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ExoMars (Exobiology on Mars)

Spacecraft     Launch    Mission Status     Sensor Complement    Arriving At Mars    References

Background: Establishing whether life ever existed, or is still active on Mars today, is one of the outstanding scientific questions of our time. The ExoMars Program seeks to timely address this and other important scientific goals, and to demonstrate key flight and in situ enabling technologies underpinning European and Russian ambitions for future exploration missions. The ExoMars Program is a cooperative undertaking between ESA (European Space Agency) and the Russian federal space agency, Roscosmos. 1)

Within ESA, ExoMars is an element of the Aurora Exploration Program, an optional program executed under the supervision of the Program Board for Human Spaceflight, Microgravity and Exploration (PBHME). However, the ESA Science Program also participates to ExoMars. The objective of the Aurora Program is to explore Solar System objects having a high potential for the emergence of life. Aurora aims to develop technologies and address scientific questions in a step-wise fashion, seeking to advance the level of technical and scientific readiness with each successive mission.

Within Roscosmos, ExoMars is part of the Russian federal space program and is supported by RAS (Russian Academy of Sciences).

To prepare for future exploration missions and to support the Program's scientific objectives, ExoMars will achieve the following technology objectives:

• EDL (Entry, Descent, and Landing) of a payload on the surface of Mars

• Surface mobility with a Rover

• Access to the subsurface to acquire samples

• Sample acquisition, preparation, distribution, and analysis.

In addition to these technology objectives already agreed in the Aurora Declaration, the following new technology objectives result from the cooperation with Roscosmos:

• Qualification of Russian ground-based means for deep-space communications in cooperation with ESA's ESTRACK

• Adaptation of Russian on-board computer for deep space missions and ExoMars landed operations

• Development and qualification of throttleable braking engines for prospective planetary landing missions.

The scientific objectives of ExoMars are:

• To search for signs of past and present life on Mars

• To investigate the water/geochemical environment as a function of depth in the shallow subsurface

• To study martian atmospheric trace gases and their sources.

In addition to these science objectives already agreed in the Aurora Declaration, the following new scientific objective results from the cooperation with Roscosmos:

• To characterise the surface environment.

The ExoMars Program consists of two missions, in 2016 and 2018. ESA and Roscosmos have agreed a well-balanced sharing of responsibilities for the various mission elements. 2)

The second ExoMars mission involves a Russian-led surface platform and a European-led rover, also to be launched on a Proton from Baikonur. Russian and European experts made their best efforts to meet the 2018 launch schedule for the mission, and in late 2015, a dedicated ESA-Roscosmos Tiger Team, also including Russian and European industries, initiated an analysis of all possible solutions to recover schedule delays and accommodate schedule contingencies.

The Tiger Team presented its final report during a meeting of the Joint ExoMars Steering Board (JESB) held in Moscow. Having assessed the possible ways to ensure successful mission implementation, the JESB concluded that, taking into account the delays in European and Russian industrial activities and deliveries of the scientific payload, a launch in 2020 would be the best solution.

ESA Director General Johann-Dietrich Woerner and Roscosmos Director General Igor Komarov discussed the ExoMars 2018 situation. After considering the Tiger Team report and the JESB recommendations, they jointly decided to move the launch to the next available Mars launch window in July 2020, and tasked their project teams to develop, in cooperation with the industrial contactors, a new baseline schedule aiming towards a 2020 launch. Additional measures will also be taken to maintain close control over the activities on both sides up to launch.

The successful implementation of both ExoMars missions will allow Russia and Europe to jointly validate cutting-edge technologies for Mars entry, descent, and landing, for the control of surface assets, to develop new engineering concepts and service systems that can be used by other Solar System exploration missions, and to carry out novel science at Mars.

Table 1: Second ExoMars mission moves to next launch opportunity in 2020 3)

The ExoMars 2016 mission will be launched on a Roscosmos-provided Proton rocket. It includes the TGO (Trace Gas Orbiter) and the EDM (Entry, descent and landing Demonstrator Module), both contributed by ESA. The TGO will carry European and Russian scientific instruments for remote observations, while the EDM will have a European payload for in situ measurements during descent and on the martian surface.

In November 2013, ESA named the EDM Schiaparelli in honor the 19th century Italian astronomer Giovanni Schiaparelli (1835-1910). He observed bright and dark straight-line surface features on Mars which he called ‘canali'. This term was mistakenly translated into English as ‘canal' instead of ‘channel', conjuring up images of vast irrigation networks constructed by intelligent beings living on Mars. The controversy ended in the early 20th century, thanks to better telescopes offering a clearer view of the planet. — The name was suggested by a group of Italian scientists to the president of the Italian space agency, ASI, who then proposed it to ESA. Italy is the largest European contributor to the ExoMars program. 4)

The ExoMars 2018 mission will land a Rover, provided by ESA, making use of a DM (Descent Module) contributed by Roscosmos. The DM will travel to Mars on an ESA-provided CM (Carrier Module). Roscosmos will launch the spacecraft composite on a Proton rocket. The Rover will be equipped with a European and Russian suite of instruments, and with Russian RHUs (Radioisotope Heating Units). The Rover will also include a 2 m drill for subsurface sampling and a SPDS (Sample Preparation and Distribution System), supporting the suite of geology and life seeking experiments in the Rover's ALD (Analytical Laboratory Drawer). The Russian SP (Surface Platform) will contain a further suite of instruments, mainly concentrating on environmental and geophysical investigations. 5)

NASA will also deliver important elements to ExoMars: The Electra UHF (Ultra-High Frequency) radio package on TGO for Mars surface proximity link communications with landed assets (such as the Rover and Surface Platform); engineering support to EDM; and a major part of MOMA (Mars Organic Molecule Analyzer), the organic molecule characterization instrument on the Rover.

Diameter: 6794 km (about half the diameter of Earth)

Surface area: 145 million km2 (about the same as the land area of Earth)

Gravity: 3.711 m s-2 (about one third of Earth's gravity)

Density: 3.93 g cm-3 (Earth: 5.51 g cm-3)

Average distance from the Sun: 227,940,000 km (1.52 times that of Earth)

Martian day (a ‘sol'): 24 hours 37 minutes

Martian year: 669 sols or 687 Earth days

Average temperature: –55ºC (from –133ºC at the winter pole to +27ºC during summer)

Atmosphere: 95.32% carbon dioxide, 2.7% nitrogen, 1.6% argon, 0.13% oxygen

Atmospheric pressure at the surface: 6.35 mbar (less than one hundredth of Earth's atmospheric pressure)

Moons: Phobos: 27 x 22 x 18 km; ~6000 km from the surface; Deimos: 15 x 12 x 11 km; ~20,000 km from the surface

Table 2: An overview of some Mars parameters 6)



Spacecraft of ExoMars 2016 mission:

The ExoMars mission is the first ESA-led robotic mission of the Aurora Program and combines technology development with investigations of major scientific interest. The main objectives of this mission are to search for evidence of methane and other trace atmospheric gases that could be signatures of active biological or geological processes and to test key technologies in preparation for ESA's contribution to subsequent missions to Mars. 7)

The ExoMars 2016 mission spacecraft includes the following elements, all developed under the leadership of the prime contractor TAS-I (Thales Alenia Space-Italia). 8)

• TGO (Trace Gas Orbiter), developed by Thales Alenia Space, France

• EDM, developed directly by TAS-I

• MSA (Main Separation Assembly), developed by RUAG.

The TGO accommodates scientific instrumentation for the detection of atmospheric trace gases and the study of their temporal and spatial evolution. In addition, it will provide telecommunications support for the 2016 mission, for the 2018 mission and possible other assets until 2022.

The objectives of the ExoMars 2016 mission are to:

1) Validate landing on the planet Mars with a demonstration capsule weighing about 600 kg, using a control system based on a radar altimeter, and with a carbon fiber shock absorber to attenuate the hard contact with the surface.

2) Gather as much information as possible during entry into the Martian atmosphere.

3) Carry out scientific sampling on the surface for a short period.

4) Observe the Martian atmosphere and surface for two years from the orbiter at an altitude of 400 km.

5) Provide the telecommunication support needed by the rover for the 2018 mission.

The EDM is mainly conceived to demonstrate EDL (Entry Descent and Landing) technologies for future planetary exploration missions. The following technologies are foreseen to be demonstrated:

• TPS (Thermal Protection System)

• PAS (Supersonic Parachute System)

• Radar technologies for ground relative altitude and velocity measurements

• Propulsion technologies for attitude control and braked landing

• Crushable material for impact load attenuation.


Figure 1: Artist's rendition of the deployed ExoMars 2016 Trace Gas Orbiter (TGO) and Schiaparelli – the entry, descent and landing demonstrator module (image credit: ESA, ATG medialag)


TGO (Trace Gas Orbiter)

The technical team behind the ExoMars spacecraft involves companies across more than 20 countries. The prime contractor, Thales Alenia Space Italia, is leading the industrial team building the spacecraft (Ref. 6). As a part of the European industrial team, OHB System AG was responsible for developing the core module of the TGO, which comprises the structure as well as the thermal and propulsion system for the 2016 mission. OHB as member of the core industrial team, is responsible for the major German contribution to ExoMars.


3.2 m x 2 m x 2 m with solar wings (20 m2) spanning 17.5 m tip-to-tip providing approximately 2000 W of power

Launch mass

4332 kg (including 112 kg of science payload and 600 kg Schiaparelli)


Bipropellant, with a 424 N main engine for Mars orbit insertion and major maneuvers


In addition to power generated by the solar wings, 2 lithium-ion batteries will be used to cover eclipses, with ~ 5100 Wh total capacity


65 W X-band system with 2.2 m diameter high-gain antenna and 3 low-gain antennas for communication with Earth; Electra UHF-band transceivers (provided by NASA) with a single helix antenna for communication with surface rovers and landers

Science instrument package

ACS (Atmospheric Chemistry Suite); CaSSIS (Color and Stereo Surface Imaging System); FREND (Fine Resolution Epithermal Neutron Detector); NOMAD (Nadir and Occultation for Mars Discovery)

Nominal mission end


Table 3: Main technical characteristics of the ExoMars Trace Gas Orbiter

NASA's participation in the 2016 ExoMars Trace Gas Orbiter includes two "Electra" telecommunication radios. Used successfully on NASA's Mars Reconnaissance Orbiter, Electra acts as a communications relay and navigation aid for Mars spacecraft. Electra's UHF radios support navigation, command, and data-return needs. 9)

TGO's Electra radios use a design from NASA/JPL with special features for relaying data from a rover or stationary lander to an orbiter passing overhead. Relay of information from Mars-surface craft to Mars orbiters, then from Mars orbit to Earth, enables receiving much more data from the surface missions than would otherwise be possible.

As an example of Electra capabilities, during a relay session between an Electra on the surface and one on an orbiter, the radios can maximize data volume by actively adjusting the data rate to be slower when the orbiter is near the horizon from the surface robot's perspective, faster when it is overhead.


Figure 2: This image shows a step in installation and testing of the first of the orbiter's Electra radios, inside a clean room at Thales Alenia Space, in Cannes, France, in June 2014 (image credit: NASA/JPL-Caltech/ESA/TAS) 10)

RCS (Reaction Control System): TGO requires a challenging propulsion subsystem. The TGO RCS will provide the thrust to the spacecraft for all initial trajectory corrections, DSMs (Deep Space Maneuvers) during the cruise phase to Mars and also the high thrust necessary for the final MOI (Mars Orbit Insertion) maneuver. Subsequently, it shall perform 3-axis attitude control of the TGO once in orbit around Mars for the remainder of its seven year lifetime. 11)

The selected RCS is a helium-pressurized bi-propellant propulsion system utilizing MMH (Monomethylhydrazine) as the fuel and mixed oxides of nitrogen (MON-1) as the oxidizer. The architecture is derived from previous flight proven European applications, however the detailed layout is unique and driven by the specific configuration of the TGO spacecraft and the redundancy needs of the ExoMars 2016 mission.

All RCS architecture and engineering activities have been performed by OHB-System (including all subsystem analyses), while Airbus Defence and Space has responsibility for the mechanical configuration, procurement and manufacturing of equipment, integration and acceptance test to ensure that the system requirements defined by TAS-F are satisfied. The subsystem test program has been defined by OHB-System and performed by Airbus DS at the Airbus DS, OHB-System and TAS facilities. Out of the 92 components comprising the flight RCS, 67 are manufactured by Airbus DS including all tanks and thrusters.


Figure 3: The ExoMars Trace Gas Orbiter and Schiaparelli (top) during vibration testing in 2015, the high-gain antenna is on the right (image credit: ESA, S. Corvaja)


Schiaparelli / EDM (Entry, Descent and Landing Demonstrator Module)

Landing on Mars: Despite a number of prominent US successes since the 1970s, landing on Mars remains a significant challenge. As part of the ExoMars program, a range of technologies has been developed to enable a controlled landing. These include a special material for thermal protection, a parachute system, a radar altimeter system, and a final braking system controlled by liquid-propellant retrorockets. Schiaparelli is designed to test and demonstrate these technologies, in preparation for future missions (Ref. 6).

Three days before reaching Mars, Schiaparelli will separate from TGO and coast towards the planet in hibernation mode, to reduce its power consumption. It will be activated a few hours before entering the atmosphere at an altitude of 122.5 km and at a speed of 21 000 km/h. An aerodynamic heatshield will slow the lander down such that at an altitude of about 11 km, when the parachute is deployed, it will be travelling at around 1650 km/h.

Schiaparelli will release its front heat shield at an altitude of about 7 km and turn on its radar altimeter, which can measure the distance to the ground and its velocity across the surface. This information is used to activate and command the liquid propulsion system once the rear heatshield and parachute has been jettisoned 1.3 km above the surface. At this point, Schiaparelli will still be travelling at nearly 270 km/h, but the engines will slow it to less than 2 km/h by the time it is 2 m above the surface. At that moment, the engines will be switched off and Schiaparelli will freefall to the ground, where the final impact, at just under 11 km/h, will be cushioned by a crushable structure on the base of the lander.

Although Schiaparelli will target the plain known as Meridiani Planum in a controlled landing, it is not guided, and the module has no obstacle-avoidance capability. It has, however, been designed to cope with landing on a terrain with rocks as tall as 40 cm and slopes as steep as 12.5º.

Because Schiaparelli is primarily demonstrating technologies needed for landing, it does not have a long scientific mission lifetime: it is intended to survive on the surface for just a few days by using the excess energy capacity of its batteries. However, a set of scientific sensors will analyse the local environment during descent and after landing, including performing the first measurements of atmospheric particle charging effects, to help understand how global dust storms get started on Mars. A communication link with TGO will provide realtime transmission of the most important operational data measured by Schiaparelli during its descent. Shortly after Schiaparelli lands, TGO will start a main engine burn and will return over the landing site only four sols later. In the meantime, the remainder of the entry, descent and landing data, along with some of the science instrument data, will be sent to Earth via ESA's Mars Express and NASA satellites already at Mars.

Schiaparelli Design:

Schiaparelli builds on a heritage of designs that have been evaluated and tested by ESA during earlier ExoMars studies. The module accommodates a series of sensors that will monitor the behaviour of all key technologies during the mission. These technologies include a special material for thermal protection, a parachute system, a radar Doppler altimeter system, and a braking system controlled by liquid propulsion. The data will be sent back to Earth for post-flight reconstruction in support of future European missions to Mars.


2.4 m in diameter with heatshield, 1.65 m without heatshield


600 kg

Heat shield material

Norcoat Liege


Aluminum sandwich with CFRP (Carbon Fiber Reinforced Polymer) skins


Disk-Gap-Band canopy, 12 m diameter


3 clusters of 3 hydrazine engines (400 N each), operated in pulse-modulation




UHF link with the ExoMars Orbiter (with 2 antennas)

Table 4: Main technical characteristics of Schiaparelli – the ExoMars EDM (Entry, Descent and Landing Demonstrator Module)


Figure 4: Photo of the Schiaparelli/EDM structural model which is being lowered onto the Multishaker at ESA/ESTEC (image credit: ESA, A. Le Floc'h, Ref. 4)


Launch preparations: In late December 2015, the ExoMars 2016 Trace Gas Orbiter and Schiaparelli (the entry, descent and landing demonstrator module) travelled aboard two Antonov 124 cargo jets from Turin, Italy, to the Baikonur Cosmodrome in Kazakhstan to be readied for launch in March. 12)

Since then, engineering teams, totaling about 65 people, from Thales Alenia Space (Italy and France), the ExoMars project team, instrument teams, and specialists from the Baikonur Cosmodrome have been steadily working through an intensive and painstaking program of final testing and preparation of the two spacecraft, which at 4.300 kg will be the heaviest spacecraft composite ever to be sent to Mars.

All this has to be completed in time for a launch scheduled for 14 March at the beginning of the 12-day launch window for this mission.

Central to the launch campaign activities is the cleanroom. Almost everything in the cleanroom has been transported from Europe for this launch campaign – hence the need for a third Antonov flight. In addition to the specialist lifting equipment and the ground support trolleys needed to move the two spacecraft, the teams have also had to prepare a dedicated ISO 7 environment cleanroom tent, within the "normal" ISO 8 cleanroom environment, for handling Schiaparelli which, being a Mars lander, must be regularly sampled to check that it satisfies the planetary protection regulations. For analysis of these samples a dedicated microbiological laboratory was brought from Turin and installed close to the cleanroom area.

The readying of the TGO (Trace Gas Orbiter) has included a series of system health checks, such as checking that signals could be sent to all spacecraft units and that they responded. The health of the payload – the four science instruments, ACS, CaSSIS, FREND and NOMAD – was checked in a similar manner by verifying that commands could be sent to them and that these commands were carried out. The flight model of FREND was swapped for the flight spare model.

Another important test that has been completed was with the Trace Gas Orbiter and the launch vehicle adapter. Mechanical fit checks and separation tests had already been done in Cannes last year. Here in Baikonur, the team checked the mechanical connections, and also verified that all electrical circuits were completed.

In parallel, Schiaparelli is also being prepared for launch and is subject to tests similar to those performed on the orbiter. The instruments, sensors (DREAMS and COMARS+) and systems have all been thoroughly checked. A leak test has been carried out. Engineers have uploaded the final software and charged the batteries - since Schiaparelli has no solar panels the fully charged batteries are essential for the surface operations. 13)

The mating of the TGO (Trace Gas Orbiter) and Schiaparelli began on 12 February, 2016 with the two spacecraft having been transferred into the fuelling area, where a mounting platform surrounding the orbiter facilitates the activities that need to be done about 4 m off the ground.

TGO and Schiaparelli are mechanically linked with the MSA (Main Separation Assembly), which attaches to TGO with 27 screws. The MSA holds onto Schiaparelli with three separation mechanisms comprising compressed and angled springs that are held by NEAs (Non-Explosive Actuators). When the NEAs are released on 16 October, as the spacecraft approaches Mars, Schiaparelli will be gently pushed away from TGO, at the same time being imparted with a rotation that will serve to stabilize its atmospheric entry.


Figure 5: The ExoMars 2016 Trace Gas Orbiter (with Schiaparelli on top) being fuelled at the Baikonur Cosmodrome in Kazakhstan (image credit: ESA) 14)

Legend to Figure 5: This spacecraft has one fuel tank and one oxidizer tank, each with a capacity of 1207 liter. When fuelling is complete, the tanks will contain about 1.5 ton of MON (mixed oxides of nitrogen) and 1 ton of MMH (monomethylhydrazine). The propellant is needed for the main engine and the 10 thrusters (plus 10 backup thrusters) that are used for fine targeting and critical maneuvers.


Figure 6: The ExoMars 2016 spacecraft, comprised of the Trace Gas Orbiter and Schiaparelli, are now sealed inside the rocket fairing (image credit: ESA, B. Bethge) 15) 16)

Legend to Figure 6: On March 2, 2016, the Breeze upper stage and spacecraft were encapsulated together within the two fairing halves. Prior to the encapsulation, they were tilted horizontally and the first fairing half was rolled underneath the spacecraft and Breeze, on a track inside the cleanroom. The second fairing half was then lowered into place by means of an overhead crane, encapsulating the payload.


Figure 7: Proton-M rocket with ExoMars 2016 Trace Gas Orbiter and Schiaparelli module at the launch pad in Baikonur, Kazakhstan (image credit: ESA, B. Bethge) 17)


Launch: The European-Russian ExoMars (TGO and the EDM Schiaparelli lander) satellite was launched on March 14, 2016 (09:31 GMT) on a Proton-M/Briz vehicle from the Baikonur Cosmodrome, Kazakhstan. The launch provider was ILS (International Launch Services) KhSC (Khrunichev State Research and Production Space Center). 18) 19) 20)

Orbit: The SCC (ExoMars Spacecraft Composite) will be inserted into a T-2 transfer trajectory to Mars. The arrival on Mars is planned on Oct. 19, 2016 after a 9-month cruise phase.

During the cruise phase, the TGO will support all necessary operations and communications with Earth, and will provide the EDM (Schiaparelli) with the required power/energy. During this period, the EDM will be mostly in hibernation mode to minimize the TGO energy consumption, and nominally will be switched on only for three checkouts: the EDM commissioning checkout few days after the launch, the mid-cruise checkout to verify the EDM health status after the DSM (Deep Space Maneuver), and the preseparation checkout few hours before the separation from the TGO.

The EDM will be released by the TGO three days before the arrival at Mars (i.e. on Oct. 16th, 2016) by means of a 3-points spin-up separation mechanism (MSA). The separation provides a relative velocity higher than 0.3 m/s and a spin rate of 2.5 rpm. The spin rate will allow the EDM for maintaining the attitude needed to reach the Mars atmosphere EIP (Entry Interface Point) with a null angle of attack. The duration of the EDM coast phase (3 days), driven by the TGO need to have enough time to correct its orbit after the EDM separation and prepare the critical MOI ()Mars Orbit Injection) maneuver, is challenging for the EDM as the dispersions, coming from the navigation and from the separation mechanism, will propagate for quite a long time, by increasing the trajectory dispersions at Mars EIP.

During the coast phase, the EDM will be mainly in hibernation mode, to minimize the energy consumption from its batteries. Shortly before the arrival at the Mars EIP, the EDM will wake up from the hibernation to prepare the EDL phase.

The ExoMars Orbiter, TGO, will be inserted into an elliptical orbit around Mars and then sweep through the atmosphere to finally settle into a circular, approximately 400 km altitude orbit ready to conduct its scientific mission; inclination = 74º, period of ~2 hours.

TGO will also serve as a data relay for the second ExoMars mission, comprising a rover and a surface science platform, planned for launch in 2018. It will also provide data relay for NASA rovers.



Mission status:

• October 16, 2017: Diffuse, water-ice clouds, a hazy sky and a light breeze. Such might have read a weather forecast for the Tharsis volcanic region on Mars on 22 November 2016, when this image was taken by the ExoMars TGO (Trace Gas Orbiter). 21)

- Below, 630 km west of the volcano Arsia Mons, the southernmost of the Tharsis volcanoes, outlines of ancient lava flows dominate the surface (Figure 8). The dark streaks are due to the action of wind on the dark-colored basaltic sands, while redder patches are wind blown dust. A handful of small impact craters can also be seen.

- The Trace Gas Orbiter, a joint effort between ESA and Roscosmos, arrived at Mars on 19 October last year. Since March it has been repeatedly surfing in and out of the atmosphere, generating a tiny amount of drag that will steadily pull it into a near-circular 400 km altitude orbit. It is expected to begin its full science operational phase from this orbit in early 2018.

- Prior to this ‘aerobraking' phase, several test periods were assigned to check the four science instrument suites from orbit and to refine data processing and calibration techniques.

- The false-color composite shown here was made from images taken with the CaSSIS (Color and Stereo Surface Imaging System) in the near-infrared, red and blue channels.

- The image is centered at 131°W / 8.5°S. The ground resolution is 20.35 m/pixel, and the image is about 58 km across. At the time the image was taken, the altitude was 1791 km, yielding a ground track speed of 1.953 km/s.


Figure 8: A cloudy day over volcanic Mars, captured by the ExoMars orbiter. Clouds, most likely of water-ice, and atmospheric haze in the sky are colored blue/white in this image (image credit: ESA/Roscosmos/CaSSIS, CC BY-SA 3.0 IGO)

• May 24, 2017: The inquiry into the crash-landing of the ExoMars Schiaparelli module has concluded, that conflicting information in the onboard computer caused the descent sequence to end prematurely. 22)

- The Schiaparelli entry, descent and landing demonstrator module separated from its mothership, the TGO (Trace Gas Orbiter), as planned on 16 October last year, and coasted towards Mars for three days.

- Much of the six-minute descent on 19 October 2016 went as expected: the module entered the atmosphere correctly, with the heatshield protecting it at supersonic speeds. Sensors on the front and back shields collected useful scientific and engineering data on the atmosphere and heatshield.


Figure 9: Schiaparelli's heatshield was equipped with a variety of sensors designed to take measurements as the module entered the atmosphere. The COMARS+ (Combined Aerothermal and Radiometer Sensors Instrument Package), used sensors on the back heatshield to measure pressure, temperature and heat flux. System sensors on the front shield were monitored by the data housekeeping system (image credit: ESA/ATG medialab)

- Telemetry from Schiaparelli was relayed to the main craft, which was entering orbit around the Red Planet at the same time – the first time this had been achieved in Mars exploration. This realtime transmission proved invaluable in reconstructing the unfolding chain of events.

- At the same time as the orbiter recorded Schiaparelli's transmissions, ESA's Mars Express orbiter also monitored the lander's carrier signal, as did the Giant Meterwave Radio Telescope in India.

- In the days and weeks afterwards, NASA's Mars Reconnaissance Orbiter took a number of images identifying the module, the front shield, and the parachute still connected with the backshield, on Mars, very close to the targeted landing site.

- The images of Figure 10 suggested that these pieces of hardware had separated from the module as expected, although the arrival of Schiaparelli had clearly been at a high speed, with debris strewn around the impact site.

- The independent external inquiry, chaired by ESA's Inspector General, has now been completed.

- It identifies the circumstances and the root causes, and makes general recommendations to avoid such defects and weaknesses in the future. The report summary can be downloaded here. A summary of the final report is available in PDF. 23)

- Around three minutes after atmospheric entry the parachute deployed, but the module experienced unexpected high rotation rates. This resulted in a brief ‘saturation' – where the expected measurement range is exceeded – of the Inertial Measurement Unit, which measures the lander's rotation rate.

- The saturation resulted in a large attitude estimation error by the guidance, navigation and control system software. The incorrect attitude estimate, when combined with the later radar measurements, resulted in the computer calculating that it was below ground level.


Figure 10: Composite of the ExoMars Schiaparelli module elements seen by NASA's MRO (Mars Reconnaissance Orbiter) HiRISE (High Resolution Imaging Science Experiment) on 1 November 2016. Both the main impact site (top) and the region with the parachute and rear heatshield (bottom left) are now captured in the central portion of the HiRISE imaging swath that is imaged through three different filters, enabling a color image to be constructed. The front heatshield (bottom right) lies outside the central color imaging swath (image credit: NASA/JPL-Caltech/University of Arizona) 24)

Legend to Figure 10: The colors have been graded according to the specific region to best reveal the contrast of features against the martian background. These images are in raw image geometry rather than map-projected, and north is about 7º west of straight up.

- This resulted in the early release of the parachute and back-shell, a brief firing of the thrusters for only 3 sec instead of 30 sec, and the activation of the on-ground system as if Schiaparelli had landed. The surface science package returned one housekeeping data packet before the signal was lost.

- In reality, the module was in free-fall from an altitude of about 3.7 km, resulting in an estimated impact speed of 540 km/h.

- The Schiaparelli Inquiry Board report noted that the module was very close to landing successfully at the planned location and that a very important part of the demonstration objectives were achieved. The flight results revealed required software upgrades, and will help improve computer models of parachute behavior.

- "The realtime relay of data during the descent was crucial to provide this in-depth analysis of Schiaparelli's fate," says David Parker, ESA's Director of Human Spaceflight and Robotic Exploration.

- "We are extremely grateful to the teams of hard-working scientists and engineers who provided the scientific instruments and prepared the investigations on Schiaparelli, and deeply regret that the results were curtailed by the untimely end of the mission. - There were clearly a number of areas that should have been given more attention in the preparation, validation and verification of the entry, descent and landing system. We will take the lessons learned with us as we continue to prepare for the ExoMars 2020 rover and surface platform mission. Landing on Mars is an unforgiving challenge but one that we must meet to achieve our ultimate goals."

- "Interestingly, had the saturation not occurred and the final stages of landing had been successful, we probably would not have identified the other weak spots that contributed to the mishap," notes Jan Woerner, ESA's Director General. "As a direct result of this inquiry we have discovered the areas that require particular attention that will benefit the 2020 mission."

- ExoMars 2020 (Figure 11) has since passed an important review confirming it is on track to meet the launch window. Having been fully briefed on the status of the project, ESA Member States at the Human Spaceflight, Microgravity and Exploration Program Board reconfirmed their commitment to the mission, which includes the first Mars rover dedicated to drilling below the surface to search for evidence of life on the Red Planet.

- Meanwhile the Trace Gas Orbiter has begun its year-long aerobraking in the fringes of the atmosphere that will deliver it to its science orbit in early 2018. The spacecraft has already shown its scientific instruments are ready for work in two observing opportunities in November and March.

- In addition to its main goal of analyzing the atmosphere for gases that may be related to biological or geological activity, the orbiter will also act as a relay for the 2020 rover and surface platform. — The ExoMars program is a joint endeavor between ESA and Roscosmos.


Figure 11: Artist's impression of the ExoMars 2020 rover (foreground), surface science platform (background) and the Trace Gas Orbiter (top). Not to scale (image credit: ESA/ATG medialab)

• March 28, 2017: Two ancient sites on Mars that hosted an abundance of water in the planet's early history have been recommended as the final candidates for the landing site of the 2020 ExoMars rover and surface science platform: Oxia Planum and Mawrth Vallis. 25)

- A primary technical constraint is that the landing site be at a suitably low level, so that there is sufficient atmosphere to help slow the landing module's parachute descent. Then, the 120 x 19 km landing ellipse should not contain features that could endanger the landing, the deployment of the surface platform ramps for the rover to exit, and driving of the rover. This means scrutinizing the region for steep slopes, loose material and large rocks.

- Oxia Planum was selected in 2015 for further detailed evaluation. Although not yet complete, the investigation so far indicates that the region would meet the various constraints. In addition, one other site had to be chosen from Aram Dorsum and Mawrth Vallis.

- After a two-day meeting with experts from the Mars science community, industry, and ExoMars project, during which the scientific merits of the three sites were presented alongside the preliminary compliance status with the engineering constraints, it was concluded that Mawrth Vallis will be the second site to be evaluated in more detail.

- Around a year before launch, the final decision will be taken on which site will become the ExoMars 2020 landing target.

- All of the sites lie just north of the equator, in a region with many channels cutting through from the southern highlands to the northern highlands. As such, they preserve a rich record of geological history from the planet's wetter past billions of years ago, and are prime targets for missions like ExoMars that are searching for signatures of past life on Mars.

- Oxia Planum lies at a boundary where many channels emptied into the vast lowland plains and exhibits layers of clay-rich minerals that were formed in wet conditions some 3.9 billion years ago.

- Observations from orbit show that the minerals in Oxia Planum are representative of those found in a wide area around this region, and so would provide insight into the conditions experienced at a global scale during this epoch of martian history.

- Mawrth Vallis is a large outflow channel a few hundred kilometers away from Oxia Planum. The proposed landing ellipse is just to the south of the channel. The entire region exhibits extensively layered, clay-rich sedimentary deposits, and a diversity of minerals that suggests a sustained presence of water over a period of several hundred million years, perhaps including localized ponds.

- In addition, light-toned fractures containing ‘veins' of water-altered minerals point to interactions between rocks and liquid in subsurface aquifers, and possible hydrothermal activity that may have been beneficial to any ancient life forms.

- Mawrth Vallis offers a window into a large period of martian history that could probe the early evolution of the planet's environment over time. "While all three sites under discussion would give us excellent opportunities to look for signatures of ancient biomarkers and gain new insights into the planet's wetter past, we can only carry two sites forward for further detailed analysis," says Jorge Vago, ESA's ExoMars rover project scientist. "Thus, after an intense meeting, which focused primarily on the scientific merits of the sites, the Landing Site Selection Working Group has recommended that Mawrth Vallis join Oxia Planum as one of the final two candidates for the ExoMars 2020 mission. Both candidate sites would explore a period of ancient martian history that hasn't been studied by previous missions."


Figure 12: Oxia Planum texture map (image credit: Base map: NASA/JPL-Caltech/Arizona State University; analysis: IRSPS/TAS-I)

Legend to Figure 12: One example of how the Oxia Planum landing site under consideration for the ExoMars 2020 mission is being analyzed. The map outlines a boundary (red) that encapsulates the range of possible 120 x 19 km landing ellipses, with some added margin. Elevation contours are also indicated. The colors represent the variety of surface terrains identified, including plains (green shades), channels (blues), impact craters (yellow, with black outlines), and wind-blown features (pink). It is not a geological map intended for scientific analysis, but rather a tool used to identify different surface textures and where potential hazards may lie.
The background image is from the Thermal Emission Imaging System instrument on NASA's Mars Odyssey orbiter.


Figure 13: Mawrth Vallis martian mosaic (image credit: ESA/DLR/FU Berlin, CC BY-SA 3.0 IGO)

Legend to Figure 9: Sculpted by ancient water flowing on the surface, Mawrth Vallis is one of the most remarkable outflow channels on Mars. The valley, once a potentially habitable place, is one of the main features of a region at the boundary between the southern highlands and the northern lowlands.

Mawrth Vallis takes center stage in this image, a bird's eye view of a 330,000 km2 area surrounding the valley. With a length of 600 km and a depth of up to 2 km, it is one of the biggest valleys on Mars. Huge amounts of water once passed through it, from a higher elevation region, part of which is shown in the lower right of the image, into the northern plains, in the top left.

Among the remarkable features are the large exposures of light-toned phyllosilicates (weathered clay minerals) that lie along its course. Phyllosilicates on Mars are evidence of the past presence of liquid water and point to the possibility that habitable environments could have existed on the planet up until 3.6 billion years ago.

A dark cap rock, remains of ancient volcanic ash, covers many of the clays and could have protected traces of ancient microbes in the rocks from radiation and erosion. This makes Mawrth Vallis one of the most interesting regions for geologists and astrobiologists alike. It is one of the candidate landing sites for ExoMars 2020, a joint mission between ESA and Russia, with the primary goal of finding out if life once existed on Mars.

The name comes from the Welsh word for Mars ("Mawrth") and the Latin for valley ("Vallis"). This mosaic was created using nine individual images taken by the high-resolution stereo camera on ESA's Mars Express spacecraft, which has been orbiting Mars since late 2003. It is one of a set of images of this region previously published on 7 July 2016 on the DLR website and the homepage of the Freie Universität Berlin.

• March 27, 2017: Choosing the rover's landing site is a demanding and lengthy process, because it must not only be interesting scientifically but also safe from an engineering viewpoint. Establishing whether life ever existed on Mars is at the heart of the ExoMars program, thus the chosen site should be ancient – around 3.9 billion years old – with abundant evidence of water having been present for extended periods. 26)

- The rover has a drill (the dark grey box at the front in Figure 14) that is capable of extracting samples from depths of 2 m. This is crucial, because the present surface of Mars is a hostile place for living organisms owing to the harsh solar and cosmic radiation. By searching underground, the rover has a better chance of finding preserved evidence.

- From an engineering perspective, the site has to be low-lying, to allow the entry module to descend through enough atmosphere to help slow its descent with parachutes, and it must not contain features that could endanger the landing, such as craters, steep slopes and large rocks.


Figure 14: ESA's ExoMars rover (foreground) and Russia's stationary surface science platform (background) are scheduled for launch in July 2020, arriving at Mars in March 2021. The Trace Gas Orbiter, which has been at Mars since October 2016, will act as a relay station for the mission, as well as conducting its own science mission (image credit: ESA/ATG medialab)

- The 310 kg rover will traverse the martian landscape on six wheels (Figure 15). It will be the first rover capable of drilling down 2 m, where ancient biomarkers may still be preserved from the harsh radiation environment on the surface. The drill is housed in the large box at the front of the rover. It will collect samples with the drill and deliver them to the Analytical Laboratory Drawer in the body of the rover, via the sample delivery window.

- The drill, shown here with the front casing of the drill box removed to reveal the interior, also contains the Mars Multispectral Imager for Subsurface Studies (Ma_MISS), which will image the walls of the borehole created by the drill to study the mineralogy and rock formation.

- PanCam, the panoramic camera, will provide stereo and 3D imagery of the terrain around the rover. ISEM (Infrared Spectrometer for ExoMars) will determine the major mineral composition of distant rocks, outcrops, and soils. CLUPI (Close-Up Imager) will acquire high-resolution, color, close-up images of outcrops, rocks, soils, drill fines and drill core samples. Navigation cameras and ‘localisation' cameras are used to determine where the rover is and where it will move.


Figure 15: Artist's impression of the ExoMars 2020 rover. This image shows the rover as viewed from the front (image credit: ESA/ATG medialab)

- The rover will traverse the martian landscape on six wheels. Power is supplied to the rover by solar arrays. These are folded during the journey to Mars and deployed once the rover is on the martian surface. Two UHF monopole antennas are used to communicate with Mars orbiters, including the Trace Gas Orbiter.

- The antennas of the WISDOM ground-penetrating radar can be seen in this view (Figure 16). The WISDOM (Water Ice Subsurface Deposit Observation on Mars) instrument suite will provide a detailed view of the Red Planet's shallow subsurface structure by sounding the upper layers of its crust. This will give three-dimensional geological context of the terrain covered by the rover.


Figure 16: Artist's impression of the ExoMars 2020 rover. This image shows the rover as viewed from behind (image credit: ESA/ATG medialab)

• March 16, 2017: The ExoMars TGO (Trace Gas Orbiter) has completed another set of important science calibration tests before a year of aerobraking gets underway. The mission was launched a year ago this week, and has been orbiting the Red Planet since 19 October. During two dedicated orbits in late November 2016, the science instruments made their first calibration measurements since arriving at Mars. The latest tests were carried out 5–7 March from a different orbit, and included checking procedures associated with taking images and collecting data on the planet's atmosphere. 27)

- For example, the NOMAD (Nadir and Occultation for Mars Discovery) instrument made test observations to help determine the best settings to make future measurements of trace gases in the atmosphere (Figure 17). Methane in particular is of high interest. On Earth it is produced primarily by biological activity, and to a smaller extent by geological processes, such as some hydrothermal reactions. Understanding how the Red Planet's methane is produced therefore has extremely exciting implications.

- NOMAD also had the opportunity to test joint measurements with the ACS (Atmospheric Chemistry Suite), which together will take highly sensitive measurements of the atmosphere to determine its constituents.


Figure 17: Test measurements of the martian atmosphere by the ExoMars TGO (Trace Gas Orbiter) NOMAD spectrometer, made on 6 March 2017. The spectra were acquired with the infrared channel of the instrument, by looking at the sunlight reflected from the planet's surface. It shows the presence of water vapor. The three colors represent three spectra taken at different times, as indicated in the legend (image credit: ESA/Roscosmos/ExoMars/NOMAD/BISA/IAA/INAF/OU)

- Meanwhile, the FREND (Fine Resolution Epithermal Neutron Detector) detector continued to collect more on the flow of neutrons from the surface. Eventually, these data will be used to identify sites where water or ice might be hidden just below the surface.

- The high-resolution CaSSIS (Color and Stereo Surface Imaging System) was commanded to take a number of images, including star calibrations, and several pointing at Mars. An example is presented here, taken just as the orbiter was crossing the boundary between day and night, over the southern hemisphere. "These dress rehearsals enable our science teams to fine-tune their data acquisition techniques including pointing commands, iron out any software bugs, and get used to working with the data, well in advance of the start of the main mission starting next year," says Håkan Svedhem, ESA's project scientist. "What we're seeing so far is really promising for our science goals."


Figure 18: The ExoMars TGO ACS (Atmospheric Chemistry Suite) made test measurements of the martian atmosphere between 28 February and 7 March 2017 (image credit: ESA/Roscosmos/ExoMars/ACS/IKI)

Legend to Figure 18: An example spectra is shown in the plot, made at thermal-infrared wavelengths. The deep and wide spectral band at the left of the plot is due to carbon dioxide, the main component of the martian atmosphere. Information held in the center of this band corresponds to the temperature of the upper layers of the atmosphere, while the ‘wings' correspond to the lower layers. - Information like this will enable scientists to compute the temperature profile of the atmosphere, which in turn will contribute to computer models of global atmosphere circulation.

- Starting next year, the craft will make its observations from a near-circular 400 km-altitude orbit, circling the planet every two hours. TGO is currently in a one-day, 200 x 33 000 km orbit but will use the atmosphere to adjust the orbit gradually by ‘aerobraking'. It will repeatedly surf in and out of the atmosphere at closest approach, pulling down its furthest point over the course of the year.

- Earlier this week, the first commands for aerobraking were uploaded, ready to be executed starting yesterday. Over the next few weeks it will make seven engine burns that will adjust its orbit as part of a ‘walk-in' period before the main aerobraking. This will first see the closest point of the orbit reduced to about 113 km.


Figure 19: The ExoMars TGO neutron detector FREND was switched on between 24 February and 2 March, and 5–7 March 2017 and collected data during eight orbits of the planet, with three of its detectors. The data obtained during the first test campaign, and those of the second campaign will be used to estimate the spacecraft internal background radiation and the level of neutron signal from Mars (image credit: ESA/Roscosmos/ExoMars/FREND/IKI, Ref. 27)

• March 13, 2017: As part of preparations for its main science mission to analyze the atmosphere for gases that may be related to biological or geological activity, and image sites that might be related to these sources, the TGO (Trace Gas Orbiter) has conducted two campaigns to test its science instruments – one last November and one last week (Figure 20). Presented here is one of the first image pairs taken by the orbiter's high-resolution camera on 22 November, 2016. 28)

- By combining the image pair, a 3D image can be constructed and information about the relative heights of the surface features can be seen. The images were taken to test the timing of the images as the spacecraft moves over the surface, in order to best reconstruct the stereo images. Additional tests were conducted last week to fine-tune the process.

- Noctis Labyrinthus, or ‘Labyrinth of the night', lies on the western edge of Valles Marineris, the grand canyon of the Solar System, and comprises a vast network of flat-topped plateaus and trenches. Landslides are seen in the flanks of the steep slopes.

- Since arriving, the orbiter has also conducted a number of maneuvers to change its orbital period and inclination, ready to begin the year-long aerobraking phase later this week. This process will use the planet's atmosphere to gradually slow the spacecraft speed and so move it into a 400 km near-circular orbit, from which the craft will conduct its main science mission.

- The images were taken by the CaSSIS camera; the scale here is 7.2 m/pixel and the images correspond to an area on Mars about 15 x 45 km.


Figure 20: The images together form a stereo pair of part of the Noctis Labyrinthus region of Mars. The camera takes one image looking slightly forwards (bottom image in this orientation, acquired on Nov. 22, 2016), and then, after having flown over the area, it rotates to look ‘back' to take the second part of the image (top), in order to see the same region of the surface from two different angles (image credit: ESA/Roscosmos/CaSSIS – CC BY-SA IGO 3.0)

• February 7, 2017: ESA's ExoMars orbiter has moved itself into a new path on its way to achieving the final orbit for probing the Red Planet. 29)

- In January, ExoMars TGO conducted a series of crucial maneuvers, firing its main engine to adjust its orbit around Mars. The three firings shifted its angle of travel with respect to the equator to almost 74º from the 7º of its October arrival. This essentially raised the orbit from equatorial to being much more north–south (Figure 21).

- The arrival orbit was set so that it could deliver the Schiaparelli lander to Meridiani Planum, near the equator, with good communications.

- Once science observations begin next year, the new 74º orbit will provide optimum coverage of the surface for the instruments, while still offering good visibility for relaying data from current and future landers.

- The inclination change was also a necessary step for the next challenge: a months-long ‘aerobraking' campaign designed to bring the spacecraft to its near-circular final science orbit, at an altitude of around 400 km.

- Mission controllers will command the craft to skim the wispy top of the atmosphere, generating a tiny amount of drag that will steadily pull it down. The process is set to begin in mid-March 2017, and is expected to take about 13 months.


Figure 21: TGO orbital inclination - before and after the maneuvers in January 2017 (image credit: ESA, C. Carreau)

- Just before aerobraking, in early March, the science teams will have another opportunity to switch on their instruments and make vital calibration measurements from the new orbit. This will add to the test data collected during two dedicated orbits late last year, and is important preparation for the main science mission.

• December 16, 2016: The first ExoMars mission arrived at the Red Planet in October and now the second mission has been confirmed to complete its construction for a 2020 launch. ESA and Thales Alenia Space signed a contract today that secures the completion of the European elements of the next mission. The main objective of the ExoMars program is to address one of the most outstanding scientific questions of our time: is there, or has there ever been, life on Mars? 30) 31)

- The TGO (Trace Gas Orbiter) will soon be exploring this question from orbit: it will take a detailed inventory of trace gases, such as methane, that might be linked to biological or geological processes. The first test of the orbiter's science instruments was recently completed. It will also act as a communications relay for various craft – in particular for 2020's rover and surface platform.

- ESA's rover will be the first capable of drilling 2 m into Mars, where ancient biomarkers may still be preserved from the harsh radiation environment on the surface.

- The Russian platform will carry instruments focused on the local atmosphere and surroundings. ExoMars is a joint endeavor between ESA and Roscosmos, with important contribution from NASA. The contract signed in Rome, Italy, secures the completion of the European elements and the rigorous tests to prove they are ready for launch.

- These include the rover itself, which will be accommodated within the Russian descent module, along with the carrier module for cruise and delivery to Mars. ESA is also contributing important elements of the descent module, such as the parachute, radar, inertial measurement unit, UHF radio elements, and the onboard computer and software.

- The science instruments for the rover and surface platform are funded by national agencies of ESA member states, Roscosmos and NASA following calls to the scientific community.

- The structural models of the carrier and rover are expected to be delivered in January and February 2017, respectively, along with structural and thermal models of the various descent module elements.

- "ExoMars is a cornerstone of ESA's exploration program," says David Parker, ESA's Director of Human Spaceflight and Robotic Exploration. "Using its miniaturized life-search laboratory and advanced robotic technology, the mission will explore the Red Planet in search of new evidence to answer questions that have long fascinated humanity. "Following the renewed support demonstrated by ESA member states in the recent Ministerial Council, this new contract allows us to complete the flight models of the European elements and keeps us on track for a July 2020 launch."

• December 16, 2016: After the smooth arrival of ESA's latest Mars orbiter, mission controllers are now preparing it for the ultimate challenge: dipping into the Red Planet's atmosphere to reach its final orbit. The ExoMars Trace Gas Orbiter is on a multiyear mission to understand the tiny amounts of methane and other gases in Mars' atmosphere that could be evidence for possible biological or geological activity. 32)

- Following its long journey from Earth, the orbiter fired its main engine on 19 October to brake sufficiently for capture by the planet's gravity. It entered a highly elliptical orbit where its altitude varies between about 250 km and 98 000 km, with each circuit taking about four Earth days. Ultimately, however, the science goals and its role as a data relay for surface rovers mean the craft must lower itself into a near-circular orbit at just 400 km altitude, with each orbit taking about two hours.

- Aerobraking: the ultimate challenge. Mission controllers will use ‘aerobraking' to achieve this, commanding the craft to skim the wispy top of the atmosphere for the faint drag to steadily pull it down. "The amount of drag is very tiny," says spacecraft operations manager Peter Schmitz, "but after about 13 months this will be enough to reach the planned 400 km altitude while firing the engine only a few times, saving on fuel."

- During aerobraking, the team at ESA's mission control in Darmstadt, Germany, must carefully monitor the craft during each orbit to ensure it is not exposed to too much friction heating or pressure. The drag is expected to vary from orbit to orbit because of the changing atmospheric, dust storms and solar activity. This means ESA's flight dynamics teams will have to measure the orbit repeatedly to ensure it does not drop too low, too quickly. The aerobraking campaign is set to begin on 15 March, when Mars will be just over 300 million km from Earth, and will run until early 2018.


Figure 22: ExoMars Trace Gas Orbiter Spacecraft Operations Manager Peter Schmitz, center, in discussions with ESA's Head of Mission Operations, Paolo Ferri, at left, during the arrival of TGO at Mars on 19 October 2016. Deputy Spacecraft Operations Manager Silvia Sangiorgi is working at the console at right (image credit: ESA, P. Shlyaev)

- Mission controllers are now working intensively to prepare the craft, the flight plan and ground systems for the campaign. First, on 19 January, they will adjust the angle of the orbit with respect to the Mars equator to 74º so that science observations can cover most of the planet.

- Next, to get into an orbit from where to start aerobraking, the high point will be reduced on 3 and 9 February 2017, leaving the craft in a 200 x 33,475 km orbit that it completes every 24 hours.

- ESA mission controllers have some previous experience with aerobraking using Venus Express, although that was done at the end of the mission as a demonstration. NASA also used aerobraking to take the Mars Reconnaissance Orbiter and other spacecraft into low orbits at Mars. "This will be our first time to use aerobraking to achieve an operational orbit, so we're taking the extra time available now to ensure our plans are robust and cater for any contingencies," says flight director Michel Denis.

- Beginning to slow down. Aerobraking proper will begin on 15 March, 2017 with a series of seven thruster firings, about one every three days, that will steadily lower the craft's altitude at closest approach – from 200 km to about 114 km. "Then the atmosphere can start its work, pulling us down," says Peter Schmitz. "If all goes as planned, very little fuel will then be needed until the end of aerobraking early in 2018, when final firings will circularize the 400 km orbit."

- No date has been set, but science observations can begin once the final orbit is achieved. In addition, the path will provide two to three overflights of each rover every day to relay signals.

- Spacecraft status: Overall, the spacecraft is in excellent health. On 30 November, it received an updated ‘operating system'. To date, only one ‘safe mode' has been triggered, when a glitch caused the craft to reboot and wait for corrective commands. That happened during preliminary testing of the main engine, when a faulty configuration was quickly identified and fixed. "We are delighted to be flying such an excellent spacecraft," says Michel. "We have an exciting and challenging mission ahead of us."

• December 6, 2016: The ExoMars TGO (Trace Gas Orbiter) has imaged the martian moon Phobos as part of a second set of test science measurements made since it arrived at the Red Planet on 19 October. 33)

- Example data from the first orbit were published last week, focusing on Mars itself. During the second orbit, the instruments made a number of measurements of Phobos, a 27 x 22 x 18 km moon that orbits Mars at a distance of only 6000 km.


Figure 23: Phobos in 3D: The camera imaged the moon on 26 November from a distance of 7700 km, during the closest part of the spacecraft's orbit around Mars. TGO's elliptical orbit currently takes it to within 230–310 km of the surface at its closest point and around 98 000 km at its furthest every 4.2 days. A color composite has been created from several individual images taken through several filters. The camera's filters are optimized to reveal differences in mineralogical composition, seen as ‘bluer' or ‘redder' colors in the processed image. (image credit: ESA)

• November 29, 2016: Data from each of the two rovers active on Mars reached Earth last week in the successful first relay test of a NASA radio aboard Europe's new TGO (Trace Gas Orbiter). 34)

- The transmissions from NASA rovers Opportunity and Curiosity, received by one of the twin Electra radios on the orbiter on Nov. 22, mark a strengthening of the international telecommunications network supporting Mars exploration. The orbiter's main radio for communications with Earth subsequently relayed onward to Earth the data received by Electra.

- Frequent use of TGO's relay capability to support Mars rover operations is planned to begin more than a year from now. That's after the orbiter finishes adjusting its orbit to a near-circular path about400 km above Mars' surface. Meanwhile, four other active Mars orbiters also carry radios that can provide relay service for missions on the surface of Mars. The two active rovers routinely send data homeward via NASA orbiters Mars Odyssey and MRO (Mars Reconnaissance Orbiter).

- "The arrival of ESA's Trace Gas Orbiter at Mars, with its NASA-provided Electra relay payload on board, represents a significant step forward in our Mars relay capabilities," said Chad Edwards, manager of the Mars Relay Network Office within the Mars Exploration Program at NASA/JPL (Jet Propulsion Laboratory), Pasadena, California. "In concert with our three existing NASA orbiters and ESA's earlier Mars Express orbiter, we now have a truly international Mars relay network that will greatly increase the amount of data that future Mars landers and rovers can return from the surface of the Red Planet."


Figure 24: This graphic depicts the geometry of Opportunity transmitting data to the orbiter, using the UHF band of radio wavelengths. The orbiter received that data using one of its twin Electra UHF-band radios. Data that the orbiter's Electra received from the two rovers was subsequently transmitted from the orbiter to Earth, using the orbiter's main X-band radio (image credit: NASA/JPL) 35)

- NASA is on an ambitious journey to Mars that will include sending humans to the Red Planet. Current and future robotic spacecraft are leading the way and will prepare an infrastructure in advance for human missions.

- The JPL-designed Electra radios include special features for relaying data from a rover or stationary lander to an orbiter passing overhead. Relay of information from Mars-surface craft to Mars orbiters, then from the Mars orbiters to Earth, enables receiving much more data from the surface missions than would be possible with a direct-to-Earth radio link from the rovers or landers.

- "We already have almost 13 years' experience using ESA's Mars Express as an on-call backup for data relay from active Mars rovers, and TGO will greatly expand this to routine science-data relay," said Michel Denis, TGO flight director at ESA/ESOC ( European Space Operations Center), Darmstadt, Germany. "In 2020, TGO will extend this relay support to ESA's ExoMars rover and the Russian Surface Platform, an important capability together with its science mission that enhances the international data network at Mars."

- As an example of Electra capabilities, during a relay session between an Electra on the surface and one on an orbiter, the radios can maximize data volume by actively adjusting the data rate to be slower when the orbiter is near the horizon from the surface robot's perspective, faster when it is overhead (Ref. 34).

• November 29, 2016: ESA's new ExoMars orbiter has tested its suite of instruments in orbit for the first time, hinting at a great potential for future observations. 36) 37)

- TGO (Trace Gas Orbiter), a joint endeavor between ESA and Roscosmos, arrived at Mars on 19 October. Its elliptical orbit takes it from 230–310 km above the surface to around 98 000 km every 4.2 days. It spent the last two orbits during 20–28 November testing its four science instruments for the first time since arrival, and making important calibration measurements.

- Data from the first orbit has been made available for this release to illustrate the range of observations to be expected once the craft arrives into its near-circular 400 km-altitude orbit late next year.

- TGO's main goal is to make a detailed inventory of rare gases that make up less than 1% of the atmosphere's volume, including methane, water vapor, nitrogen dioxide and acetylene. Of high interest is methane, which on Earth is produced primarily by biological activity, and to a smaller extent by geological processes such as some hydrothermal reactions.


Figure 25: A 25 km-wide image strip over a structure called Arsia Chasmata, which lies on the flank of the large volcano Arsia Mons. The formation is volcanic in origin and many pit craters, possibly caused by subsidence, can be seen. The image was taken on 22 November 2016 and is one of the first acquired by the CaSSIS (Color and Stereo Surface Imaging System) onboard the ExoMars Trace Gas Orbiter. The image was taken as part of an eight-day campaign to test the science instruments for the first time since arriving at the Red Planet on 19 October [image credit: ESA/Roscosmos/ExoMars/CaSSIS/UniBE; mosaicking tool: AutoStitch (University of British Columbia)]

- The two instruments tasked with this role have now demonstrated they can take highly sensitive spectra of the atmosphere. During the test observations last week, the Atmospheric Chemistry Suite focused on carbon dioxide, which makes up a large volume of the planet's atmosphere, while the Nadir and Occultation for Mars Discovery instrument homed in on water.

- They also coordinated observations with ESA's Mars Express and NASA's Mars Reconnaissance Orbiter, as they will in the future.


Figure 26: First look at the atmosphere: NOMAD infrared measurements (limb, nadir and occultation mode) acquired on Nov. 22, 2016 (image credit: ESA/Roscosmos/ExoMars/BIRA)


Figure 27: First look at the atmosphere: NOMAD ultraviolet and visible measurements acquired on Nov. 22, 2016 (image credit: ESA/Roscosmos/ExoMars/BIRA)

- Complementary measurements by the orbiter's neutron detector, FREND (Fine Resolution Epithermal Neutron Detector), will measure the flow of neutrons from the planet's surface. Created by the impact of cosmic rays, the way in which they are emitted and their speed on arriving at TGO points to the composition of the surface layer, in particular to water or ice just below the surface.

- The instrument has been active at various times during the cruise to Mars and on recent occasions while flying close to the surface could identify the relative difference between regions of known higher and lower neutron flux, although it will take several months to produce statistically significant results.


Figure 28: First detection of atmospheric carbon dioxide: ACS (Atmospheric Chemistry Suite) measurement of carbon dioxide (image credit: ESA/Roscosmos/ExoMars/UniBE)

- The different capabilities of the CaSSIS (Color and Stereo Surface Imaging System) were also demonstrated, with 11 images captured during the first close flyby on 22 November. At closest approach the spacecraft was 235 km from the surface, and flying over the Hebes Chasma region, just north of the Valles Marineris canyon system. These are some of the closest images that will ever be taken of the planet by TGO, given that the spacecraft's final orbit will be at around 400 km altitude.


Figure 29: First ExoMars stereo reconstruction of CaSSIS observations (image credit: ESA/Roscosmos/ExoMars/UniBE)

- The camera team also completed a quick first test of producing a 3D reconstruction of a region in Noctis Labyrinthus, from a stereo pair of images. Although the images are impressively sharp, data collected during this test period will help to improve the camera's onboard software as well as the quality of the images after processing.


Figure 30: First neutron flux measurements of FREND (image credit: ESA/Roscosmos/ExoMars/UniBE)

- "We are extremely happy and proud to see that all the instruments are working so well in the Mars environment, and this first impression gives a fantastic preview of what's to come when we start collecting data for real at the end of next year," says Håkan Svedhem, ESA's TGO Project Scientist. "Not only is the spacecraft itself clearly performing well, but I am delighted to see the various teams working together so effectively in order to give us this impressive insight.

- "We have identified areas that can be fine-tuned well in advance of the main science mission, and we look forward to seeing what this amazing science orbiter will do in the future."


Figure 31: Close-up of the rim of a large unnamed crater north of a crater named Da Vinci, situated near the Mars equator. A smaller, 1.4 km-diameter crater is seen in the rim along the left hand side of the image. The image scale is 7.2 m/pixel. The image was taken on 22 November 2016 and is one of the first acquired by the CaSSIS (Color and Stereo Surface Imaging System) onboard the ExoMars TGO. The image was taken as part of an eight-day campaign to test the science instruments for the first time since arriving at the Red Planet on 19 October (image credit: ESA/Roscosmos/ExoMars/CaSSIS/UniBE)


Figure 32: ExoMars science orbit 1: A graphic summarising when the TGO instruments were operating during the 20–24 November orbit (image credit: ESA/Roscosmos/ExoMars/BIRA, Ref. 36)

• November 18, 2016: The ExoMars orbiter is preparing to make its first scientific observations at Mars during two orbits of the planet starting next week. The TGO (Trace Gas Orbiter), a joint endeavor between ESA and Roscosmos, arrived at Mars on 19 October. It entered orbit, as planned, on a highly elliptical path that takes it from between 230 and 310 km above the surface to around 98,000 km every 4.2 days. 38)

- The main science mission will only begin once it reaches a near-circular orbit about 400 km above the planet's surface after a year of ‘aerobraking' – using the atmosphere to gradually brake and change its orbit. Full science operations are expected to begin by March 2018.

- But next week provides the science teams with a chance to calibrate their instruments and make the first test observations now the spacecraft is actually at Mars.

- In fact, the neutron detector has been on for much of TGO's cruise to Mars and is currently collecting data to continue calibrating the background flux and checking that nothing changed after the Schiaparelli module detached from the spacecraft. - It will measure the flow of neutrons from the martian surface, created by the impact of cosmic rays. The way in which they are emitted and their speed on arriving at TGO will tell scientists about the composition of the surface layer. In particular, because even small quantities of hydrogen can cause a change in the neutron speed, the sensor will be able to seek out locations where ice or water may exist, within the planet's top 1–2 m.

- The orbiter's other three instruments have a number of test observations scheduled during 20–28 November.

- During the primary science mission two instrument suites will make complementary measurements to take a detailed inventory of the atmosphere, particularly those gases that are present only in trace amounts. Of high interest is methane, which on Earth is produced primarily by biological activity or geological processes such as some hydrothermal reactions.

- In the upcoming orbits there are only opportunities for pointing towards the horizon or directly at the surface. This will allow the science teams to check the pointing of their instrument to best prepare for future measurements. - There is the possibility that they might detect some natural nightside airglow – an emission of light in the upper atmosphere produced when atoms broken apart by the solar wind recombine to form molecules, releasing energy in the form of light.

- During the second orbit, the scientists have also planned observations of Phobos, the larger and innermost of the planet's two moons.

- Finally, the camera will take its first test images at Mars next week. In each of the two orbits, it will first point at stars to calibrate itself for measuring the planet's surface reflectance.

- CASSIS (Color and Stereo Surface Imaging System) is the high-resolution camera onboard the TGO. It is capable of acquiring color stereo images of surface features possibly associated with trace gas sources and sinks in order to better understand the range of processes that might be related to trace gas emission.


Figure 33: How TGO's camera takes stereo images (image credit: University of Bern)

• November 3, 2016: New high-resolution images taken by a NASA's MRO (Mars Reconnaissance Orbiter) on Nov. 1, show parts of the ExoMars Schiaparelli module and its landing site in color on the Red Planet. The main impact site is now captured in the central portion of the swath that is imaged by the high-resolution camera through three filters, enabling a color image to be constructed. In addition, the image of November 1 was taken looking slightly to the west, while the earlier image was looking to the east, providing a contrasting viewing geometry. 39)

- Indeed, the latest image set sheds new light on some of the details that could only be speculated from the first look on October 25. For example, a number of the bright white spots around the dark region interpreted as the impact site are confirmed as real objects – they are not likely to be imaging ‘noise' – and therefore are most likely fragments of Schiaparelli.


Figure 34: Composite of the ExoMars Schiaparelli module elements seen by NASA's HiRISE (High Resolution Imaging Science Experiment) on MRO on Nov. 1, 2016. Both the main impact site (top) and the region with the parachute and rear heatshield (bottom left) are now captured in the central portion of the HiRISE imaging swath that is imaged through three different filters, enabling a color image to be constructed. The front heatshield (bottom right) lies outside the central color imaging swath (image credit: NASA/JPL-Caltech/University of Arizona)

Legend to Figure 34: The colors have been graded according to the specific region to best reveal the contrast of features against the martian background. These images are in raw image geometry rather than map-projected, and north is about 7º west of straight up.

• October 27, 2016: Spacecraft operations manager Peter Schmitz gives the thumbs up in the main control room at ESA's control center in Darmstadt, Germany, on 19 October 2016, shortly after the ExoMars TGO (Trace Gas Orbiter) arrived at the Red Planet. The spacecraft fired its main engine for 139 minutes to slow it down to be captured by Mars, entering an elliptical 101,000 x 3691 km orbit (with respect to the center of mass of the planet). It is in excellent health and will start making observations to calibrate its science instruments during two circuits in November 2016. 40)

• October 27, 2016: The most powerful telescope orbiting Mars is providing new details of the scene near the Martian equator where Europe's Schiaparelli test lander hit the surface last week. 41)

- The October 25, 2016, image (Figure 35) shows the area where the ESA's Schiaparelli test lander reached the surface of Mars, with magnified insets of three sites where components of the spacecraft hit the ground. It is the first view of the site from the HiRISE (High Resolution Imaging Science Experiment) camera on NASA's Mars Reconnaissance Orbiter taken after the Oct. 19, 2016, landing event. 42)

- This HiRISE observation adds information to what was learned from observation of the same area on Oct. 20 by the Mars Reconnaissance Orbiter's Context Camera (CTX). Of these two cameras, CTX covers more area and HiRISE shows more detail. A portion of the HiRISE field of view also provides color information. The impact scene was not within that portion for the Oct. 25 observation, but an observation with different pointing to add color and stereo information is planned.

- This Oct. 25 observation shows three locations where hardware reached the ground, all within about 1.5 km of each other, as expected. The annotated version includes insets with six-fold enlargement of each of those three areas. Brightness is adjusted separately for each inset to best show the details of that part of the scene. North is about 7 degrees counterclockwise from straight up. The scale bars are in meters.

- At lower left is the parachute, adjacent to the back shell, which was its attachment point on the spacecraft. The parachute is much brighter than the Martian surface in this region. The smaller circular feature just south of the bright parachute is about the same size and shape as the back shell (diameter of 2.4 m).

- At upper right are several bright features surrounded by dark radial impact patterns, located about where the heat shield was expected to impact. The bright spots may be part of the heat shield, such as insulation material, or gleaming reflections of the afternoon sunlight.

- According to the ExoMars project, which received data from the spacecraft during its descent through the atmosphere, the heat shield separated as planned, the parachute deployed as planned but was released (with back shell) prematurely, and the lander hit the ground at a velocity of more than than 300 km/hr.

- At mid-upper left are markings left by the lander's impact. The dark, approximately circular feature is about (2.4 m in diameter, about the size of a shallow crater expected from impact into dry soil of an object with the lander's mass — about 300 kg — and calculated velocity. The resulting crater is estimated to be about half a meter deep. This first HiRISE observation does not show topography indicating the presence of a crater. Stereo information from combining this observation with a future one may provide a way to check. Surrounding the dark spot are dark radial patterns expected from an impact event. The dark curving line to the northeast of the dark spot is unusual for a typical impact event and not yet explained. Surrounding the dark spot are several relatively bright pixels or clusters of pixels. They could be image noise or real features, perhaps fragments of the lander. A later image is expected to confirm whether these spots are image noise or actual surface features.


Figure 35: This Oct. 25, 2016, annotated image from the HiRISE camera on NASA's Mars Reconnaissance Orbiter shows the area where the Europe's Schiaparelli test lander struck Mars, with magnified insets of three sites where spacecraft components hit the ground. It adds detail not seen in earlier imaging of the site (image credit: NASA/JPL-Caltech/Univ. of Arizona)

• October 25, 2016: Photos of a huge circle of churned-up Martian soil leave few doubts: theESA probe Schiaparelli that was supposed to test landing technology on Mars crashed into the red planet instead, and may have exploded on impact. 43)

Figure 36: Before-and-after images taken by the Mars Reconnaissance Orbiter of NASA seem to show the impact of the Schiaparelli lander (fuzzy dark patch, 15 m x 40 m) and its parachute (bright white spot) on Mars (image credit: NASA/JPL-Caltech/Univ. of Arizona) 44)

- The events of 19 October may be painful for ESA scientists to recall, but they will now have to relive them over and over again in computer simulations. The lander, called Schiaparelli, was part of ESA's ExoMars mission, which is being conducted jointly with the Russian Space Agency Roscosmos. It was a prelude to a planned 2020 mission, when researchers aim to land a much larger scientific station and rover on Mars, which will drill up to 2-meters down to look for signs of ancient life in the planet's soil. Figuring out Schiaparelli's faults and rectifying them is a priority, says Jorge Vago, project scientist for ExoMars. "That's super important. I think it's on everybody's mind."

- Schiaparelli sent data to its mother ship during its descent. Preliminary analysis suggests that the lander began the maneuver flawlessly, braking against the planet's atmosphere and deploying its parachute. But at 4 minutes and 41 seconds into an almost 6-minute fall, something went wrong. The lander's heat shield and parachute ejected ahead of time, says Vago. Then thrusters, designed to decelerate the craft for 30 seconds until it was meters off the ground, engaged for only around 3 seconds before they were commanded to switch off, because the lander's computer thought it was on the ground.

- The lander even switched on its suite of instruments, ready to record Mars's weather and electrical field, although they did not collect data. "My guess is that at that point we were still too high. And the most likely scenario is that, from then, we just dropped to the surface," says Vago.

- The craft probably fell from a height of between 2 and 4 km before slamming into the ground at more than 300 km/hr, according to estimates based on images of Schiaparelli's likely crash site, taken by NASA's Mars Reconnaissance Orbiter on 20 October.

- The most likely culprit is a flaw in the craft's software or a problem in merging the data coming from different sensors, which may have led the craft to believe it was lower in altitude than it really was, says Andrea Accomazzo, ESA's head of solar and planetary missions. Accomazzo says that this is a hunch; he is reluctant to diagnose the fault before a full post-mortem has been carried out. But if he is right, that is both bad and good news.

- European-designed computing, software and sensors are among the elements of the lander that are to be reused on the ExoMars 2020 landing system, which, unlike Schiaparelli, will involve a mixture of European and Russian technology. But software glitches should be easier to fix than a fundamental problem with the landing hardware, which ESA scientists say seems to have passed its test with flying colors. "If we have a serious technological issue, then it's different, then we have to re-evaluate carefully. But I don't expect it to be the case," says Accomazzo.

- The ExoMars team will try to replicate the mistake using a virtual landing system designed to simulate the lander's hardware and software, says Vago, to make sure that scientists understand and can deal with the issue before redesigning any aspects of ExoMars 2020.

- ESA is keen to stress that overall, the ExoMars mission can be seen as a triumph: Schiaparelli sent back test data from the majority of its descent, and its sister craft — the Trace Gas Orbiter — successfully maneuvered into Martian orbit. The orbiter is the more scientifically valuable of the two halves of the mission: from December 2017, it will study Mars's atmosphere, aiming to find evidence for possible biological or geological sources of methane gas. It will also be a communications relay for the 2020 rover.

• October 24, 2016: Scientists and engineers on the ExoMars project had their hearts in their mouths as the ExoMars mission reached the red planet, with the Schiaparelli probe going missing in action at the end of its descent just as the TGO mothership swept into a perfectly timed orbit. 45)

- The plight of Schiaparelli remains unclear. It is certainly on the Martian surface, but may well have hit the red dust much harder then engineers had planned, and nothing has been heard from it since. Data relayed during the lander's descent shows the initial high-speed entry to the Martian atmosphere went well, with the heatshield slowing the craft and the parachute deploying. However once the back heat shield and parachute were ejected the flow of events did not go to plan.

• October 20, 2016: The TGO of ESA's ExoMars 2016 mission has successfully performed the long, 139-minute burn required for Mars capture and has entered an elliptical orbit around the Red Plane; however, contact has not yet been confirmed with the mission's test lander Schiaparelli from the surface of the planet. 46)

- TGO's Mars orbit Insertion burn lasted from 13:05 to 15:24 UTC on October 19th, reducing the spacecraft's speed and direction by more than 1.5 km/s. The TGO is now on the planned orbit around Mars. European Space Agency teams at ESOC (European Space Operations Center) in Darmstadt, Germany, continue to monitor the good health of their second orbiter around Mars, which joins the 13-year old Mars Express.

- The ESOC teams are trying to confirm contact with the Entry, Descent & Landing Demonstrator Module (EDM), Schiaparelli, which entered the Martian atmosphere some 107 minutes after the TGO's maneuver for orbit insertion. Schiaparelli was programmed to autonomously perform an automated landing sequence, with parachute deployment and front heat shield release between 11 and 7 km, followed by a retrorocket braking starting at 1100 meters from the ground and a final fall from a height of 2 meters protected by a crushable structure.

• October 12, 2016: As the ExoMars Schiaparelli module descends onto Mars on 19 October it will capture 15 images of the approaching surface. Scientists have simulated the view we can expect to see from the descent camera. - Schiaparelli will separate from its mothership, the TGO (Trace Gas Orbiter), on 16 October, with some six million km still to travel before entering the atmosphere of Mars at 14:42 GMT three days later. Its descent will take just under six minutes, using a heatshield, parachute, thrusters and a crushable structure for the landing. 47)

- Schiaparelli is primarily a technology demonstrator to test entry, descent and landing technologies for future missions and is therefore designed to operate for only Schiaparelli is primarily a technology demonstrator to test entry, descent and landing technologies for future missions and is therefore designed to operate only for a few days.

- The small surface science package will take readings of the atmosphere, but there is no scientific camera like those found on other landers or rovers – including the ExoMars rover that is planned for launch in 2020. - The lander does, however, carry ESA's small, 0.6 kg technical camera, a refurbished spare flight model of the Visual Monitoring Camera flown on ESA's Herschel/Planck spacecraft to image the separation of the two craft after their joint launch.

• July28, 2016: Following a lengthy firing of its powerful engine this morning, ESA's ExoMars TGO (Trace Gas Orbiter )is on track to arrive at the Red Planet in October. ExoMars made its first critical maneuver since its 14 March launch this morning, firing its engine for 52 minutes to help it intercept Mars on 19 October, 2016. 48)

- The deep-space firing began automatically at 09:30 GMT, after commands to orient itself and ignite the 424 N main engine were uploaded on July 26. The maneuver was closely monitored by ESA's mission control in Darmstadt, Germany, who followed the craft's signals via the highly sensitive radio dish at New Norcia, Australia. The firing was planned well in advance, and its duration was carefully calculated to minimize fuel consumption for the overall set of cruise and Mars capture maneuvers. These include a second burn on 11 August and smaller 'trim' maneuvers on 19 September and 14 October.

- Teams have been using the relatively quiet cruise phase to test spacecraft systems, including the Schiaparelli lander and the radio unit that will be used to relay data from rovers on Mars, and to check TGO's four science instruments.

- Over the following months, TGO will shave the outer reaches of the atmosphere to lower its orbit. Its final circular orbit at about 400 km altitude will allow it to begin its five-year scientific mission in December 2017.


Figure 37: Artist's impression of the ExoMars 2016 Trace Gas Orbiter with the entry, descent and landing demonstrator module, Schiaparelli, attached (image credit: ESA/ATG medialab)

• June 22, 2016: With just over half of the journey to Mars completed, the Schiaparelli entry, descent and landing module has carried out its mid-cruise checkout. DREAMS and DECA have called home to report that they are in good health. The Schiaparelli module, launched with the ExoMars Trace Gas Orbiter on 14 March, is a demonstrator to test key technologies in preparation for ESA's contributions to subsequent missions to Mars. 49)

- During the mid-cruise checkout of DREAMS that was run on 16 and 17 June, the sensors measured the environmental conditions inside the ExoMars entry descent and landing module, both in the warm compartment where the electronics are housed and in the central area of the module where the sensors are situated.

- The measurements are all perfectly in line with what is expected, according to DREAMS Principal Investigator, Francesca Esposito, from INAF - Osservatorio Astronomico di Capodimonte, Naples, Italy. "During this check-out we have looked at how the DREAMS sensors are responding inside the module as well as making some science measurements," she explains. "These tests are used to monitor the health of the sensors and to compare their behavior in space with that in the laboratory. We also use these tests to set the zero point for some of our sensors – this is important for when we are operating on Mars because we need to be sure that our sensors are all well calibrated."

- The small descent camera, DECA, was also tested during this mid-cruise checkout. DECA, which is the flight spare of the Herschel visual monitoring camera, will take 15 images at 1.5 s intervals shortly after the front shield of Schiaparelli has been jettisoned, from an altitude of a few kilometers.

- During these recent tests DE CA cycled through its image acquisition sequence to obtain 15 pictures of the dark interior of the module. These are used to check the health of the camera and to calibrate it. "DECA operates autonomously while taking the 15 images during descent," explains Detlef Koschny, Team Leader of DECA, from ESA's Scientific Support Office at ESTEC . "These checkout tests are very important as they allow us to monitor the status of the camera during flight and to calibrate it so that we can make the most of the 15 images that we will get."

- In addition to DREAMS and DECA, Schiaparelli carries the COMARS+ package to characterize the heat shield response during descent; supports an investigation into atmospheric studies with AMELIA, using engineering sensors; and carries a retroreflector, called INRRI.

• June 16, 2016: ExoMars captured its first images of Mars this week as part of its preparations for arriving at the Red Planet in October. The ExoMars TGO (Trace Gas Orbiter) acquired its first image of Mars on 13 June 2016 as part of its extensive instrument commissioning en route to the Red Planet. The line-of-sight distance to Mars on 13 June was 41 million km, giving an image resolution of 460 km/pixel. The planet is roughly 34 arcseconds in diameter at this distance. The Tharsis region of Mars, home to the planet's largest volcanoes, faces the spacecraft in this view. 50)


Figure 38: First picture of Mars acquired on June 13, 2016 by the TGO from about 41 million km away (image credit: ESA/Roscosmos/ExoMars/CaSSIS/UniBE)

• May 23, 2016: The ExoMars spacecraft, built by TAS-I (Thales Alenia Space-Italy) as prime contractor for ESA (European Space Agency ) has successfully completed its IOCR (In-Orbit Commissioning Review). 51)

- TAS has analyzed the results of the LEOP (Launch and Early Orbit Phase) and commissioning operations to draw up a report submitted to ESA. The report confirms the full functionality of the spacecraft's two constituent modules: EDM (Entry and Descent Module) and TGO (Trace Gas Orbiter). Tests on the TGO during the LEOP phase confirmed that the satellite's temperatures are within operational limits; the propulsion subsystem (Reaction Control System RCS) is operating as expected and energy consumption is nominal. The electrical parameters (voltage and current) remain stable in relation to the results of tests on Earth.

• April 14, 2016: The ESA–Roscosmos ExoMars spacecraft TGO and Schiaparelli are in excellent health following launch last month, with the orbiter sending back its first test image of a starry view taken en route to the Red Planet. In the weeks following liftoff on 14 March, mission operators and scientists have been intensively checking the TGO (Trace Gas Orbiter) and the Schiaparelli entry, descent, and landing demonstrator to ensure they will be ready for Mars in October. 52)

- TGO's control, navigation and communication systems have been set up, the 2.2 m diameter high-gain dish is already providing a 2 Mbit/s link with Earth, and the science instruments have undergone initial checks.

- Once orbiting Mars, TGO will embark on a mission to measure the abundance and distribution of rare gases in the atmosphere with its sophisticated sensors. Of particular interest is methane, which could point to active geological or biological processes on the planet.

- "All systems have been activated and checked out, including power, communications, startrackers, guidance and navigation, all payloads and Schiaparelli, while the flight control team have become more comfortable operating this new and sophisticated spacecraft," says Peter Schmitz, ESA's Spacecraft Operations Manager.

- On 7 April, TGO's high-resolution camera was switched on for the first time, acquiring its first images of space.


Figure 39: The image was taken by the CaSSIS (Color and Stereo Surface Imaging System), and points to a randomly selected portion of the sky close to the southern celestial pole (image credit: ESA/Roscosmos/CaSSIS)

Legend to Figure 39: The picture shows the result of taking one CaSSIS frame, turning the camera's rotation mechanism, and then taking another. By subtracting the two frames, a series of bright and dark spots are seen, all equally offset from each other, demonstrating that these are positive and negative images of the same stars. The FOV (Field of View) is 0.2º in the horizontal direction, and is a subset of a larger image, extracted for this purpose to show the stars at a reasonable size. The arrows indicate the offset star positions. 53)

In operation at Mars, about 400 km above the planet, CaSSIS will sweep out a swath as TGO approaches it, then turn the rotation mechanism by 180º and image the same swath as it recedes. By doing so, CaSSIS will make stereo images of the surface.

• March 23, 2016: After the critical first few days in space, TGO is performing flawlessly. Over the next two weeks the ExoMars team will continue to check and commission its systems, including the power, communications, star trackers, and the guidance and navigation system. Schiaparelli, which is hitching a ride to Mars with TGO, will also be thoroughly checked in the coming weeks. 54)

- On March 17, the mission control team had declared the LEOP (Launch and Early Orbit Phase) complete.

- In June, the science control center at ESAC (European Space Astronomy Center) near Madrid, Spain, will start working with the instrument teams at their various institutes, and the Roscosmos science operations center, to perform a mid-cruise checkout of TGO's instruments.

•Some 12 hours after launch, and after a very precise orbital delivery from the Russian Proton–Breeze rocket, ground stations in Africa, Spain and Australia began receiving the spacecraft's initial signals, confirming that TGO was alive and well, and had started its automatic sequence, switching itself on, orienting its antenna towards Earth and deploying the solar wings.

• The Breeze-M upper stage, with ExoMars attached, then completed a series of four burns before the spacecraft was released at 20:13 GMT.

• Following separation of Proton's first and second stages, the payload fairing was released. The third stage separated nearly 10 minutes after liftoff.


Figure 40: Artists rendition of the ExoMars spacecraft separation from the Briz (Breeze) fourth stage (image credit: ESA)


14 March 2016

Schiaparelli – Trace Gas Orbiter separation

16 October 2016

Trace Gas Orbiter insertion into Mars orbit

19 October 2016

Schiaparelli enters Martian atmosphere and lands on the target site

19 October 2016

Schiaparelli science operations begin

19 October 2016

TGO (Trace Gas Orbiter) changes inclination to science orbit (74°)

December 2016

Apocenter reduction maneuvers (from the initial 4-sol orbit to a 1-sol orbit)

December 2016

Aerobraking phase (Trace Gas Orbiter lowers its altitude to 400 km circular orbit)

January 2017 - November 2017

TGO science operations begin. (In parallel, TGO will start data relay operations to support NASA landers on Mars.)

December 2017

Superior solar conjunction (critical operations are paused while the Sun is between Earth and Mars)

11 July - 11 August 2017

Start of the TGO data relay operations to support communications for the rover mission and for the surface science platform

15 January 2019

End of Trace Gas Orbiter mission

December 2022

Table 5: Planned ExoMars 2016 mission phases overview 55)



Sensor complement of TGO (ACS, CaSSIS, FREND, NOMAD)

With a science payload of four instruments , the TGO will investigate trace gases – those gases that are present in small concentrations in the atmosphere, making up less than 1 per cent of it. There will be particular focus on hydrocarbons and sulphur species, some of which could be signatures of active biological or geological processes, at present or in the past.


Figure 41: Artist's rendition of the ExoMars 2016 TGO (Trace Gas Orbiter) and Schiaparelli along with the sensor allocations (image credit: ESA, ATG medialab)


ACS (Atmospheric Chemistry Suite)

ACS is a suite of three infrared spectrometers to investigate the chemistry, aerosols, and structure of the atmosphere. The package is part of the Russian contribution to the ExoMars ESA-Roscosmos mission. ACS will complement NOMAD by extending the coverage at infrared wavelengths. PI (Principal Investigator): Oleg Korablev, Space Research Institute (IKI), Moscow, Russia. Next to IKI, the following institutions are collaborating on ACS: Moscow Institute of Physics and Technology;Main Astronomical Observatory, Kyiv, Ukraine; and the National Research Institute for Physical-technical and Radiotechnical Measurements (VNIIFTRI), Moscow Region. 56) 57) 58) 59)

ACS is the set of three spectrometers (NIR, MIR, TIRVIM), covering in total range of 0.7-17 µm developed by IKI. Its design capitalizes on the previous developments of high-technology readiness: two instruments built for the unsuccessful Phobos-Grunt project and one instrument flown on the ISS (International Space Station) in the timeframe 2009–2012.12. Some components/subsystems were contributed by the DLR German Aerospace Center) Institut für Planetenforschung and by LATMOS (CNRS) in France.

The three ACS spectrometers share common mechanical, thermal, and electrical interfaces. The ACS architecture and its concept design are shown in Figure 42. ACS has several optical openings allowing observations in nadir (-Y in the spacecraft coordinate system), and in solar occultation, at 67º from -Y to -X in the XY plane, and possibly on the limb (using nadir apertures). The accuracy of spacecraft attitude control is ±1 mrad. The main opening of NIR is pointed to the nadir direction (-Y). The auxiliary solar port of NIR and the only opening of MIR (Mid-Infrared) are pointed to the sun. The thermal infrared channel (TIRVIM) is equipped with a one-dimensional (1D) scanner/positioner rotating its FOV (Field of View) in the XY plane from +X to almost -X. It allows us to observe nadir, internal blackbodies, and the open space, which are necessary for absolute calibration of TIRVIM in the IR. TIRVIM has also a separate solar occultation port.


Figure 42: The concept design of ACS. Suite consists of four blocks: the NIR channel, the MIR channel, the TIRVIM channel, and the electronic block. The yellow blocks designate the instrument's radiators. The pointing directions of the ACS channels are shown (image credit: IKI)

The ACS block diagram is shown in Figure 43. The common BE (Electronic Block) serves as a single electrical interface of the ACS to the spacecraft in terms of power, commands, and data. The power interface includes the main power switch, power conditioning, and the specific switches for each scientific channel. The final power distribution is done in the channels using regulated voltage lines from the BE. The command and data interfaces to TGO are MIL1553 and SpaceWire, respectively. The fully redundant BE electronics feature an FPGA (Field-Programmable Gate Array) and include a 32 GB of flash memory. The control electronics units of each channel are redundant as well. The data and command interfaces between the BE and the scientific channels are of the type low-voltage differential signaling.




Figure 43: The ACS block diagram. The common electronic block (BE) serves as a single electrical interface of the ACS to the spacecraft in terms of power, commands, and data (image credit: IKI)

General measurement and interface parameters of ACS are summarized in Table 6. ACS consists of four blocks bolted together and sharing a single mechanical interface to the spacecraft. Roughly two-thirds of its mass allocation of 33.5 kg is dedicated to the larger channels, MIR and TIRVIM. The remaining mass is shared between the smaller NIR channel, the BE, the mechanical structure, and the thermal regulation system.

Following the spacecraft requirements, the ACS suite regulates its thermal characteristics, minimizing thermal flux to the spacecraft. The thermal control is provided by several radiators placed at the upper plane of TIRVIM and MIR channels, and a radiator at the right surface of IR (as in Figure 42; +X and -Z axes of the spacecraft, respectively), as well as by independent operational and survival thermal control systems. During the cruise/aerobraking phases of flight, the BE is off and the regulation of survival heaters is provided by dedicated subsystems.






Operation modes

Nadir (dayside and nightside), SO

SO (Solar Occultation)

Nadir (dayside and nightside), SO

Nadir, SO, limb

FOV (Field of View)

2º x 0.02º

10 x 0.5 arcmin

3º full solar disk in SO


Spectral range

0.73-1.6 µm

2.3-4.3 µm 7 photometers (TBC) 0.2-0.9 µm

2-17 µm, 1.7 µm nadir CH4

0.25–17 µm full
0.73–17 µm spectral

Instantaneous spectral range

50 x 100 cm-1
16 nm at 1.37 µm

7 x (0.28-0.32 µm) ex.
3.13-3.46 µm

Full range


Time to measure one spectrum

1 s nadir 50 ms SO

0.5-1 s

4 s nadir 10 s nadir CH4 2 s SO


No of spectra/measurement

≤ 10

1 or 2

1 or 2


Spectral resolution/resolving power

λ/Δλ ≥ 20,000

λ/Δλ ≥ 50,000

1.6 cm nadir
0.2 cm nadir CH4 0.2 cm
SO (λ/Δλ) ~15,000 at 3.3 μm


Mass (preliminary)

3.3 kg

12.2 kg

11.6 kg

33.5 kg

Power (preliminary)

15 W

30 W

28 W

39–85 W, survival 22 W


12 x 35 x 25 cm3

20 x 50 x 60 cm3

20 x 44 x 30 cm3

52 x 60 x 47 cm3

Data rate (preliminary)

0.1 Gbit/day

0.7 Gbit/day

0.7 Gbit/day

1.5 Gbit/day

Table 6: Measurement and interface parameters of the three scientific channels of ACS and the overall values for the whole instrument


Figure 44: Photograph of the prototype interferometer unit of TIRVIM (image credit: IKI)

• ACS-NIR is an Echelle AOTF (Acousto-Optic Tuneable Filter) spectrometer, which will operate in nadir, limb and solar occultation modes, detecting infrared light in the wavelength range from 0.7 µm - 1.7 µm. 60)

• ACS-MIR is an Echelle spectrometer, which will operate in solar occultation mode, covering the range from 2.3 µm - 4.6 µm.

• ACS-TIR is a Fourier spectrometer with two channels, one covering 1.7 µm - 17 µm that will operate in nadir and solar occultation modes, and another covering 1.7 µm - 4 µm (optimized for 3.3 µm) that will operate in nadir mode.


Figure 45: ACS accommodation on the TGO (image credit: ESA)


CaSSIS (Color and Stereo Surface Imaging System)

This high-resolution camera (5 m/pixel) will obtain color and stereo images of the surface covering a wide swath. It will provide the geological and dynamic context for sources of trace gases detected by NOMAD and ACS. PI: Nicolas Thomas, University of Bern, Switzerland. 61) 62)

CaSSIS will characterize sites that have been identified as potential sources of trace gases and investigate dynamic surface processes – for example, sublimation, erosional processes and volcanism – which may contribute to the atmospheric gas inventory. The instrument will also be used to certify potential landing sites by characterizing local slopes, rocks and other possible hazards.

By acquiring color and stereoscopic images of surface features, CaSSIS will allow scientists to investigate whether specific types of geological processes might be associated with trace gas sources and sinks. The NOMAD and ACS instruments, also being carried by the orbiter, will identify sources of trace gases that could be evidence for biological or geological activity. The CaSSIS imaging system will have a horizontal scale of about five meters per pixel; stereoscopic reconstruction will enable a vertical resolution of about six meters.

CaSSIS will be located on the Mars-surface-facing side of the orbiter. The orbiter science payload will be primarily nadir pointing to keep the Martian surface in constant view. The orbiter will rotate about an axis that will maintain its solar panels oriented towards the Sun while avoiding solar illumination of its thermal radiators. CaSSIS can compensate for the spacecraft's yaw rotation using a drive mechanism, but during nominal stereoscopic imaging the orbiter will pause its yaw-rotation to maximize the paired-image accuracy. The rotation mechanism will be able to turn the entire telescope system by 180º while its support structure remains fixed.


Figure 46: Principle of stereo image acquisition with CaSSIS (image credit: University of Bern)

This rotation system will also enable the camera to acquire stereo images with only one telescope and focal plane assembly. A stereo image pair will be acquired by first rotating the telescope to point 10º ahead of the spacecraft track to acquire the first image, then rotating it 180º to point 10º behind for the second stereo image. Optimal correlation of the stereo signals will be ensured as there will be identical illumination conditions every time a stereo image pair is acquired.

CaSSIS is a high-resolution camera system capable of acquiring color stereo images of surface features possibly associated with trace gas sources and sinks in order to better understand the range of processes that might be related to trace gas emission. The NOMAD and ACS instruments, also being carried by the orbiter, will identify sources of trace gases that could be evidence for biological or geological activity.


Figure 47: The CaSSIS instrument on a bench in the University of Bern laboratory in Nov. 2015. The electronics unit (left) controls the telescope (right). The black part of the instrument is the telescope structure. The main mirror can be seen in the center. The telescope is cantilevered off the gold colored support structure (image credit: University of Bern)

The camera consists of a three-mirror off-axis telescope with an additional slightly powered folding mirror, which will project an image onto the focal plane. The instrument electronics unit will be mounted separately on the spacecraft deck, next to the telescope. The imager will cover an eight-kilometer-wide swath of the planet's surface in four different wavelength ranges.

Telescope type

TMA (Three-Mirror Anastigmat)

Focal length, aperture, angular scale

880 mm, 135 mm diameter, 5 µrad/pixel

FOV (Field of View)

1.34º x 0.88º

Filter wavelengths (bandwidths)

Pan 650 nm (250 nm)
IR 950 nm (150 nm)
NIR 850 nm (120 nm)
Blue-Green 475 nm (150 nm)

Table 7: CaSSIS imaging characteristics


FREND (Fine Resolution Epithermal Neutron Detector)

This neutron detector will map hydrogen on the surface down to a meter deep, revealing deposits of water-ice near the surface. FREND's mapping of shallow subsurface water-ice will be up to 10 times better than existing measurements. PI: Igor Mitrofanov, Space Research Institute (IKI), Moscow, Russia. 63)

FREND is a neutron detector with a collimation module that significantly narrows the field of view of the instrument, thus allowing the creation of higher-resolution maps of hydrogen-abundant regions on Mars. FREND will measure the flux of neutrons from the Martian surface; these are produced by the continuous cosmic ray bombardment interacting with the first few meters of rock and regolith. The cosmic rays are sufficiently energetic to break apart atoms in the top 1-2 m of the planetary surface, releasing high-energy neutrons that are then slowed down and absorbed by the nuclei of elements in the surrounding material. Not all the neutrons are captured – many escape, creating a leakage flux of neutrons that the FREND instrument will observe. 64)

The distribution of neutron velocities, which depends upon how much they were slowed down before escaping, can reveal much about the surface material since it depends on the composition of that material – primarily on its hydrogen content. Even small quantities of hydrogen are known to cause a measurable change in the neutron velocity distribution from the surface of celestial bodies with thin or no atmospheres. This measured hydrogen content can be related to the presence of water.

Epithermal neutrons with energies in the 0.4 eV - 500 keV range will be detected by 3He counters, while neutrons with energies from 0.5 MeV - 10 MeV will be detected using a stylbene scintillator crystal.

FREND also contains a dosimeter module to monitor the local radiation environment. This helps to increase the accuracy of the neutron measurements by providing information about other radiation fluctuations (including space weather driven by the Sun) that can have an impact on the signals from the 3He and stylbene detectors.

FREND is designed to:

• perform high spatial resolution mapping of epithermal and fast neutron fluxes from the Martian surface

• monitor neutrons and charged particle fluxes over broad energy ranges during periods of quiet Sun and during solar particle events

• provide maps of hydrogen concentration in the Martian soil at high spatial resolution

• allow comparison of orbital and ground data as measured by FREND on TGO, the DAN (Dynamic Albedo of Neutrons) instrument on the MSL (Mars Science Laboratory), also known as Curiosity, and the Adron instrument on the ExoMars 2018 Rover

• search for temporal changes in neutron fluxes related to the seasonal Martian water cycle and galactic cosmic ray variations.

FREND builds on previous and current flight heritage, most notably the HEND (High Energy Neutron Detector) on Mars Odyssey; the LEND (Lunar Exploration Neutron Detector) on the LRO (Lunar Reconnaissance Orbiter); the Mercury Gamma and Neutron Spectrometer on BepiColombo; and DAN on MSL.

To map with high spatial resolution the fluxes of neutrons (epithermal, thermal, and fast ones) and, thereafter, hydrogen distribution, FREND is equipped with a set of four 3He detectors and one stilbene-based scintillation crystal. The 3He detectors are proportional counters filled with helium-3 under the pressure of 6 atmospheres and placed inside four openings of the collimator. Each of them counts neutrons independently, so that count statistics is higher (and, thus, maps are statistically more reliable) and instrument is more resistant to failures.

These detectors measure neutrons with energies from 0.4 to 500 keV. The scintillation counter, which uses a stilbene crystal, measures fast neutrons with energies 0.5–10 MeV. It is also placed inside the collimator. The scintillation module includes anti-coincidence shielding, to discriminate between signals from high-energy charged particles and neutrons.

FREND's collimation module is a passive element, encasing all five detectors. The collimator consists of two layers, the outer one made of high-density polyethylene, the inner one of enriched boron powder (B10). The neutrons, hitting the collimator's sides, are slowed down by polyethylene, with a large number of hydrogen atoms. So thermalized neutrons then pass through and get into the B10 layer, which absorbs them.

The collimator's opening angle narrows the FOV of the detectors to the spot with diameter of 40 km on the Martian surface, when seen from the circular orbit with 400 km altitude, allocated for TGO. Thus, the spatial resolution of the neutron maps of Mars will be enhanced 7.5 times compared to the maps of the HEND instrument.


Figure 48: General view of the FREND instrument (image credit: IKI)

The FREND instrument consists of electronics and dosimetry modules (located separately, in the upper part of Figure 48), collimator module (several composite sections), which shield the detectors from radiation coming from outside the nadir direction, and five detectors (not seen in the figure).


Figure 49: Illustration of the instrument's profile and inner architecture of the collimator and detectors (image credit: IKI)

Mass, power consumption, size

36 kg, 14 W, 465 x 380 x 370 mm

Energy range

0.4–500 keV (neutrons); 0.5–10 MeV (charged particles)

Time resolution

from 1 second

Surface resolution, depth resolution

~40 m, ~ 1 m

Telemetry rate

50 Mbit/day

Table 8: Main parameters of FREND


NOMAD (Nadir and Occultation for Mars Discovery)

NOMAD combines three spectrometers, two infrared and one ultraviolet, to perform high-sensitivity orbital identification of atmospheric components, including methane and many other species, via both solar occultation and direct reflected-light nadir observations. PI: Ann Carine Vandaele, BIRA-IASB (Belgian Institute for Space Aeronomy), Brussels, Belgium. The countries contributing to NOMAD are: Spain, Italy ,United Kingdom, United States of America, Canada. The NOMAD infrared channels were built upon the expertise of BIRA-IASB's successful SOIR (Solar Occultation in the Infra-Red) instrument which is on-board ESA's VEX (Venus Express) mission.

The NOMAD spectrometer suite on the ExoMars Trace Gas Orbiter will map the composition and distribution of Mars' atmospheric trace species in unprecedented detail, fulfilling many of the scientific objectives of the joint ESA-Roscosmos ExoMars Trace Gas Orbiter mission. 65)

NOMAD is a spectrometer suite that can measure the spectrum of sunlight across a wide range of wavelengths (infrared, ultraviolet and visible). This broad coverage of the instrument enables the detection of the components of the Martian atmosphere, even in low concentrations. In addition to identifying the constituents of the Martian atmosphere, NOMAD will also map their locations. 66) 67) 68) 69)

The measurements will be carried out in solar occultation, i.e. the instrument points toward the Sun when the Orbiter moves at the dark side of Mars, as well as in nadir mode, i.e. looking directly at the sunlight reflected from the surface and atmosphere of Mars. The inclination of the Orbiter has been chosen to optimize the science that can be done with the instrument suite.


Figure 50: Illustration of the NOMAD instrument (image credit: BIRA)

NOMAD covers the infrared (2.2-4.3 µm) and the ultraviolet-visible (0.2-0.65 µm) spectral regions, using the following three operational modes:

SO (Solar Occultation) mode: The SO operates by observing up to six small slices of the full spectral range each second. This allows observing several different target molecules that absorb at different wavelengths, whilst maximizing the SNR (Signal-to-Noise Ratio) for each. During a solar occultation, which lasts about 5 minutes, 300 spectra at each wavelength can be taken providing a profile of the atmospheric composition from the top of the atmosphere down to almost the surface, depending on dust levels.

LNO (Limb, Nadir and Occultation) mode: The LNO is sensitive to the lower light levels during nadir observations on Mars. The nadir coverage will facilitate the study of the atmospheric composition in addition to examining Martian surface features, such as ice and frost. This measurement will be carried out on average every 3 to 4 sols (a solar day on Mars, or sol, is 24 hours and 39 minutes) with varying local times across the planet.

UVIS (Ultraviolet and Visible) mode: The UVIS will image the wavelength domain between 200 and 650 nm, every second, covering and providing more information about several interesting molecules, such as ozone, sulphuric acid and aerosols in the atmosphere.

The SO spectrometer channel will perform occultation measurements, operating between 2.2 and 4.3 µm at a resolution of ~0.15 cm-1, with 180 to 1000 m vertical spatial sampling. LNO will perform limb scanning, nadir and occultation measurements, operating between 2.2 and 3.8 µm at a resolution of ~0.3 cm-1. In nadir, global coverage will extend between ± 74º latitude with an IFOV (Instantaneous Field of View) of 0.5 x 17 km on the surface. This channel can also make occultation measurements should the SO channel fail. UVIS will make limb, nadir and occultation measurements between 200 and 650 nm, at a resolution of 1.5 nm. It will achieve 300 m vertical sampling with a 1 km vertical resolution during occultation and 5 x 60 km ground resolution during 15 s nadir observations (IFOV of 5 x 5 km).

An order-of-magnitude increase in spectral resolution over previous instruments will allow NOMAD to map previously unresolvable gas species, such as important trace gases and isotopes. CO, CO2, H2O, C2H2, C2H4, C2H6, H2CO, CH4 SO2, H2S, HCl, O3 and several isotopologues of methane and water will be detectable, providing crucial measurements of the Martian D/H ratios. It will also be possible to map the sources and sinks of these gases, such as regions of surface volcanism/outgassing and atmospheric production, over the course of an entire Martian year, to further constrain atmospheric dynamics and climatology. NOMAD will also continue to monitor the Martian water, carbon, ozone and dust cycles, extending existing data sets made by successive space missions in the past decades, from which surface UV radiation levels will be determined. Using SO and LNO in combination with UVIS, aerosol properties such as optical depth, composition and size distribution can be derived for atmospheric particles and for distinguishing dust from ice aerosols, as demonstrated on Venus by the analysis of the SPICAV-UV, IR and SOIR data.

Wavelength λ, Wavenumber

2.3-4.3 µm, 4250–2320 cm-1

Instrument line profile (ILP), ILP for CH4

0.22 cm-1, 0.15 cm-1

Pixel sampling FWHM (Full Width Half Maximum)



linear, parallel to slit

Resolving power λ/Δλ


Slit width in object space, Slit length in object space

2 arcmin, 30 arcmin

FOV (Field of View)

2 x 30 arcmin

Spatial sampling, vertical sampling

1 arcmin, ≤1 km



Mass ((including all NOMAD electronics)

13.5 kg

Dimensions (without periscope)

490.5 x 353 x 208 mm3

Table 9: Summary of SO channel specifications


Wavelength λ, Wavenumber

2.3-3.8 µm, 4250–2630 cm-1

Instrument line profile (ILP)

0.5 cm-1

Pixel sampling FWHM (Full Width Half Maximum)



linear, parallel to slit

Resolving power λ/Δλ


Slit width in object space, Slit length in object space

4 arcmin, 150 arcmin

FOV (Field of View)

4 x 150 arcmin

Spatial sampling

1 arcmin

Entrance aperture diameter

29.5 x 24 mm2


9.4 kg

Dimensions (without periscope)

445 x 327 x 182 mm3

SO (Solar Occultation)

Vertical sampling, SNR

≤1 km, ≥900

Nadir footprint (400 km orbit)

60 x 0.3 arcmin2

SNR, SNR for CH4

≥400, ≥1000

Table 10: Summary of LNO channel specifications


SO (Solar Occultation)

Nadir Observation

Volume, mass

128 mm x 152 mm x 89 mm, 950 g

Spectral range, spectral resolution

200-650 nm, 1.5 nm

Numerical aperture of the fiber






2 arcmin, 1 km

43 arcmin, 5 km x 5 km

Typical observation binning, observation time

8 rows, 0.2 s

64 rows, 15 s

Footprint of nadir channel during a typical 15 s observation


60 km x 5 km

Vertical sampling

< 300 m (Δz at limb)


SNR (specification requirement)

230-450 nm: SNR≥1000
450-650 nm: SNR≥500

230-450 nm: SNR≥500
450-650 nm: SNR≥250

Detector e2V back-thinned CCD30-11
Pixel pitch
Dark current at 293 K
Dark signal non uniformity on binned column of 256 pixels at 293 K
Read-out noise
Detector full well capacity (at 293 K)

2D 1024 x 256 pixel CCD
26 µm
1000 e-/pixel/s
30 e-/pixel/s
6 e-/pixel
540 000 e-

Table 11: NOMAD-UVIS characteristics and performances

The mass of NOMAD is 28.86 kg including margins. From this, the SO and LNO optical bench masses are 13.35 kg (including all NOMAD electronics) respective 9.4 kg. The remaining mass is attributed to UVIS (940 g) and harnessing, MLI (Multilayer Insulation), and instrument-to-spacecraft mounting hardware (3.7 kg).



Sensor complement of Schiaparelli (DREAMS, AMELIA, COMARS+, INRRI, DECA)

Science investigations to be carried on Schiaparelli, the ExoMars entry, descent and landing demonstration module (EDM), were selected in June 2011 following an announcement of opportunity released by ESA and NASA. 70)

The selected investigations consist of a surface payload, called DREAMS, which will operate on the surface of Mars for 2–8 sols, and an investigation known as AMELIA, for entry and descent science investigations using the spacecraft engineering sensors.


Figure 51: Artist's rendition of the Schiaparelli EDM without heat shield and back cover (image credit: ESA, ATG medialab) 71)


DREAMS (Dust Characterization, Risk Assessment, and Environment Analyzer on the Martian Surface)

The surface payload, consisting of a suite of sensors to measure local wind speed and direction (MetWind), humidity (DREAMS-H), pressure (DREAMS-P), atmospheric temperature close to the surface (MarsTem), transparency of the atmosphere (Solar Irradiance Sensor, SIS), and atmospheric electric fields (Atmospheric Radiation and Electricity Sensor, MicroARES). PI: Francesca Esposito, INAF – Osservatorio Astronomico di Capodimonte, Naples, Italy; Co-PI: Stefano Debei, CISAS –Università di Padova, Italy.

DREAMS will provide the first measurements of electric fields on the surface of Mars (with MicroARES). Combined with measurements (from SIS) of the concentration of atmospheric dust, DREAMS will provide new insights into the role of electric forces on dust lifting, the mechanism that initiates dust storms.


Figure 52: Artist's rendition of DREAMS (image credit: ESA, ATG medialab) 72)


AMELIA (Atmospheric Mars Entry and Landing Investigation and Analysis)

The objective of AMELIA is to collect entry and descent science data using the spacecraft engineering sensors. PI: Francesca Ferri, Università degli Studi di Padova, Italy. The engineering data is used to reconstruct Schipiarelli's trajectory and determine atmospheric conditions, such as density and wind, from a high altitude to the surface. These measurements are key to improving models of the Martian atmosphere.


COMARS+ (Combined Aerothermal and Radiometer Sensors instrumentation package)

The objective of COMARS+ is to measure aerothermal parameters on the exterior of Schiaparelli as it passes through the atmosphere. Team leader: Ali Gülhan, DLR, Cologne, Germany. Determining what happens to Schiaparelli's external surface as it penetrates the Martian atmosphere and descends to the surface is essential in order to understand the engineering and physics required to make entry, descent, and landing on Mars a success. COMARS+, which is installed on the back cover of Schiaparelli will gather the data to study this.

COMARS+ consists of three combined sensors (COMARS) spaced equally across the back cover of Schiaparelli, one broadband radiometer, and an electronic box (inside the module). The entire package has a mass of 1.73 kg and draws 4.5 W of power. The sensors, located on the back cover of the module, will measure the pressure, the temperature of the module's surface, the rate at which heat energy is transferred to the surface (total heat flux rate), and the amount of radiated heat from the hot gas to the back cover (radiative heat flux).


Figure 53: COMARS+ sensors on Schiaparelli (image credit: DLR) 73)

Two so-called ICOTOM narrow band radiometers in each COMARS sensor are provided by CNES. In addition, a broadband radiometer provided by DLR is integrated close to the COMARS 3 sensor. The data produced from this instrument package will provide essential input for the improved design of future missions landing on Mars. The COMARS+ package is provided by the German Aerospace Center (DLR).


INRRI (INstrument for landing-Roving laser Retroreflector Investigations)

The INRRI instrument is developed by ASI together with INFN (Italian National Institute for Nuclear Physics). Team leader: Simone Dell'Agnello, INFN/LNF National Laboratories of Frascati), Frascati, Italy. INRRI will be the first passive laser reflector on the surface of Mars and the first to go further than the Moon. 74)

INRRI for Mars Rovers is a new enabling technology for planetary exploration because: it will provide accurate Rover georeferencing during its exploration activity, recording its positions where significant geological measurements have been made by Rover instruments as reference for future exploratory missions. Example of the latter: future sample return mission targeting an INRRI-georeferenced position explored/surveyed by the Rover of particularly high interest to NASA/ESA/ASI long-term goals for Mars exploration (outstanding astrobiologically relevant sites, potential biosignature locations). 75)

INRRI is a laser retroreflector micropayload of about 50 gr weight and about 55 mm x 20 mm size. It will be laser tracked by Mars orbiters capable of laser ranging and/or laser altimetry, like for example LOLA (Lunar Orbiter Laser Altimeter) on LRO (Lunar Reconnaissance Orbiter) and/or laser communication, like for example LLCD (Lunar Laser Comm demo) on LADEE (Lunar Atmosphere and Dust Environment Explorer), or OPALS (Optical PAyload for Lasercomm Science) on the ISS.


Figure 54: Drawing and photo of INRRI (Instruments for landing/Roving laser Retroreflector Investigations), image credit: INFN/LNF

INRRI for Mars Rovers is a new, wavelength-independent, enabling technology to test, validate, and locally diagnose, on Mars, certain aspects related to transmitter and receiver subsystems for future laser-communication from Mars orbiters to Earth, an activity that is a long-term interest for future Mars missions. This will be also applied to future laser-comm between Mars orbiters and Mars surface (future Rovers and distributed installations).


DECA (Descent Camera)

Will record several images during descent, but will not be able to take any images of the surface after landing. Team leader: Detlef Koschny, ESA Science Support Office. 76)

DECA is the flight spare of the VMC (Visual Monitoring Camera), which flew on the Herschel spacecraft. It will be used to perform high-resolution imaging of the Schiaparelli landing site, to determine the transparency of the martian atmosphere, and to support the generation of a 3-D topography model of the surface of the landing region.

DECA was designed and built by OIP (Optique et Instruments de Précision) in Belgium for ESA.The camera has a mass of 0.6 kg and dimensions of about 9 cm x 9 cm x 9 cm.


Figure 55: Photo of DECA (Descent Camera) on Schiaparelli (image credit: ESA)

DECA will start taking images after the front-shield of Schiaparelli has been jettisoned during the journey through the martian atmosphere to the planet's surface. It will take 15 images at 1.5 s intervals. These images will be stored in local memory. To avoid electrostatic discharges affecting the instrument, there will be a delay of several minutes after Schiaparelli has landed on the surface of Mars, before the data are read out by Schiaparelli's computer and subsequently downlinked to Earth.



Arriving at Mars

Although designed to demonstrate entry, descent and landing technologies, Schiaparelli also offers limited, but useful, science capabilities. It will deliver a science package that will operate on the surface of Mars for a short duration after landing, planned to last approximately 2-4 sols (martian days). 77)

• Three days before reaching the atmosphere of Mars, Schiaparelli will separate from the Orbiter.

• The module will then coast to Mars during which phase it will remain in hibernation mode in order to reduce its power consumption.

• Schiaparelli will be activated a few hours before entering the atmosphere of Mars, at an altitude of 122.5 km and a speed of approximately 21,000 km/h.


Figure 56: Artist's rendition showing the Schiaparelli Rover release from the TGO (Trace Gas Orbiter) for a landing on the surface of Mars (image credit: ESA)


Figure 57: Schiaparelli descent sequence (image credit: ESA, ATG medialab)

• Entry: An aerodynamic heatshield will protect Schiaparelli from the severe heat flux and deceleration, so that at an altitude of about 11 km, when the parachute is deployed, it will be travelling at around 1650 km/h.

• Descent: The module will first release the front heatshield and then the rear heatshield will also be jettisoned.

- Schiaparelli will turn on its Doppler radar altimeter and velocimeter to locate its position with respect to the Martian surface.

• Landing: The liquid propulsion system will be activated to reduce the speed to less than 7 km/h when it is 2m above the ground. At that moment the engines will the switched off and the lander will drop to the ground.

- As Schiaparelli lands, the final shock will be cushioned by a crushable structure built into module.

- The primary landing site has been identified: it is a plain known as Meridiani Planum, a plain located 2 degrees south of Mars' equator in the westernmost portion of Terra Meridiani. This area interests scientists because it contains an ancient layer of hematite, an iron oxide that, on Earth, almost always forms in an environment containing liquid water.

A communication link between Schiaparelli and the TGO (Trace Gas Orbiter) will facilitate the realtime transmission of the most important data measured by the module. The complete set of data acquired will be transmitted to the Orbiter within 8 sols after the landing (a solar day on Mars, or sol, is 24 hours and 37 minutes). The Schiaparelli mission then comes to an end.


Figure 58: Illustration of Schiaparelli's landing site, acquired by the Mars Reconnaissance Orbiter (image credit: NASA/JPL, Arizona State University, ESA, Ref. 6)


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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 (

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