew Module Adapter (CMA) to form the Orion Service Module. This process takes some time, as all fluid and gas pipes must be welded and electrical wiring connected. The crew module will then be mated with the service module and the completely integrated spacecraft will head to NASA Glenn Research Center's Plum Brook Station in Ohio for a 60-day test campaign. The entire spacecraft will be subjected to intense launch conditions in the world's largest vacuum chamber.
- Once complete, the spacecraft will travel back to Kennedy Space Center to meet its launcher, the Space Launch Systems (SLS) rocket, and prepare for its first mission, a lunar orbital mission without astronauts, to demonstrate the spacecraft's capabilities.
- Work is already underway on the second European Service Module which will provide air, water, and temperature control for the astronauts that will fly on Orion's Exploration Mission-2.
- ESA is immensely proud to play a crucial role in humanity's return to the Moon, thanks to the hard work and determination of the many teams involved in bringing the European Service Module to this next step on the journey back to the Moon.
• November 6, 2018: The powerhouse that will help NASA's Orion spacecraft venture beyond the Moon is stateside. The European-built service module that will propel, power and cool during Orion flight to the Moon on Exploration Mission-1 arrived from Germany at the agency's Kennedy Space Center in Florida on Tuesday to begin final outfitting, integration and testing with the crew module and other Orion elements (Figure 24). 15)
- The service module is integral to human missions to the Moon and Mars. After Orion launches on top of the agency's Space Launch System rocket, the service module will be responsible for in-space maneuvering throughout the mission, including course corrections. The service module will also provide the powerful burns to insert Orion into lunar orbit and again to get out of lunar orbit and return to Earth. It is provided by ESA (European Space Agency) and built by ESA's prime contractor Airbus of Bremen, Germany. NASA's prime contractor for Orion, Lockheed Martin, built the crew module and other elements of the spacecraft.
- "We have a strong foundation of cooperation with ESA through the International Space Station partnership, and the arrival of the service module signifies that our international collaboration extends to our deep space human exploration efforts as well," said Bill Gerstenmaier, NASA's associate administrator for Human Exploration and Operations.
- The European-built service module brings together new technology and lightweight materials while taking advantage of spaceflight-proven hardware. It is comprised of more than 20,000 components, including four solar array wings that provide enough electricity to power two three-bedroom homes, as well as an orbital maneuvering system engine, a recently refurbished engine previously used for in-orbit control by the space shuttle. Beginning with Exploration Mission-2, the module also will provide air and water for astronauts flying inside Orion, which will carry people to destinations farther than anyone has travelled before and return them safely to Earth.
- "Our teams have worked together incredibly hard to develop a service module that will make missions to the Moon and beyond a reality," said Mark Kirasich, NASA's Orion program manager. "It is quite an accomplishment of ESA and Airbus to have completed the developmental work on the module and have this major delivery milestone behind us."
- Now that the service module is at Kennedy, it will undergo a host of tests and integration work ahead of Exploration Mission-1. Engineers will complete functional checkouts to ensure all elements are working properly before it is connected to the Orion crew module. Teams will weld together fluid lines to route gases and fuel and make electrical wiring connections. The service module and crew module will be mated, and the combined spacecraft will be sent to NASA's Glenn Research Center's Plum Brook Station in Ohio early next year where it will undergo 60 days of continuous testing in the world's largest thermal vacuum chamber to ensure Orion can withstand the harsh environment of deep space. Once that testing is complete, it will return to Kennedy for integration with the SLS rocket in preparation for launch.
- NASA is leading the next steps to establish a permanent human presence at the Moon. The first in a series of increasingly complex missions, Exploration Mission-1 is a flight test of an uncrewed Orion spacecraft and SLS rocket that will launch from NASA's modernized spaceport at Kennedy. The mission will send Orion 40,000 miles beyond the Moon and back and pave the road for future missions with astronauts. Together, NASA and its partners will build the infrastructure needed to explore the Moon for decades to come while laying the groundwork for future missions to Mars.
Figure 24: The European Service Module for NASA's Orion spacecraft was loaded on an Antonov airplane in Bremen, Germany, on Nov. 5, 2018, for transport to NASA's Kennedy Space Center in Florida. For the first time, NASA will use a European-built system as a critical element to power an American spacecraft, extending the international cooperation of the International Space Station into deep space (image credit: NASA/Rad Sinyak)
• October 30, 2018: The European Service Module that will power and propel the Orion spacecraft on its first mission around the Moon will ship early next week from Bremen to the United States. It will take off in an Antonov An-124 aircraft in the early hours of 5 November and arrive at Kennedy Space Center in Florida, US on 6 November. 16)
- Designed and manufactured in Italy and Germany, the powerful workhorse is Europe's contribution to humanity's return to the Moon.
- Trusted partner: For the first time, NASA will use a European-built system as a critical element to power an American spacecraft, thanks in large part to ESA's successful Automated Transfer Vehicle (ATV) program that brought supplies to the International Space Station.
- The knowledge gained by ESA and European industry from designing, building and operating the complex and successful Automated Transfer Vehicle missions was instrumental for ESA's participation in NASA's Orion spacecraft.
- The unit resembles ATV, from which it evolved. Three types of engine will propel Orion to its destination and can turn it in all directions to align the spacecraft as needed.
- Inside the European Service Module, large tanks hold fuel as well consumables for the astronauts: oxygen, nitrogen and water.
- Radiators and heat exchangers keep the astronauts and equipment at a comfortable temperature, while the module's structure is the backbone of the entire vehicle, like a car chassis.
- The European Service Module was built by main contractor Airbus Defence and Space, with many companies all over Europe supplying components.
- Once at Kennedy Space Center, the European Service Module will be connected to the Orion crew module and its adapter in preparation for Exploration Mission-1 – a test flight without astronauts that will travel farther into space than any human-rated spacecraft has ventured. The mission is expected to launch in 2020.
- Work is already underway on the second European Service Module that will power a crewed mission around the Moon.
- The Orion spacecraft will eventually launch together with components of the Gateway, a human-tended outpost in lunar orbit that will aid human and robotic exploration of the Moon.
• October 29, 2018: Aerojet Rocketdyne recently completed qualification testing for the enhanced reaction control thruster system for NASA's Orion crew vehicle, helping to clear the way for the Lockheed Martin-built spacecraft's second test flight, and first mission to cislunar space, called Exploration Mission-1 (EM-1). 17)
- The RCS (Reaction Control System) is the only means of guiding the Orion crew module after it separates from its service module in preparation for atmospheric reentry and subsequent splashdown. Consisting of 12 MR-104G hydrazine thrusters capable of 160 pounds of thrust each, the system also will ensure that the spacecraft is properly oriented (with its heat shield pointed downward) for reentry, and stable during descent.
- Aerojet Rocketdyne employed cutting-edge additive manufacturing processes, also known as 3D printing, in fabricating the RCS engine nozzle extensions. These 3D printed components, along with other items on the spacecraft, mark one of the first times in history that a spacecraft carrying humans will incorporate additively manufactured parts.
- "Additive manufacturing eliminates traditional design constraints, as well as reduces manufacturing times," said Eileen Drake, Aerojet Rocketdyne CEO and president. "Our use of 3D printing on Orion is just one example of how we are incorporating this breakthrough technology across our portfolio of propulsion products."
- During the yearlong qualification test program at Aerojet Rocketdyne's Redmond, Washington, facility, a single engine was subjected to shock and vibration, exceeding the maximum stresses expected during the upcoming EM-1 launch. For EM-1, Orion will be launched toward the Moon on the maiden flight of NASA's Space Launch System (SLS) rocket. The non-flight test engine – drawn from the same production lot as the EM-1 RCS flight engines – burned through 619 pounds of propellant during the test program, accumulating 962 seconds of total firing time.
- "Following our rigorous qualification testing program, we're confident that this enhanced RCS system is ready to fly," added Drake. "The reaction control thrusters are critical to the Orion capsule's safe return to Earth at the completion of EM-1 as well as future crewed missions."
- The EM-1 RCS thruster design builds on the flight proven engine demonstrated on the Exploration Flight Test-1 mission in 2014. The enhanced system features a stronger structure, increased resistance to thermal stresses and reduced mass. The improved manufacturing process updated the system to account for changed loads and to ultimately increase affordability.
- On EM-1 an uncrewed Orion spacecraft will launch into a distant retrograde orbit around the Moon before returning to Earth for a splashdown in the Pacific Ocean. It will be followed by EM-2, during which Orion will fly near the Moon with astronauts on board.
- In addition to the RCS, Aerojet Rocketdyne is supplying the main- and upper-stage liquid engines for the SLS, and well as the jettison motor that will separate Orion's launch abort system from the crew module shortly after activation of the SLS's second stage. The company also is supplying the auxiliary thrusters for Orion's European Service Module (ESM), and supported a NASA-led effort to modify a Space Shuttle OMS-E engine, originally built by Aerojet Rocketdyne for its new application as the ESM main maneuvering engine.
• October 23, 2018: After years of planning, development, building and integration, the European Service module that will power the Orion spacecraft on its journey into lunar space is ready to be shipped. In November the fully integrated, tested, and sealed European workhorse will leave Bremen on an Antonov cargo plane for Kennedy Space Center in Florida, USA where it will be integrated with the rest of the Orion spacecraft. 18)
- ESA's European service module will provide power, water, air and electricity to NASA's Orion exploration spacecraft that will eventually fly beyond the Moon with astronauts. The European Service Module is now complete for Orion's first mission that will do a lunar fly-by without astronauts to demonstrate the spacecraft's capabilities.
- Orion's solar wings will be shipped separately, also from Bremen. In the USA the module will be stacked together with NASA's Crew Module Adaptor and Crew Module, the first time the complete spacecraft will be on display.
- More tests await the Orion spacecraft at NASA's Plum Brook facility where it will be put in the world's largest vacuum chamber to simulate spaceflight as well as being subjected to acoustic tests to simulate the intense vibrations Orion will endure when launched on the world's largest rocket, NASA's Space Launch Systems.
- This is a proud moment for Europe. For the first time, NASA will use a European-built system as a critical element to power an American spacecraft, extending the international cooperation of the International Space Station into deep space.
- Work is already underway on the second European Service Module. The structure is complete and over 11 km of cables are being meticulously placed in preparation for the computers and equipment that will keep astronauts alive and well for the second Orion mission called EM-2 (Exploration Mission-2).
Figure 25: Human and robotic exploration image of the week: The European Service Module of the Orion spacecraft is ready for shipment to the US (image credit: Airbus)
• October 2018: Following a very successful year of manufacturing, assembly and testing in factories located around the globe, NASA and ESA are preparing to deliver the major Exploration Mission-1 (EM-1) Orion flight elements, including the Crew Module, ESA Service Module and Launch Abort System. This international effort to design and develop a deep space exploration capable human spacecraft is rapidly transitioning from the design, development and test phase to the early test flight and production phase. Two major flight tests, an Ascent Abort test and EM-1, Orion's first flight onboard NASA's new heavy lift Space Launch System, are planned for the near future. Further, Orion will play a crucial role in the ambitious new Deep Space Gateway human exploration Program. 19)
• September 18, 2018: Last week at the Airbus integration hall in Bremen, Germany, technicians installed the last radiator on the European Service Module for NASA's Orion spacecraft marking the module's finished integration. 20)
- ESA's European service module will provide power, water, air and electricity to NASA's Orion exploration spacecraft that will eventually fly beyond the Moon with astronauts. The European Service Module is now complete for Orion's first mission that will do a lunar fly-by without astronauts to demonstrate the spacecraft's capabilities.
Figure 26: Technicians instal the radiators on the European Service Module for NASA's Orion spacecraft marking the module's finished integration (image credit: ESA–A. Conigli)
- Much like closing the bonnet on a car, with the radiators in place technicians can no longer access the internals of the European service module, symbolically ending the assembly and integration of the module that will fly further into our Solar System than any other human-rated spacecraft has ever flown before.
- Technicians worked 24 hours a day in three shifts to complete the service module's assembly which is now going through the last stages of its extensive testing. Engineers will put the module through its paces with functional tests that include checking the newly installed radiators and testing the propulsion system with its intricate pipelines that deliver fuel and oxidizer to the spacecraft's 33 engines.
Figure 27: View from below: Orion European Service Module-1. Technicians work underneath the European Service Module for NASA's Orion spacecraft, September 2018 (image credit: ESA–A. Conigli)
- Once complete the service module will be packed and flown to NASA's Kennedy Space Center in Florida, USA. Orion's solar wings will be shipped separately, also from Bremen. In the USA the module will be stacked together with NASA's Crew Module Adaptor and Crew Module, the first time the complete spacecraft will be on display.
- More tests await the Orion spacecraft at NASA's Plum Brook facility where it will be put in the world's largest vacuum chamber to simulate spaceflight as well as being subjected to acoustic tests to simulate the intense vibrations Orion will endure when launched on the world's largest rocket, NASA's Space Launch Systems.
- Second module getting ready: Meanwhile technicians in Bremen are not resting as work on the second European Service Module is already well under way. The structure is complete and over 11 km of cables are being meticulously placed in preparation for the computers and equipment that will keep astronauts alive and well for the second Orion mission called Exploration Mission-2.
• August 16, 2018: Technicians at NASA's Kennedy Space Center (KSC) in Florida recently secured the heat shield to the bottom of the crew module, using 68 bolts. Designed and manufactured by Orion prime contractor, Lockheed Martin, the heat shield is like an intricate puzzle with pieces that all have to fit together perfectly. Before the final installation, a fit check was performed to ensure all of the bolt fittings lined up. 21)
Figure 28: Lockheed Martin engineers and technicians check fittings during installation of the heat shield to the Orion crew module July 25, 2018, inside the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida (image credit: NASA)
- "Installation of the EM-1 crew module heat shield is a significant milestone representing the beginning of closing out the crew module assembly," said Jules Schneider, Lockheed Martin Orion senior manager for KSC Operations. "When the heat shield is installed, access to components becomes more difficult, and in some cases there is no more access. So by installing the heat shield you are declaring that a certain percentage of the spacecraft is finished."
- Measuring 5.06 m in diameter, Orion's new heat shield is the largest of its kind developed for missions that will carry astronauts. The heat shield base structure has a titanium truss covered with a composite substrate, or a skin composed of layers of carbon fiber material.
- In a new process, several large blocks of an ablative material called Avcoat, licensed from Boston-based Textron Systems, were produced at Michoud Assembly Facility in New Orleans by Lockheed Martin. They were shipped to Kennedy, where Lockheed Martin technicians machined them into more than 180 unique blocks and bonded them to the heat shield's surface.
- To fill tiny gaps between the blocks, the seams were filled with a mixture that over time will become solid. Technicians applied a coat of white epoxy paint to the heat shield's surface and then applied aluminized tape after the painted surface dried. The tape provides surface resistivity, and absorbs solar heat and infrared emissions.
- While Avcoat isn't new to spacecraft – it was used on the heat shields of Apollo and the Orion EFT-1 (Exploration Flight Test-1) – the technique of using blocks instead of injecting the ablative material is proving to be a real production time-saver.
- "A benefit of switching from the honeycomb system to the blocks is we now can make the Avcoat blocks at the same time that the Orion structure is being made, and when the module is ready we can secure the blocks, which saves time," said John Kowal, NASA Orion Thermal Protection System manager at Johnson Space Center in Houston. "Before, with EFT-1, we had to wait for the carrier portion to be done, and then apply the Avcoat directly to the crew module."
- During its first mission around the Moon, engineers will monitor how Orion's systems perform in the environment of deep space and its return to Earth. During re-entry the ablative material of the Avcoat blocks will burn away, essentially carrying the heat away from Orion because of the gases created during the ablative process.
• June 6, 2018: At centers across NASA, the agency is rocketing ahead toward Exploration Mission 1 (EM-1) and Exploration Mission 2 (EM-2). 22)
- EM-1 and EM-2 are the final stages of a three-part mission series designed to establish NASA's new Exploration Class human spaceflight capability. The first stage, Exploration Flight Test 1 (EFT-1), was completed in 2014 when a Delta IV Heavy rocket sent the uncrewed Orion capsule 3,600 miles from Earth.
- "It was the first time that we had flown a vehicle designed to carry humans that far away from Earth," said Dr. Ellen Ochoa, former Johnson Space Center (JSC) director, speaking at JSC about ongoing efforts to expand manned deep space exploration. "[EFT-1] was testing the items that are really most critical for crew survival, including things like the parachute system and the heat shield. It made headlines not only around the country but around the world. And it's really just a hint of things to come."
- The next stage of the mission is EM-1. Scheduled for 2020, it will be the first integrated flight of Orion and the Space Launch System (SLS), the world's most powerful launch vehicle. EM-1 will be followed by EM-2 in 2023: the first flight to unite crew with Orion and the SLS. EM-2 will take astronauts 40,000 miles past the moon—farther than any manned spacecraft has ever gone.
- Before EM-2 can get off the ground, the agency will conduct a flight test in 2019 called the Ascent Abort-2 (AA-2). The test will examine Orion's launch abort system (LAS), which makes it possible to rescue the crew in the event of a catastrophic malfunction during launch.
- "It's really the only full-scale system test that we have before we put crew on the vehicle. So it's definitely critical for making sure that we can get the crew safely away in an emergency," said Jennifer Devolites, AA-2 crew module deputy manager.
- For the three-minute test, the LAS will be launched from Cape Canaveral on a solid rocket motor providing 500,000 pounds of thrust (2224 kN) to propel the system six miles up to the abort condition. At that point, the crew module flight computers will send commands to light the abort motor rocket and separate the crew module from the booster.
- "When the abort motor fires, it pulls the crew module away from the booster extremely fast. After 1.1 seconds after abort, we've got greater than five F-22 fighter jets on full afterburners in terms of thrust," said Devolites. "After 15 seconds, the crew modules gain more than two miles of altitude. At around 43,000 feet, the attitude control motor starts to reorient the system. And then after reorientation is complete, the LAS separates to allow the capsule to descend safely back to Earth."
- Work on the rest of the Orion spacecraft is moving forward as well. "Orion is more than just a crew module. It's a complex set of systems—life support, propulsion, thermal control," said Annette Hasbrook, assistant manager for Orion Program Integration. "Down at the Kennedy Space Center, we're making great progress. That is our production facility and that's where we're assembling the Exploration Mission 1 spacecraft."
- Below the crew module sits the ESM (European Service Module), which is being provided by ESA (European Space Agency). "The ESM is being assembled in Bremen by the Airbus Corporation," said Hasbrook. "They are in almost final assembly and test and will be bringing that service module, delivering it to the Kennedy Space Center later this summer. Once that arrives, we have a 404-day timeline from the time we bring it in until we turn it over to the ground systems at Kennedy Space Center for final integration onto the amazing SLS rocket for launch."
- The agency is also in build for EM-2. "We have multiple vehicles in flow, and the Exploration Mission 2 spacecraft is currently under assembly at the Michoud Assembly Facility down in Louisiana. They're building their primary structure and that's going to be delivered to KSC later this summer to begin its integration," Holbrook added.
- While work continues on Orion and the SLS, NASA is also making plans to build the Lunar Orbital Platform-Gateway in the 2020s. This manned spaceport, which will be constructed on orbit, will include a power and propulsion element as well as habitation, logistics, and airlock capabilities.
- "NASA and its partners will use the Gateway for deep space operations, including missions on the moon, with decreasing reliance on Earth. We'll use the lunar orbit as a place to stage: where we will actually build up a small crew-tended spaceport that will then do testing. We will learn about what's going on at the moon, we'll do testing on the moon surface, and then we will build up, do other testing, and move on to Mars," said Vanessa Wyche, director of the Exploration Integration and Science Directorate at JSC.
- The power and propulsion element for the Gateway is being led by NASA/GRC (Glenn Research Center). The habitation systems are in design, with concepts being worked by five commercial partners. "Of those five companies, there are two that are going to do ground testing here at the Johnson Space Center. We're readying ourselves for the hardware to show up so that we will test it. That will happen next summer," added Wyche.
- At JSC, the work for EM-1 and EM-2 is being conducted using a "lean development" approach. "That's been really one of the goals of this project as well. To look at how we can do things differently. Find more efficiencies," said Devolites.
- One of the areas they have focused on is developing a team culture that encourages people to innovate. "We also reduce cost and schedule through iterative systems engineering," said Devolites. "By doing that, we actually had 90% of our flight software complete by the time we got to our Critical Design Review because of all the early integrated testing that we did. And we also used an agile software development process for that." Additionally, the center employs a data-centric, online collaborative system to enhance systems engineering and team communication. This has produced two important results: less paperwork and fast decision-making.
- While the focus of EM-1 and EM-2 is on advancing human spaceflight farther than ever before, the mission benefits can be felt on Earth as well. NASA's work on Orion and the SLS is supported by companies in 49 of the 50 states. These efforts are fueling industries and technology development across the nation, helping advance job opportunities and workforce skill development.
• April 23, 2018: The European service module that will provide power, water, air and electricity to NASA's Orion Moon module has taken a large step closer to completion with the installation of its fuel tanks and testing of its solar wings. 23)
- The large tanks that will provide propellant for the spacecraft are now fitting snugly inside the spacecraft at the Airbus assembly hall in Bremen, Germany.
Figure 29: The large tanks that will provide propellant for the spacecraft are now fitting snugly inside the spacecraft. The four tanks will each contain about 2000 liters of propellant. In the vacuum of space there is no air to burn so spacecraft fuel tanks include oxidizer and fuel that are mixed to ignite and provide thrust (image credit: Airbus)
Legend to Figure 29: The two sets of tanks are connected by intricate pipelines to 33 engines. Sensors and computers control the system. The European service module is a small but complex spacecraft packed with equipment. The large tanks are installed as one of the last components to allow technicians more room to work.
- Meanwhile the solar arrays Orion will use to produce electricity are being tested at ESA's technical heart in the Netherlands. Folded for launch, the fragile solar panels need to survive the rumbling into space aboard the most powerful rocket ever built, NASA's Space Launch System.
- Orion's solar panels will be folded inside the rocket fairing on the first leg of the trip around the Moon. Once released from the rocket they will unfold and rotate towards the Sun to start delivering power.
- To make sure the solar panels will work after the intense launch, ESA engineers are putting them through rigorous tests that exceed what they will experience on launch day. This includes vibrating them on a shaking table and placing them in front of enormous speakers that recreate the harsh launch conditions.
• April 20, 2018: A few multi-layer windows on a spacecraft provide astronauts the view they may need for navigating space and carrying out their exploration mission with visual data. NASA is working to improve the durability of those windows, and reduce cost and weight, while maintaining the clarity astronauts need to carry out their tasks and view the Earth and other destinations as they travel farther into the solar system. 24)
- The space shuttle used only glass panes for its primary windows. While these provided good optical quality, they added costly mass to the spacecraft. Modern spacecraft windows incorporate acrylic and other plastics that are lighter, stronger and less brittle, but often provide lower quality optical properties.
Figure 30: Inside a laboratory in the Neil Armstrong Operations and Checkout Building at NASA's Kennedy Space Center in Florida, Mark Nurge, Ph.D., at left, a physicist in the Applied Physics Lab with the center's Exploration Research and Technology Programs, and Bence Bartha, Ph.D., a specialist in non-destructive testing with URS Federal Services, are performing the first optical quality testing on a full window stack that is ready for installation in the docking hatch of NASA's Orion spacecraft. The data from the tests will help improve the requirements for manufacturing tolerances on Orion's windows and verify how the window should perform in space. Orion is being prepared for its first integrated uncrewed flight test atop NASA's Space Launch System rocket on Exploration Mission-1 (photo credit: NASA/Amanda Griffin)
• March 6, 2018 (update), Jan. 5, 2018: Engineers preparing NASA's deep space exploration systems to support missions to the Moon, Mars, and beyond are gearing up for a busy 2018. The agency aims to complete the manufacturing of all the major hardware by the end of the year for EM-1 (Exploration Mission-1), which will pave the road for future missions with astronauts. Planes, trains, trucks and ships will move across America and over oceans to deliver hardware for assembly and testing of components for the Orion spacecraft and the SLS (Space Launch System) rocket while teams at NASA's Kennedy Space Center in Florida prepare the Ground Systems infrastructure. Testing will take place from the high seas to the high skies and in between throughout the year and across the country, not only in support of EM-1, but also for all subsequent missions.25)
• March 5, 2018: With the arrival of the Orion crew module to be used in the Ascent Abort-2 test at Johnson Space Center in Houston, the team is already at work with a lean, iterative development approach to minimize cost and ensure the flight test stays on schedule. 26)
- The approach involves considering how to do things differently, finding ways to execute elements of the buildup more efficiently and pushing on the norms of doing business to see if there are areas where productivity can be enhanced.
- Engineers and technicians at NASA/LaRC (Langley Research Center) in Hampton, Virginia modified a previously built Orion test vehicle for the flight. Development hardware from the Pad Abort-1 test is being reused and components such as radio frequency transmitters have been repurposed to support characterization and integrated tests. Shuttle heritage hardware, such as pyrotechnic control cards that otherwise were not being used, are being integrated into flight designs which allows the team to avoid building or building everything new. Flight and ground software architectures have been evolved from other development projects.
- Engineers involved in outfitting the crew module simultaneously are being trained to be flight controllers who will supervise the test when it launches from Cape Canaveral Air Force Station in Florida. Since the engineers involved in the work are extremely knowledge about the vehicle's systems, they are being trained as operators and builders at the same time.
- Several milestones lay ahead of the team now that the crew module has arrived at Johnson. In the spring, various subsystem elements will be incorporated into the vehicle. In June, it will be powered "on" for the first time to ensure all the proper connections are made and the vehicle can execute its flight profile. After testing and verification, the crew module will be attached to a test rig and rotated sideways so engineers can once again measure mass and center-of-gravity. These attributes must mirror those projected for the first Orion with crew to ensure the AA-2 crew module will provide representative data.
- "We're going to integrate hundreds of elements into the crew module," said Jon Olansen, manager of the Ascent Abort-2 test crew module. "To get the vehicle ready to execute this critical test for future crew safety, we will install the avionics, power and communication components, the guidance, navigation and control instruments, all the interconnecting electrical wiring, and load the software to control it all. We will also install the flight instrumentation and data retrieval systems and a variety of sensors that will collect data essential for characterizing the performance of the vehicle during and after an abort."
- Once complete, the crew module will be sent to NASA Glenn's Plum Brook Station in Ohio, where it will undergo testing in an acoustic chamber to characterize how the structure will react to the abort environment. While the crew module is at Plum Brook, a separation ring that will connect the capsule to its booster will arrive at Johnson and be outfitted with wiring and other necessary elements. The crew module will return to Johnson in September and be mated with the separation ring before the two elements are then tested together and shipped to Kennedy Space Center in December.
- NASA's work to build the test article and execute the flight test is a combined effort between the Orion Program and Advanced Exploration Systems Division at NASA Headquarters in Washington.
Figure 31: Technicians lower the crew module for Ascent Abort-2 onto a stand at Johnson Space Center in Houston on March 2 (image credit: NASA, Robert Markowitz)
• February 16, 2018: When NASA's Orion spacecraft launches into space atop the agency's Space Launch System rocket on its first uncrewed integrated flight, Exploration Mission-1, it will travel thousands of miles beyond the Moon and return to Earth for splashdown in the Pacific Ocean. While traveling to deep space, Orion will experience extreme hot and cold temperatures, with re-entry temperatures nearing 5,000 degrees Fahrenheit (~2700ºC). 27)
- Before Orion is exposed to the harsh conditions of launch, deep space and re-entry, it is being prepared and tested inside the Neil Armstrong Operations and Checkout Building high bay at Kennedy Space Center in Florida.
- The Orion Program successfully completed a thermal cycle test on the Orion crew module inside a specially constructed thermal cycle chamber in the airlock of the high bay. Over the next five days, the crew module was rapidly cycled between hot and cold temperatures to thermally stress the hardware and ensure the workmanship of the crew module's critical hardware and its subsystem operations. The cycle of temperatures for the initial thermal test ranged from 29º to 129ºF (-1.66ºC to 53.9ºC) during 105 hours of testing.
- "Our goal was to expose the vehicle to rapid changes in temperature to see how Orion and its systems performed," said Rafael Garcia, Orion Program Test and Verification lead. "When the test was completed, we found no major issues."
- NASA and Lockheed Martin engineers in three different areas conducted and monitored the test, including the team in the high bay near the chamber controls, the ground test instrumentation readout area, and the Test and Launch Control Center, where system managers powered on and monitored the crew module's subsystems.
- A thermal cycle test of Orion's integrated crew and service module, along with electromagnetic interference and compatibility testing, is scheduled for early next year at NASA Glenn's Plum Brook Station in Sandusky, Ohio. While testing at Kennedy helps ensure Orion is ready for EM-1, Plum Brook facilities can simulate more extreme conditions and will help validate the integrated spacecraft design for future missions. The service module is the powerhouse of the spacecraft, providing it with the electricity, propulsion, thermal control, air and water it will need in space.
- During EM-1, the Orion crew module structure will reach temperatures ranging from minus 300 F to plus 250 F (-184ºC to +121ºC) depending on the Sun's angle on its way to the Moon.
• February 14, 2018: Construction of the living and working area for the first crewed Orion spacecraft is well underway at the Michoud Assembly Facility (MAF) in New Orleans. Building on lessons learned from previous construction, Orion prime contractor Lockheed Martin has already completed four of the seven welds necessary to assemble the crew module pressure vessel. 28)
- Current schedules call for the completed pressure vessel to be shipped in September to the Kennedy Space Center (KSC) in Florida, where it will be outfitted to fly on EM-2 (Exploration Mission-2).
Figure 32: EM-2 welding taking place at MAF (image credit: NASA)
• October 12, 2017: While engineers in Europe continue to outfit the Orion spacecraft's service module for EM-1 (Exploration Mission-1) in preparation for shipment to NASA's Kennedy Space Center in Florida next year, work is already beginning on the service module that will power, propel, cool and provide air and water for the first crewed mission in the Orion spacecraft in the early 2020s. Technicians at Thales Alenia in Turin, Italy, are working on the primary structure of the European Service Module that will carry astronauts in Orion beyond the Moon during EM-2 (Exploration Mission-2). ESA (European Space Agency) and its contractors are providing Orion's service module for its first two missions atop the Space Launch System rocket. NASA is leading the next steps in human space exploration and will send astronauts to the vicinity of the Moon to build and test the systems needed for challenging missions to deep space destinations including Mars. NASA is working with domestic and international partners to solve the great challenges of deep space exploration. 29) 30) 31)
Figure 33: Work progresses on Orion Powerhouse for Crewed Mission (image credit: NASA, Rad Sinyak)
• August 24, 2017: Engineers at Lockheed Martin and NASA breathed life into the next Orion crew module when they powered up the spacecraft for the first time at the Kennedy Space Center, Florida. Designed for human spaceflight, this Orion will be the first to fly more than 60,000 km beyond the Moon during its nearly three-week EM-1 (Exploration Mission-1), a feat that hasn't been possible before. 32) 33)
- "Orion was designed from the beginning to take humanity farther into space than we've ever gone, and to do this, its systems have to be very robust and reliable," said Mike Hawes, vice president and Orion program manager at Lockheed Martin. "Over the last year, we've built great momentum in assembling the crew module for EM-1. Everyone on the team understands how crucial this test campaign is, and more importantly, what this spacecraft and mission means to our country and future human space flight."
- The initial power-on event was the first time the vehicle management computers and the power and data units were installed on the crew module, loaded with flight software and tested. Evaluating these core systems, thought of as the "brain and heart" of the Orion capsule, is the first step in testing all of the crew module subsystems.
- Although astronauts will not fly in this capsule on this flight, a large majority of the subsystems and avionics are the same design that astronauts will rely on during following missions with Orion into the solar system. Launching on NASA's Space Launch System — the most powerful rocket in the world — the EM-1 flight is critical to confirming the Orion spacecraft and all of its interdependent systems operate as designed in the unforgiving environment of deep space.
- With the successful initial power on behind them, engineers and technicians will now continue integrating the 55 components that make up the spacecraft avionics suite, connecting them with nearly 400 harnesses. Over the course of the next two to three months, as each system is installed, they will perform thorough functional tests to ensure Orion is ready to move to the all-important environmental testing phase.
• April 6, 2017: Curtiss-Wright's Defense Solutions division has successfully delivered eight of the nine data acquisition flight units that it is building for use on NASA's Orion spacecraft planned for use in EM-1 (Exploration Mission-1), Orion's second test flight in space. 37)
- For the Orion EM-1 flight, Curtiss-Wright supplies its MnACQ-2000 Miniature Network Data Acquisition System, a compact, stackable Fast Ethernet 100BASE-T-based networked encoding unit that processes and delivers packetized instrumentation data to designated network nodes. Each of the nine rugged COTS-based units built for Orion EM-1 includes a radiation tolerant power supply, system management overhead and the specific signal conditioning modules needed to address the number and type of measurements needed during flight.
- Two 12-Port Ethernet switches that tie the system together and route the data and video have also been delivered for the Orion EM-1 flight. Curtiss-Wright expects to deliver the ninth and final MnACQ-2000 by the end of June 2017.
• February 27, 2017: ESA's contribution to NASA's Orion spacecraft is the European Service Module, providing the spacecraft with its main power source and propulsion mechanism. Designed by Airbus Defence and Space and assembled by OHB Sweden, the Propulsion Qualification Model was shipped to the NASA's White Sands facility in January. 38)
- The model is now set up and awaiting extensive testing by NASA, ESA and Airbus. Its 21 engines, including the Shuttle OMS (Orbital Maneuvering System) engine, eight auxiliary thrusters and 12 smaller thrusters will undergo ‘hot firing', in which all engines will be ignited.
Figure 34: The European propulsion system of the Orion spacecraft has been installed at NASA's White Sands Test Facility in New Mexico and is ready for testing (image credit: NASA)
• February 16, 2017: Airbus DS has signed a new contract with ESA (European Space Agency) for the construction of the second European service module (ESM) for NASA's Orion spacecraft. The contract is worth around € 200 million. The ESM is a key element of Orion, the next-generation spacecraft that will take astronauts beyond LEO (Low Earth Orbit) for the first time since the end of the Apollo program. 39)
• In mid-January 2017, Airbus Defence and Space delivered to NASA a propulsion test module for the Orion program. The PQM (Propulsion Qualification Test Model) will be used to check that the Orion ESM (European Service Module) spacecraft's propulsion subsystem functions correctly. On behalf of ESA, Airbus DS is the prime contractor for the ESM, a key element of NASA's next generation Orion spacecraft. 40)
- Although the PQM will never see space, this is an important step in the development of the Orion program. Complex systems for human spaceflight must first be tested and qualified on Earth before being used as flight hardware in space. The engineers want to determine how the system behaves in different environments, to ensure that it functions properly.
- The test module is travelling via Bremerhaven and Houston / USA to its final destination at NASA's WSTF (White Sands Test Facility) near Las Cruces in New Mexico / USA. Arrival is expected mid-February. The tests will take place later in the year at WSTF for the qualification of Orion ESM's propulsion subsystem.
• On December 12, 2016, ESA handed over ownership of the Orion European Service Module test article to NASA at the agency's Plum Brook facility in Sandusky, Ohio – marking the end of individual testing for the structure. 41)
- The module sits directly below Orion's crew capsule and provides propulsion, power, thermal control, and water and air for four astronauts. The solar array spans 19 m and provides enough electricity to power two households.
- From a design perspective, the launch is one of the most demanding moments in a mission. Orion will sit atop the SLS (Space Launch System) and more than 2500 tons of propellant. The vibrations and forces are intense until they reach the relative calm of space.
- To ensure the service module can withstand these forces, it is placed on a large table that shakes and moves to recreate the vibrations of launch. Almost 1000 sensors monitor how the 35 ton spacecraft flexes and withstands the stress. The blue wires carry the data during the tests for later analysis.
- The tests are running smoothly and the first flight model is already being built in Bremen, Germany. It will be shipped to the USA next year for more testing and final integration ahead of launch at the end of 2018.
Figure 35: This test article of the Orion ESM has the same structure and mass as the real thing but does not include the electronics and engines. It is being used to confirm the design before starting to build the flight version (image credit: ESA)
Orion / EM-1 Continued
• January 2, 2017: A former space shuttle OMS-E (Orbital Maneuvering System-Engine) has been delivered to Germany for attachment to the European-built service module destined to steer NASA's next Orion spacecraft (EM-1) on a course around the moon on an uncrewed test flight in late 2018. 42)
- The engine was refurbished and reassembled at NASA's White Sands Test Facility in New Mexico, then shipped to Johnson Space Center in Houston for shake testing and returned to White Sands for leak tests, according to an ESA (European Space Agency) blog post. 43)
- It flew from Dallas/Fort Worth International Airport to Frankfurt last month, and then continued its journey by truck to Airbus Defense and Space's spacecraft assembly facility in Bremen, Germany, ESA said.
- ESA is providing the service modules for at least the next two Orion missions — an unpiloted shakedown cruise in lunar orbit scheduled to lift off in November 2018, and the first Orion flight with astronauts on-board in the early 2020s.
- European governments agreed to pay for the service module for the 2018 flight, named EM-1 (Exploration Mission-1), at a meeting of government ministers in December 2012. ESA member states last month committed funding for a second service module for EM-2 (Exploration Mission-2), which will carry up to four astronauts farther than the moon's orbit as soon as 2021.
Figure 36: Orion's service module engine, OMS-E, undergoes vibration testing at NASA/JSC (Johnson Space Center) in Houston (image credit: NASA)
- The service module has 33 engines and thrusters to control the Orion capsule's orientation and adjust its trajectory after launch. The main engine for EM-1 is a refurbished OMS-E (Orbital Maneuvering System-Engine) that flew on 19 space shuttle missions.
- The OMS engines were mounted on pods on each side of the shuttle's vertical tail, used to change the craft's orbit and begin the spaceship's trip back to Earth with a de-orbit burn.
- The ESM (European Service Module) has 33 engines and thrusters to control the Orion capsule's orientation and adjust its trajectory after launch. The main engine for EM-1 is a refurbished Orbital Maneuvering System engine that flew on 19 space shuttle missions (Figure 37).
- The OMS engines were mounted on pods on each side of the Shuttle's vertical tail, used to change the craft's orbit and begin the spaceship's trip back to Earth with a de-orbit burn. - The engines burn hydrazine and nitrogen tetroxide propellants, and were each designed for 100 missions and rated for multiple restarts on each flight. Aerojet Rocketdyne built the OMS engines, which provide around 26.6 kN of thrust in vacuum.
- The OMS engine slated to launch on EM-1 flew on the shuttle Challenger, Discovery and Atlantis in its career. Its first launch was on the STS-41G mission in October 1984, and its last shuttle mission was STS-112 in October 2002.
Figure 37: The Shuttle Atlantis touches down at KSC's Shuttle Landing Facility runway on Oct. 18, 2002. One of the OMS engines mounted on each side of the tail will fly on Orion's EM-1 mission beyond Earth orbit in late 2018 (image credit: NASA)
- The European-built service module is in the "critical path" for EM-1 to remain on track for its launch readiness window, which runs from September through November of 2018. The service module is due for delivery to NASA/KSC (Kennedy Space Center) in Florida in April 2017 — after engineers in Germany add the OMS engine and propellant tanks to the already-finished primary structure.
- At KSC, ground crews will connect the service module with the Orion crew module, then ship the spacecraft to NASA's Plum Brook Station in Ohio by the end of 2017 to subject it to the extreme temperatures and vacuum conditions it will encounter in space.
- The craft will return to KSC in early 2018 for final assembly steps, including the spacecraft's fueling and the addition of the Orion launch abort system before the stack is mounted on top of NASA's SLS (Space Launch System) inside the Vehicle Assembly Building for rollout to launch pad 39B.
Figure 38: Artist's rendition of the Orion spacecraft with the European-built service module (image credit: NASA)
• December 7, 2016: ESA and NASA are extending their collaboration in human space exploration following confirmation that Europe will supply a second Service Module to support the first crewed mission (EM-2)of the Orion spacecraft. The mission is set for launch from NASA's Kennedy Space Center in Florida, USA, as early as 2021 and will include up to four astronauts – the first time humans have left low orbit since 1972. Crew size and composition will be determined closer to launch. 44)
• Nov. 21, 2016: The processing activity at NASA/KSC (Kennedy Space Center) in Florida has ramped up in preparation for the agency's launch of the Orion spacecraft atop the SLS (Space Launch System) rocket on its first deep space mission, Exploration Mission 1 (EM-1). The Orion CMA (Crew Module Adapter) for EM-1 was lifted for the first and only time, Nov. 11, during its processing flow inside the Neil Armstrong Operations and Checkout (O&C) Building high bay at KSC. 45)
- The CMA will connect the Orion crew module to the European Space Agency-provided service module. The Orion spacecraft will launch on the SLS rocket on EM-1 scheduled for late 2019.
Figure 39: Image of the CMA uplift on Nov. 11. The CMA is now undergoing secondary structure outfitting (image credit: NASA, Glen Benson)
• Sept. 19, 2016: The Orion heat shield that will protect the Orion crew module during re-entry after the spacecraft's first uncrewed flight atop NASA's Space Launch System rocket in 2018 arrived at the agency's Kennedy Space Center in Florida on on August 25. It was transported to the Shuttle Landing Facility, which is managed and operated by Space Florida, aboard NASA's Super Guppy aircraft. 46)
- The shipping container with the heat shield inside was offloaded and transported to the Neil Armstrong Operations and Checkout (O&C) Building high bay where technicians uncrated and secured it on a stand to begin the work to prepare it for Orion's next test flight, known as EM-1 (Exploration Mission-1).
- The heat shield was designed and manufactured by Lockheed Martin in the company's facility near Denver. Orion's heat shield will be capable of withstanding temperatures of up to 2750ºC during reentry into Earth atmosphere. The heat shield measures 5 m in diameter, making it the largest of its kind.
Figure 40: Inside the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, technicians assist as a crane lifts the Orion heat shield for EM-1 away from the base of its shipping container (image credit: NASA, Dimitri Gerondidakis)
• June 27, 2016: NASA and ESA conducted a CDR (Critical Design Review) culminating in a final review board June 16 for Orion's European-built service module (Figure 41). The service module is an essential part of the spacecraft that will power, propel, and cool Orion in deep space as well as provide air and water for crew members. The CDR rounds out the latest in a series of reviews for the three human exploration systems development programs that will enable the journey to Mars. 47)
- The recently completed review focused on the overall service module design while discussing differences between Orion's first deep space mission atop the SLS (Space Launch System) rocket and the mission to follow that will carry crew. No new major issues were identified during the review, and the teams worked together to develop a plan for work going forward in areas such as power, solar array management and propellant usage.
- "The teams at NASA and ESA worked together successfully over the past few weeks to bring design decisions and required products to the CDR board," said William Gerstenmaier, associate administrator for NASA's Human Exploration and Operations Mission Directorate. "International collaboration is an important part of the effort NASA is leading to pioneer deep space."
- The review was conducted at ESA/ESTEC (European Space Research and Technology Center) in Noordwijk, the Netherlands with teams from NASA, ESA, Lockheed Martin and Airbus Defence & Space in Bremen, Germany. Lockheed Martin is NASA's main contractor building Orion, and Airbus is ESA's contractor for the service module.
- The CDR identified April 2017 as the target for the service module delivery to Kennedy Space Center in Florida. Teams will begin integrating hardware into the rocket before the service module is delivered, and NASA plans to continue to optimize processing when it arrives at Kennedy. Initial results maintain EM-1 launch date no later than November 2018.
• May 25, 2016: Replicating the thunderous noise of a rocket launch is no easy task, but engineers at NASA Glenn's Plum Brook Station in Sandusky, Ohio are mimicking the launch environment the Orion spacecraft will experience on a 2018 mission beyond the moon. They recently concluded a series of tests on a structural representation of the Orion service module to help ensure it can withstand the force and pressure of the acoustics environment it will experience as it makes its way from the launch pad to space atop NASA's Space Launch System rocket. 48)
- Orion's service module is a critical piece of the overall spacecraft. Provided by ESA (European Space Agency) and built by Airbus Defence & Space, the 13 ton component will be responsible for propelling, powering and cooling the vehicle, as well as providing air and water for its eventual crew.
- When a powerful rocket launches, it can produce noise of up to 180 decibels, levels so high that it can vibrate and damage spacecraft components if they aren't designed and built to be strong enough to withstand the environment. For comparison, a person standing about 100 m away from a jet taking off would experience approximately 130 decibels of sound pressure, and for every additional 10 decibels, sound intensity increases 10-fold.
- While engineers have designed Orion components to endure a range of harsh environments like launch and missions in space, testing on the ground helps to validate computer modeling predictions. "Orion is undertaking an unprecedented mission, so the acoustics testing we've done is helping us make sure the service module will fare as we expect it to," said Aron Hozman, lead engineer for the acoustics testing campaign.
- Engineers performed numerous evaluations at different decibel levels over the course of several weeks in Plum Brook Station's Reverberant Acoustic Test Facility. The facility is the world's most powerful spacecraft acoustic test chamber. In it, a series of modulators or horns embedded on one of the facility's walls and supporting subsystems such as a gaseous nitrogen generation system and a hydraulic supply system were used to modulate noise and produce a wide range of acoustic spectra.
- The series of testing was done in two configurations – one with "wet" tanks where the service module's propellant tanks were filled with a simulant that modeled the density of Orion fuel, and with them empty to determine if the noise affected the structure differently. The maximum test with fuel simulant lasted approximately three minutes. Engineers also used the testing to help qualify the service module's solar array wing. They placed a microphone inside the test article and determined that the noise in the test chamber matched the expected acoustic environment inside the service module where the wing is housed.
- The service module structural test article will next move to Plum Brook Station's Mechanical Vibration Facility, a powerful spacecraft shaker system that will help assess the component's ability to withstand the tremor that an SLS launch will produce. As these ground tests continue to validate the service module's design, the first flight unit service module for EM-1 is now being built in Europe. This unit, which will be built by the same teams who built the structural test article, recently arrived to Airbus' facility in Bremen, Germany for integration. It is expected to be shipped to the United States in 2017.
• May 19, 2016: Airbus DS has started assembling the ESM (European Service Module), a key element of NASA's next-generation Orion spacecraft that will transport astronauts into deep space for the first time since the end of the Apollo program. Integrating more than 20,000 parts and components in the ESM flight model ranging from electrical equipment to rocket engines, solar arrays, tanks for propellant and life support consumables as well as hundreds of meters of cables and tubes marks a major milestone for the Orion program. After the arrival of the flight model structure from Thales Alenia Space Italy the assembly is being carried out at Airbus Defence and Space's site at Bremen, Germany, where officials from ESA, NASA, Airbus Defence and Space and partners gave an update on the Orion program's progress on May 19. 49)
- The ESM is cylindrical in shape and about four meters in diameter and in height. It features the ATV's (Automated Transfer Vehicle) distinctive four-wing solar array (19 m across unfurled) that generates enough electricity to power two households. Its 8.6 tons of propellant will power one main engine and 32 smaller thrusters. The ESM has a total mass of just over 13 tons. In addition to the main propulsion capability for the Orion spacecraft, the ESM will perform orbital maneuvering and attitude control functions. It also provides the main elements of the life support system such as water and oxygen for the crew while providing power and thermal control while it is docked to the crew module. The unpressurized service module can also be used to carry additional cargo.
• May 11, 2016: The EM-1 has passed a critical series of proof pressure tests which confirm the effectiveness of the welds holding the spacecraft structure together. Lockheed Martin, the manufacturer of the Orion crew module, ran the test at incremental steps over two days to reach the maximum pressure. During each step, the team pressurized the chamber and then evaluated the data to identify changes for the next test parameter. The results revealed the workmanship of the crew module pressure vessel welds and how the welds reacted to the stresses from the pressurization. 50)
• April 29, 2016: The first European hardware to arrive at NASA for Orion is the ESM (European Service Module) structural test article. This test version of the service module has the same mass and configuration as the real thing and will undergo advanced testing at NASA's Plum Brook Station in Ohio, USA. 51)
Figure 41: Photo of the European Structural Test Article which undergoes testing in NASA's acoustic test facility in Plum Brook, Ohio, USA (image credit: NASA)
• On 29 February 2016, a test model of Orion's solar array was unfolded at NASA's Plum Brook Station test facility in Sandusky, Ohio to check everything works as expected. The solar panels were made by Airbus Defence and Space in the Netherlands for the ESA module that will supply power and life support for up to four astronauts. 52)
- Each wing stretches more than 7 m, folded inside the SLS (Space Launch System's) rocket of NASA that will launch the spacecraft on its first unmanned mission in 2018. Orion sports four wings of three panels with 1242 cells per panel to provide 11.1 kW of power – enough to run two typical European households. The distinctive X-wings are an evolution and improvement of ESA's ATV (Automated Transfer Vehicle).
- The test was passed with flying colors as the 260 kg array unfurled into its flight configuration. The stresses of flying to the Moon and beyond – and back again – mean the array is designed to bend up to 60º forward and backward, much like a bird in flight.
Figure 42: Photo of the Orion wing array unfolding test at NASA's Plum Brook Station (image credit: ESA)
• Feb. 2. 2016: NASA's unique Super Guppy aircraft, loaded with the structural backbone for NASA's next Orion crew module, swooped in for a landing at the KSC (Kennedy Space Center) on Feb. 1, 2016 (coming from NASA's Michoud Assembly Facility in New Orleans). Orion's arrival at KSC marks a major milestone on the road to starting NASA's ‘Journey to Mars' initiative. 53)
- This Lunar Orion vehicle is destined for blastoff to the Moon in 2018 on NASA's EM-1 (Exploration Mission-1) atop the agency's mammoth SLS (Space Launch System) rocket. EM-1 is a ‘proving ground' mission that will fly an unmanned Orion thousands of kilometers beyond the Moon, further than any human capable vehicle, and back to Earth, over the course of a three-week mission.
Figure 43: The nose of the Super Guppy aircraft opened to reveal cargo hold carrying the Orion crew module pressure vessel after arrival at KSC (image credit: Ken Kremer)
• January 22, 2016: The first European hardware to arrive at NASA for Orion is the European Service Module structural test article (Figure 44). This test version of the service module has the same weight and configuration as the real thing and will undergo advanced testing at NASA's Plum Brook Station in Ohio, USA. Once mating is complete the Service Module will have a mass of 13,000 kg in total. The Service Module will be placed on a shaker and vibrated to recreate the stress of launch. 54)
Figure 44: In this picture, the European Service Module structural test article is being ‘mated' to the Crew Module Adapter, which connects the service module to the Orion Crew Module (image credit: ESA, NASA)
• January 2016: In a major step towards flight, engineers at NASA's Michoud Assembly Facility in New Orleans have finished welding together the pressure vessel for the first Lunar Orion crew module that will blastoff in 2018 atop the agency's SLS (Space Launch System) rocket. The 2018 launch of NASA's Orion on an unpiloted flight dubbed Exploration Mission, or EM-1, counts as the first joint flight of SLS and Orion, and the first flight of a human rated spacecraft to deep space since the Apollo Moon landing era ended more than 4 decades ago. 55)
- The friction-stir welding work to assemble the primary structure of NASA's maiden Lunar Orion capsule was just finished last week on Jan. 13. According to NASA, friction-stir welding produces incredibly strong bonds by transforming metals from a solid into a plastic-like state, and then using a rotating pin tool to soften, stir and forge a bond between two metal components to form a uniform welded joint, a vital requirement of next-generation space hardware.
Figure 45: Orion EM-1 pressure vessel was completed Jan. 13, 2016 at NASA's Michoud Assembly Facility in New Orleans, LA. The pressure vessel is the spacecraft's underlying structure on which all of the spacecraft's systems and subsystems are built and integrated (image credit: NASA)
• Nov. 16, 2015: After the completion of Orion's CDR (Critical Design Review) in October, the spacecraft is one important step closer toward the upcoming EM-1 (Exploration Mission-1, scheduled to take place in 2018. It means that Lockheed Martin, the prime contractor building Orion, can now focus on full-scale fabrication, assembly, integration and tests of the spacecraft. 56)
• Nov. 10, 2015: A test version of ESA's service module for NASA's Orion spacecraft arrived at the Cleveland Hopkins airport in Ohio, USA before continuing by road to NASA's Plum Brook Station. 57) 58) 59)
- The module sits directly below Orion's crew capsule and provides propulsion, power, thermal control, and water and air for four astronauts. The solar array spans 19 m and provides enough to power two households. A little over 5 m in diameter and 4 m high, it weighs 13.5 tons. The 8.6 tons of propellant will power one main engine and 32 smaller thrusters.
- Following initial tests in Europe, it will now undergo rigorous vibration tests in NASA's Plum Brook Station in Ohio to ensure the structure and components can withstand the extreme stresses during launch.
• Nov. 6, 2015: Airbus Defence and Space is preparing to deliver the Orion ESM (European Service Module) structural test model to NASA. The model is an exact copy of the flight model, only without the functionality. It will determine whether the structural and weight specifications have been met, and whether the module lives up to NASA's crew safety requirements. Testing will take place at NASA's Plum Brook Station test center in Ohio, USA. 60)
- The design of the ESM is based on the ATV (Automated Transfer Vehicle), the European supply craft for the International Space Station. It is a cylindrical module with a diameter of 4.5 m and a total length – main engine excluded – of 2.7 m. It is fitted with four solar array ‘wings' with a span of 18.8 m. Besides propulsion and power, the ESM is also equipped with oxygen tanks to supply the crew.
Figure 46: A look at the propulsion side of the Orion ESM (European Service Module) structural test model (image credit: Airbus Defence and Space SAS 2015)
• Oct. 26, 2015: Lockheed Martin and NASA have completed the majority of Orion's CDR (Critical Design Review) which means the spacecraft's design is mature enough to move into full-scale fabrication, assembly, integration and test of the vehicle. It also means that the program is on track to complete the spacecraft's development to meet NASA's Exploration Mission-1 (EM-1) performance requirements. The complete Orion EM-1 CDR process will conclude after the European Service Module CDR and a presentation to the NASA Agency Program Management Council in the spring 2016. 61) 62)
- Orion's CDR kicked off in August 2015. The review focused on the EM-1 design as well as additional common elements that will be included on the Exploration Mission-2 (EM-2) spacecraft. These elements include the structure, pyrotechnics, LAS (Launch Abort System), software, guidance, navigation and control, and many others.
- Although the EM-1 vehicle is designed to accommodate all the necessary elements for human exploration of deep space, systems unique to the EM-2 mission, such as crew displays and the Environmental Control and Life Support System, will be evaluated at a later EM-2 CDR.
- In early 2016, Orion's crew module pressure vessel will be shipped to the Operations and Checkout Facility at NASA's Kennedy Space Center. There it will undergo final assembly, integration and testing in order to prepare for EM-1 when Orion is launched atop NASA's SLS (Space Launch System) for the first time.
• Oct. 22, 2015: NASA completes the CDR (Critical design Review) for SLS (Space Launch System). The CDR examined the first of three configurations planned for the rocket, referred to as SLS Block 1. The Block I configuration will have a minimum 70-metric-ton (77-ton) lift capability and be powered by twin boosters and four RS-25 engines. The next planned upgrade of SLS, Block 1B, would use a more powerful exploration upper stage for more ambitious missions with a 105-metric-ton (115-ton) lift capacity. Block 2 will add a pair of advanced solid or liquid propellant boosters to provide a 130-metric-ton (143-ton) lift capacity. In each configuration, SLS will continue to use the same core stage and four RS-25 engines. 63)
• Oct. 12, 2015: Aerojet Rocketdyne announced that it passed the CDR (Critical Design Review) for the jettison motor and the crew module RCS (Reaction Control System) on the Orion spacecraft. These two major subsystems that Aerojet Rocketdyne is building for Lockheed Martin and NASA are critical for ensuring astronaut safety and mission success. Astronaut safety is paramount and the jettison motor and the crew module reaction control system will ensure that the crew begins their mission into deep space and lands at the completion without harm. 64)
- The jettison motor is a solid rocket motor that separates the launch abort system from the Orion spacecraft about five seconds after fairing separation, allowing the crew to continue safely on their way into deep space. In addition to its normal operations, the jettison motor serves a double duty if an anomaly occurs. Designed to assist crew escape, the jettison motor is one of three solid rocket motors on the launch abort system that will rapidly pull the capsule away from the stack in the event of an emergency.
- The RCS on the crew module the company is providing for Orion is equally important to crew safety. The crew module RCS provides the only course control authority after separation from the service module. It ensures that the heat shield is properly oriented, the crew module is stable under the parachutes and that the vehicle is in the correct orientation for splashdown.
• NASA is a small step closer to sending astronauts on a journey to Mars. On Sept. 5, 2015, engineers at the agency's MAF (Michoud Assembly Facility) in New Orleans welded together the first two segments of the Orion crew module that will fly atop NASA's SLS (Space Launch System) rocket on a mission beyond the far side of the moon. 65)
Figure 47: At NASA's MAF in New Orleans, engineers welded together on Sept. 5, 2015 two sections of the Orion spacecraft's primary structure that will fly on Exploration Mission-1, the first flight of Orion atop the agency's Space Launch System rocket (image credit: NASA)
The primary structure of Orion's crew module is made of seven large aluminum pieces that must be welded together in detailed fashion (Figure 48). The first weld connects the tunnel to the forward bulkhead, which is at the top of the spacecraft and houses many of Orion's critical systems, such as the parachutes that deploy during reentry. Orion's tunnel, with a docking hatch, will allow crews to move between the crew module and other spacecraft.
"Each of Orion's systems and subsystems is assembled or integrated onto the primary structure, so starting to weld the underlying elements together is a critical first manufacturing step," said Mark Geyer, Orion Program manager. "The team has done tremendous work to get to this point and to ensure we have a sound building block for the rest of Orion's systems."
Engineers have undertaken a meticulous process to prepare for welding. They have cleaned the segments, coated them with a protective chemical and primed them. They then outfitted each element with strain gages and wiring to monitor the metal during the fabrication process. Prior to beginning work on the pieces destined for space, technicians practiced their process, refined their techniques and ensured proper tooling configurations by welding together a pathfinder, a full-scale version of the current spacecraft design.
NASA's prime contractor for the spacecraft, Lockheed Martin, is doing the production of the crew module at Michoud.
Through collaborations across design and manufacturing, the teams have been able to reduce the number of welds for the crew module by more than half since the first test version of Orion's primary structure was constructed and flown on the EFT-1 (Exploration Flight Test-1) in December 2014. The EM-1 (Exploration Mission-1) structure will include just seven main welds, plus several smaller welds for start and stop holes left by welding tools. Fewer welds will result in a lighter spacecraft.
Figure 48: Seven welds of Orion's pressure vessel. This diagram shows the seven pieces of Orion's primary structure and the order in which they are welded together (image credit: NASA)
The tunnel is the passageway astronauts crawl in and out of when Orion is docked with another vehicle. The forward bulkhead, located at the top of the crew module, must handle extreme loads during re-entry because that is where the parachutes are connected when they deploy. In order to certify the new welding process, the team at Michoud Assembly Facility welded a pathfinder vehicle to verify the design changes and welding changes would perform as expected. 66)
In early 2016, once the pieces that make up the crew module's pressure vessel are welded together, it will be shipped to the Operations and Checkout Facility at NASA's Kennedy Space Center. There it will undergo final assembly, integration and testing in order to prepare for Exploration Mission-1 when Orion is launched atop NASA's SLS (Space Launch System) for the first time. The test flight will send Orion into lunar distant retrograde orbit—a wide orbit around the moon that is farther from Earth than any human-rated spacecraft has ever traveled. The mission will last more than 20 days and will certify the design and safety of Orion and SLS for human-rated exploration missions.
Launch: Orion EM-1 will launch uncrewed on the maiden test flight of NASA's SLS (Space Launch System). Liftoff is expected in mid-2020.The SLS-1/EM-1 test flight with the uncrewed Orion spacecraft will launch from Launch Complex 39-B at the Kennedy Space Center, Cape Canaveral, FL. 67) 68) 69)
The EM-1 mission will last more than three weeks, sending the Orion spacecraft into a high-altitude retrograde orbit around the moon before heading back to Earth for a splashdown in the Pacific Ocean.
• March 8, 2018: Exploration Mission-1 (EM-1) will be the first integrated test of NASA's deep space exploration systems: the Orion spacecraft, Space Launch System (SLS) rocket and the ground systems at Kennedy Space Center in Cape Canaveral, Florida. The first in a series of increasingly complex missions, EM-1 will be an uncrewed flight test that will provide a foundation for human deep space exploration, and demonstrate our commitment and capability to extend human existence to the Moon and beyond. 70)
- During this flight, the spacecraft will launch on the most powerful rocket in the world and fly farther than any spacecraft built for humans has ever flown. It will travel 280,000 miles from Earth, thousands of miles beyond the Moon over the course of about a three-week mission. Orion will stay in space longer than any ship for astronauts has done without docking to a space station and return home faster and hotter than ever before.
- "This is a mission that truly will do what hasn't been done and learn what isn't known," said Mike Sarafin, EM-1 mission manager at NASA Headquarters in Washington. "It will blaze a trail that people will follow on the next Orion flight, pushing the edges of the envelope to prepare for that mission."
- Leaving Earth: SLS and Orion will blast off from Launch Complex 39B at NASA's modernized spaceport at Kennedy Space Center in Florida. The SLS rocket is designed for missions beyond low-Earth orbit carrying crew or cargo to the Moon and beyond, and will produce 8.8 million pounds of thrust during liftoff and ascent to loft a vehicle weighing nearly six million pounds to orbit. Propelled by a pair of five segment boosters and four RS-25 engines, the rocket will reach the period of greatest atmospheric force within ninety seconds. After jettisoning the boosters, service module panels, and launch abort system, the core stage engines will shut down and the core stage will separate from the spacecraft.
- As the spacecraft makes an orbit of Earth, it will deploy its solar arrays and the ICPS (Interim Cryogenic Propulsion Stage) will give Orion the big push needed to leave Earth's orbit and travel toward the Moon. From there, Orion will separate from the ICPS within about two hours after launch. The ICPS will then deploy a number of small satellites, known as CubeSats, to perform several experiments and technology demonstrations.
- On to the Moon: As Orion continues on its path from Earth orbit to the Moon, it will be propelled by a service module provided by the European Space Agency, which will supply the spacecraft's main propulsion system and power (as well as house air and water for astronauts on future missions). Orion will pass through the Van Allen radiation belts, fly past the Global Positioning System (GPS) satellite constellation and above communication satellites in Earth orbit. To talk with mission control in Houston, Orion will switch from NASA's Tracking and Data Relay Satellites system and communicate through the Deep Space Network. From here, Orion will continue to demonstrate its unique design to navigate, communicate, and operate in a deep space environment.
- The outbound trip to the Moon will take several days, during which time engineers will evaluate the spacecraft's systems and, as needed, correct its trajectory. Orion will fly about 62 miles (100 km) above the surface of the Moon, and then use the Moon's gravitational force to propel Orion into a new deep retrograde, or opposite, orbit about 70,000 km from the Moon.
- The spacecraft will stay in that orbit for approximately six days to collect data and allow mission controllers to assess the performance of the spacecraft. During this period, Orion will travel in a direction around the Moon retrograde from the direction the Moon travels around Earth.
- Return and Reentry: For its return trip to Earth, Orion will do another close flyby that takes the spacecraft within about 60 miles of the Moon's surface, the spacecraft will use another precisely timed engine firing of the European-provided service module in conjunction with the Moon's gravity to accelerate back toward Earth. This maneuver will set the spacecraft on its trajectory back toward Earth to enter our planet's atmosphere traveling at 25,000 mph (11 kilometers per second), producing temperatures of approximately 5,000 degrees Fahrenheit (2,760 degrees Celsius) – faster and hotter than Orion experienced during its 2014 flight test.
- After about three weeks and a total distance traveled exceeding 1.3 million miles, the mission will end with a test of Orion's capability to return safely to the Earth as the spacecraft makes a precision landing within eyesight of the recovery ship off the coast of Baja, California. Following splashdown, Orion will remain powered for a period of time as divers from the U.S. Navy and operations teams from NASA's Exploration Ground Systems approach in small boats from the waiting recovery ship. The divers will briefly inspect the spacecraft for hazards and hook up tending and tow lines, and then engineers will tow the capsule into the well-deck of the recovery ship to bring the spacecraft home.
- Future Missions: With this first exploration mission, NASA is leading the next steps of human exploration into deep space where astronauts will build and begin testing the systems near the Moon needed for lunar surface missions and exploration to other destinations farther from Earth, including Mars. The SLS rocket will evolve from an initial configuration capable of sending more than 26 metric tons to the Moon, to a final configuration that can send at least 45 metric tons. The second flight will take crew on a different trajectory using a powerful exploration upper stage and test Orion's critical systems with humans aboard. Together, Orion, SLS and the ground systems at Kennedy will be able to meet the most challenging crew and cargo mission needs in deep space.
- Future exploration missions with crew aboard Orion will dock with a Lunar Orbital Platform-Gateway. NASA and its partners will use the gateway for deep-space operations including missions to and on the Moon with decreasing reliance on the Earth. Using lunar orbit, we will gain the experience necessary to extend human exploration farther into the solar system than ever before.
Figure 49: The Orion EM-1 mission map (image credit: NASA) 71)
Figure 50: ORION - NASA's Deep Space Exploration Spacecraft - Explained in Detail (video credit: NASA)
Radiation Payload of Orion EM-1
MARE (Matroshka AstroRad Radiation Experiment)
Future long duration Exploration missions require renewed efforts to adequately mitigate risks of crew health effects due to radiation exposure. Orion is NASA's next generation human Exploration spacecraft. Radiation protection constitutes a design driver for Orion. During the spacecraft development process, Lockheed Martin has proactively pursued radiation protection approaches in compliance with the ALARA (As low as reasonably achievable) principle. A collaborative effort with StemRad Ltd, Tel Aviv, Israel, resulted in the development of personal protective equipment for astronauts, the AstroRad. AstroRad provides customizable protection focused on stem cell rich organs and tissues. Orion's first test flight beyond Earth orbit (BEO) is Exploration Mission 1 (EM-1). 72)
MARE, an EM-1 international radiation science payload, has been proposed by the German Aerospace Center (DLR) and the Israel Space Agency (ISA) as an Orion science payload, approved by NASA, and in May 2017 was manifested on the EM-1 flight. In the past year, significant progress towards AstroRad customization, active detector development, and integration for MARE has been accomplished. The experiment is scheduled to be sent to the Moon and back on the Orion spacecraft in 2020 in collaboration with NASA. This innovative mission aims to collect data on the deep space radiation to which the human body is exposed during a voyage to the Moon, and at the same time test a radiation protection vest. 73) 74)
The spacecraft will carry two DLR measurement bodies, called the Matroshka Phantoms (test dummies). They are identical and are both fitted with more than 1400 active and passive sensors spread across their exterior and interior to acquire data on the effects of cosmic radiation on the bodies' interior and organs. During the flight, one of the phantoms will wear the AstroRad protective vest by StemRad, the industry partner from Israel. The other model will be exposed to the radiation without any protection whatsoever. 75)
The measurement bodies will be fitted with sensors and prepared for the space voyage at the DLR Institute of Aerospace Medicine in Cologne, where the data collected during the flight will be compared and evaluated on behalf of all partners and co-investigators. A number of DLR Matroshka phantoms have already travelled to space, but exclusively to the International Space Station ISS – so only in a near-Earth orbit. The MARE project will mark the first time that scientists collect data on radiation exposure beyond ISS orbit.
• To perform radiation measurements that help refine risk projections
- Skin- and internal body organs dosimetry
- During Van Allen belt transit & in cis-lunar space
- Intravehicular environment specific to Orion
• To validate the protection provided by AstroRad
• To expand the ISS Matroshka international participation heritage
• Trailblazer for science payloads on Orion
MARE Ground Rules:
• Phantoms will be installed inside the cabin at seat positions 3 and 4
- Phantom w/ AstroRad at position 3
- Representative of the nominal crew radiation environment on upcoming missions
• Payload is fully self-contained - no power and data interfaces from Orion
- Passive dosimeters: TLDs (Thermoluminescent Dosimeters), OSLDs (Optically Stimulated Luminescence Dosimeters), CR-39 PNTDs (Plastic-Nuclear Track Detectors)
- Battery powered active detectors with integrated data processing and recording
• Payload installation at L-15 days, post-flight removal at S+15 days (KSC)
• Payload must satisfy all vehicle safety requirements
• Mass and volume allocation.
CIRS (Computerized Imaging Reference Systems, Inc.) Radiation Phantom
• Made of tissue-equivalent material & containing human skeleton 76)
- Female Model
- 38 slices: 95 cm, 35 kg
- TLD holes in 3 cm grid over the phantom.
Figure 51: MARE configuration as baselined for Orion consists of two radiotherapy phantoms located at seat positions 3 and 4 in the spacecraft. The phantom at position 4 is fitted with the AstroRad astronaut radiation shield (image credit: MARE collaboration)
AstroRad Radiation Vest
• Developed by international collaboration between StemRad Ltd and Lockheed Martin SSC Advanced Programs
- Grant funding by MATIMOP and Space Florida
• Astronaut individually customizable personal protective equipment
- Designed using StemRad proprietary algorithms for selective shielding optimization focused on stem cell rich organs and tissues
- The manufacturing process leverages StemRad ground radiation protection expertise
Figure 52: Illustration of the AstroRad astronaut radiation shield on a female person (image credit: MARE collaboration)
BRIC (Biological Research in Canisters)
NASA's Space Biology Program selected four space biology investigations that will look at the nutritional value of seeds, DNA repair of fungi, adaptation of yeast, and gene expression of algae to help researchers better understand how biological systems are affected by a deep space environment in preparation for human missions to the Moon, and eventually Mars. The common theme to these investigations is to study DNA damage and protection from radiation, for Moon missions, where radiation exposure will be roughly twice what it is on the International Space Station. 77)
Researchers will use this uncrewed flight test as an opportunity to study effects from the combined environment of space radiation and microgravity. Beyond low-Earth orbit, cosmic radiation is trapped in the Van Allen Belts that are part of Earth's magnetosphere and can be dangerous to humans and other living organisms, as well as sensitive electronics. The Moon is about 250,000 miles from the Earth, which is about 1,000 times more than the distance from Earth to the International Space Station, and offers a true deep space radiation environment outside the Van Allen Belts.
The experiments will be carried in a container stored in the crew compartment of the Orion capsule for the duration of the mission as it passes through the Van Allen Belts on the way out to the Moon and again on the way back to Earth. All specimens will be returned to the researchers for post-flight analyses after the spacecraft splashes down in the Pacific Ocean.
Figure 53: The BRIC system will be used by the selected proposals. This image shows a BRIC-100VC with petri dish rack insert (left) and conical tube configuration (right), image credit: NASA
NASA selected investigators from four institutions. When fully implemented, the awards will total ~$1.6 million in fiscal years 2019-2022. The awardees are as follows:
• Federica Brandizzi, Ph.D., Michigan State University: Life beyond Earth: Effect of space flight on seeds with improved nutritional value. This study will characterize how spaceflight effects nutrient stores in plants seeds with the goal of gaining new knowledge that will help increase the nutritional value of plants grown in spaceflight.
• Timothy Hammond, Ph.D., Institute For Medical Research, Inc. Fuel to Mars. This research will include studies with the photosynthetic algae, Chlamydomonas reinhardtii, to identify important genes that contribute to its survival in deep space.
• Zheng Wang, Ph.D., Naval Research Laboratory , Investigating the Roles of Melanin and DNA Repair on Adaptation and Survivability of Fungi in Deep Space. Researchers will be using the fungus Aspergillus nidulans to investigate radioprotective effects of melanin and the DNA damage response."
• Luis Zea, Ph.D., University of Colorado, Boulder: Multi-Generational Genome-Wide Yeast Fitness Profiling Beyond and Below Earth's van Allen Belts. This investigation will use yeast as a model organism to identify genes that help organisms adapt to the conditions of both deep spaceflight on the EM-1 mission, and of Low Earth Orbit on the ISS.
NASA awarded these grants under the NASA Research Announcement NNH18ZTT001N-EM1 "Appendix A: Orion Exploration Mission-1 Research Pathfinder for Beyond Low Earth Orbit Space Biology Investigations" which is part of the Research Opportunities in Space Biology (ROSBio) Omnibus. The Space Biology Program is managed by the Space Life and Physical Sciences Research and Applications Division in NASA's Human Exploration and Operations Mission Directorate at the agency's headquarters in Washington, D.C.
Payload Accommodations on EM-1:
Secondary payloads on EM-1 will be launched in the OSA (Orion Stage Adapter). Payload dispensers will be mounted on specially designed brackets, each attached to the interior wall of the OSA as shown in Figure 54. For the EM-1 mission, a total of fourteen brackets will be installed, allowing for thirteen payload locations. The final location will be used for mounting an avionics unit, which will include a battery and sequencer for executing the mission deployment sequence. 78)
Figure 54: The Orion Stage Adapter with payload locations (image credit: NASA)
Each bracket is designed to hold the volume equivalent of 6U and 12U dispensers. The current design baseline for the EM-1mission is for payloads to be compatible with 6U class dispensers. Payloads in 6U class will be limited to 14 kg maximum mass. Detailed physical accommodations are documented in Table 6 and Figure 55.
The avionics unit will interface with each deployer through cables mounted in the OSA. Payloads will remain powered off until the sequencer transmits the deployment signal to each dispenser, and the payload is released. Payloads will exit the dispenser at an approximate rate of 1.2 m/s, with deployments separated by a minimum of 5 seconds. No other payload services are currently planned for EM-1.
Table 6: Payload maximum dimensions
Figure 55: Payload volume dimension (image credit: NASA)
GSDO (Ground Systems Development and Operations) : The GSDO program at the KSC (Kennedy Space Center) will perform SLS ground processing. Payloads will be fully integrated into their dispenser at the time of delivery to GSDO. Once delivered, integrated payloads will be installed into the OSA, prior to stacking operations with the Orion system. Prior to roll-out to the pad, battery charging for the avionics unit and each payload containing approved batteries will occur at the VAB (Vehicle Assembly Building).
Operations: Secondary payloads on SLS will remain powered off during the ascent phase of the launch vehicle, through separation of the Orion spacecraft. Once separation is confirmed, the ICPS will send a discrete signal to the SPDS avionics to activate. The schedule for deployments will be loaded as a skit prior to vehicle stacking. No real-time commanding or telemetry is available; therefore payloads will be deployed automatically through the pre-determined mission timeline sequence.
Payloads will have opportunity to deploy beginning after the ICPS disposal sequence is complete (approximately T+4 hours) up to 10 days from launch. All deployments will be completed before avionics batteries are expended. Figure 56 provides an overview of the mission profile.
Once deployed, payloads will be required to wait 15 seconds before deploying antennas, solar panels, sails, etc. to ensure adequate clearance from ICPS. Payload communications following deployment will be the responsibility of the payload project, with no resources being provided by SLS.
Figure 56: EM-1 mission profile (NASA)
Secondary payloads of Orion/EM-1
The first flight of NASA's new rocket, SLS ( Space Launch System), will carry 13 CubeSats/Nanosatellites to test innovative ideas along with an uncrewed Orion spacecraft in 2019. These small satellite secondary payloads will carry science and technology investigations to help pave the way for future human exploration in deep space, including the journey to Mars. SLS' first flight, referred to as EM-1 (Exploration Mission-1 ), provides the rare opportunity for these small experiments to reach deep space destinations, as most launch opportunities for CubeSats are limited to low-Earth orbit. 79) 80)
The secondary payloads, 13 CubeSats, were selected through a series of announcements of flight opportunities, a NASA challenge and negotiations with NASA's international partners.
All the CubeSats will ride to space inside the OSA (Orion Stage Adapter), which sits between the ICPS (Interim Cryogenic Propulsion Stage) and Orion (Figure 58). The CubeSats will be deployed following Orion separation from the upper stage and once Orion is a safe distance away.
The SPIE ( Spacecraft and Payload Integration and Evolution) office is located at NASA/MSFC (Marshall Space Flight Center) in Huntsville, Alabama, which handles integration of the secondary payloads.
These small satellites are designed to be efficient and versatile—at no heavier than 14 kg, they are each about the size of a boot box, and do not require any extra power from the rocket to function. The science and technology experiments enabled by these small satellites may enhance our understanding of the deep space environment, expand our knowledge of the moon, and demonstrate technology that could open up possibilities for future missions. 83)
A key requirement imposed on the EM-1 secondary payload developers is that the smallsats do not interfere with Orion, SLS or the primary mission objectives. To meet this requirement, payload developers must take part in a series of safety reviews with the SLS Program's Spacecraft Payload Integration & Evolution (SPIE) organization, which is responsible for the Block 1 upper stage, adapters and payload integration. In addition to working with payload developers to ensure mission safety, the SLS Program also provides a secondary payload deployment system in the OSA (Orion Space Adapter). The deployment window for the CubeSats will be from the time ICPS disposal maneuver is complete (currently estimated to require about four hours post-launch) to up to 10 days after launch. 84)
Deployment windows of secondary payloads: The smallsats manifested on EM-1 will undertake a diverse variety of experiments and technology demonstrations. Seven payloads will be deployed after the ICPS has cleared the first Van Allen Radiation Belt (bus stop 1, Figure 57).
• JAXA, the Japanese Space Agency, will have two smallsats deploy at the first stop: OMOTENASHI will land the smallest lander to date on the lunar surface to demonstrate the feasibility of the hardware for distributed cooperative exploration systems. If this mission is successful, Japan will be the fourth nation to successfully land a mission on the Earth's moon. The other JAXA payload, EQUULEUS, will fly to a libration orbit around the EML2 (Earth-Moon L2) point and demonstrate trajectory control techniques within the sun-Earth-moon region for the first time by a smallsat.
• Lunar Flashlight is a NASA/JPL ( Jet Propulsion Laboratory) mission that will look for ice deposits and identify locations where resources may be extracted from the lunar surface.
Figure 57: Providing smallsats with extraordinary access to deep space, SLS presented payload developers with several "bus stops," or deployment opportunities, for the first mission; similar opportunities are expected to be available on future missions (image credit: NASA)
• The NASA/ARC ( Ames Research Center) developed the BioSentinel mission is a yeast radiation biosensor that will measure effects of space radiation on DNA.
• ArgoMoon, sponsored by the Agenzia Spaziale Italiana (ASI), will perform proximity operations with the ICPS post-disposal and record imagery of engineering and historical significance — as well as of the Earth and moon — by testing an advanced software imaging recognition system using high-definition cameras.
• Cislunar Explorers, a team from Cornell University in Ithaca, New York, competing in NASA's Cube Quest Centennial Challenge competition, has designed a 6U CubeSat that will split into two smaller spacecraft that will orbit the moon using a novel propulsion system of inert water to carry out gravity assists with the moon, and then be captured into lunar orbit.
• Finally, Lunar Icecube, developed by Morehead State University in Kentucky, will search for water in ice, liquid and vapor forms as well as other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact infrared spectrometer.
• About 90 minutes after the ICPS clears the first Van Allen Belt, the NEA Scout (Near Earth Asteroid) Scout, a NASA/MSFC (Marshall Space Flight Center) mission equipped with a solar sail to rendezvous with an asteroid, will be deployed. NEA Scout will gather detailed imagery and observe the asteroid's position in space.
• After the ICPS has cleared both radiation belts, the LunaH-Map (Lunar-Polar Hydrogen Mapper) payload from Arizona State University will be released. LunaH-Map will help scientists understand the quantity of hydrogen-bearing materials in cold traps in permanently shaded lunar craters via low-altitude flybys of the moon's south pole.
• About one hour after clearing the radiation belts (bus stop 2, Figure 57), Lockheed Martin's LunIR spacecraft, a technology demonstration mission that will perform a lunar flyby, will be deployed. Using a miniature high-temperature MWIR (Mid-Wave Infrared) sensor to collect spectroscopy and thermography data, LunIR will provide data related to surface characterization, remote sensing and site selection for lunar future missions.
About 12 hours after the ICPS passes the moon (bus stop 5, Figure 57) and uses its gravity to enter heliocentric orbit, the final three smallsats will be released.
• The CuSP (CubeSat Mission to Study Solar Particles) mission of SwRI (Southwest Research Institute) in San Antonio, Texas, will study the sources and acceleration mechanisms of solar and interplanetary particles in near-Earth orbit, support space weather research by determining proton radiation levels during ESP (Solar Energetic Particle) events and identifying suprathermal properties that could help predict geomagnetic storms.
• Team Miles, of Miles Space, LLC, of Tampa, Florida, another Cube Quest competitor, has a mission that will fly autonomously using a sophisticated onboard computer system. The spacecraft will be propelled by evolutionary plasma thrusters.
• The final Cube Quest entrant, the University of Colorado CU-E3 (Earth Escape Explorer), is a CubeSat from the University of Colorado in Boulder, Colorado, that will use solar radiation pressure rather than an onboard propulsion system.
Block 1 SmallSat Accommodations:
To release the payloads, the SLS Program installed a secondary payload deployment system in the OSA (Orion Space Adapter) that includes mounting brackets for the COTS (Commercial Off-The-Shelf) dispensers, cable harnesses and an avionics unit. Prior to shipping the completed OSA to the EGS (Exploration Ground Systems) Program at Kennedy, engineers at Marshall Space Flight Center tested the avionics unit to ensure possible scripts for controlling bus stop deployments performed as expected based on the flight time to the moon. For EM-1, each payload developer is responsible for the payload, the specified dispenser, vibration isolation system and thermal protection (Ref. 84).
Before the OSA is stacked on the ICPS in Kennedy's Vehicle Assembly Building, the EGS Program will install the payloads previously integrated in their COTS dispensers onto the brackets. Then the payloads and the deployment avionics unit's batteries will be charged. EGS technicians will connect the electrical ground support equipment to the secondary payload deployment system via the OSA. The electrical ground support equipment will be removed and no further interaction with the payloads will be performed. On launch day, ICPS contractor ULA (United Launch Alliance) will load the upper stage operational parameters for the flight, including data needed for the secondary payload deployment system avionics unit to perform the correct skit for the mission based on trip time to the moon and when the payloads need to be deployed to complete their missions.
After the TLI (Translunar Injection) burn and separation of Orion from the ICPS/OSA, and conclusion of most of the ICPS disposal maneuvers, the ICPS will power on the secondary payload deployment system. The ICPS will put itself into a 1 rpm roll and be pointed at a 55º beta angle to the sun and proceed with hydrazine depletion as part of stage disposal. Once the propellant is spent, the ICPS will take one more set of readings, downlink those readings and shut down. Soon after, the ICPS/OSA and secondary payload deployment system arrive at the first bus stop where seven payloads will be released into deep space.
Another noteworthy benefit SLS provides to the EM-1 smallsats is the ability to incorporate propulsion systems on the payloads. In most smallsat missions to LEO, CubeSats are restricted from having propulsion systems. Smallsats operating in deep space, on the other hand, require propulsion systems in many mission scenarios. The EM-1 CubeSats employ several types of propulsion systems, including ion, solid, green propellant, solar, pressure, etc., providing mission developers with the rare opportunity to utilize these small propulsion systems in deep space.
A prime example of both extraordinary deep space exploration opportunities and cooperation among numerous organizations, the 13 EM-1 6U-class payloads present the opportunity for science and technology advancement on what is otherwise a demonstration flight, paving the way for additional opportunities for CubeSats on future SLS missions.
Figure 58: At the top of the Block 1 configuration, the OSA (Orion Stage Adapter) has capacity for 13-17 smallsats; the SLS Program provides an integrated deployment system for the payloads (image credit: NASA)
Figure 59: Secondary payloads infographic (image credit: NASA) 85)
The secondary payloads will be described in separate files on the eoPortal — if sufficient technical information is available of each secondary mission.
Interplanetary CubeSats take advantage of the CubeSat paradigm and of the availability of commercial components developed for LEO (Low Earth Orbit) missions, but they are specifically designed to explore deep space. As a result, interplanetary CubeSats are essentially very different from LEO CubeSats in at least three technological areas: propulsion, radiation tolerance and telecommunication. 86)
In particular, interplanetary CubeSats require changes in almost every subsystem. To start, they generally need a propulsion system. In addition, they often need power systems with lower power modes and higher energy storage capabilities since they have more power requirements than LEO missions, due to the presence of propulsion and due to demanding telecommunication systems. Interplanetary CubeSats also require radiation tolerant components as they are significantly far from the protection of the Earth magnetosphere which is instead granted to the LEO CubeSat missions. For what concerns ADCS (Attitude Determination and Control Subsystem ), interplanetary CubeSats need a combination of traditional control system and propulsion to avoid the issues of wheel`s saturation outside the Earth`s geomagnetic field. In terms of autonomy, interplanetary missions will have less frequent contact with the ground than LEO missions and they will need agile algorithms to facilitate autonomous on board operations.
Finally, one of the most important changes between LEO missions and interplanetary missions is represented by the telecommunication systems. Telecommunication systems for interplanetary CubeSats face harsher environments, longer path distances and have more navigation needs than the LEO CubeSats. For this reason, the design of telecommunication systems for interplanetary missions is extremely challenging and significant development is currently ongoing in the areas of radio design, antenna design and in the design of ground support architectures.
Telecommunication systems for Lunar IceCube and LunaH-Map.
An effort is underway at JPL to develop a common set of telecommunication hardware systems to fit the envelope of these missions' goals. As a result, the two missions share the same radio (Iris transponder), the same low noise amplifiers, the same low gain patch antennas, and they are equipped with very similar SSPAs (Solid State Power Amplifiers) that differ only in the power levels that they provide. Additionally, Lunar IceCube and LunaH-Map will share the use of the DSN (Deep Space Network) antennas and of the Morehead State University 21 m station, which is currently being upgraded especially for this purpose.
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The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (firstname.lastname@example.org).