Minimize ISARA

ISARA (Integrated Solar Array and Reflectarray Antenna)

Spacecraft    Launch    Experiment Complement   References

ISARA is a NASA/JPL (Jet Propulsion Laboratory) nanosatellite (3U CubeSat) demonstration mission with the goal to demonstrate a Ka-band reflectarray antenna that will increase the downlink data rates for small spacecraft from the typical existing rates from a baseline of 9.6 kbit/s to over 100 Mbit/s, a hundredfold increase in data capacity. For a modest increase in mass, volume, and cost, the high data rate this technology enables will pave the way for high value science missions and formation flying missions that utilize distributed CubeSats and small satellites. 1)

ISARA is a JPL PM-led mission that will be carried out in close collaboration with Pumpkin, Inc. and Aerospace Corp. In February 2013, ISARA was down-selected for a launch opportunity through the NASA ELaNa program.

The ISARA mission is funded through NASA's SSTP (Small Spacecraft Technology Program), a program within the new Space Technology Mission Directorate which was formed as a catalyst for the creation of technologies and innovation needed to maintain NASA leadership in space, while also benefiting America's economy. The SSTP was created specifically to develop and demonstrate new technologies and capabilities for small spacecraft.

ISARA Rideshare Opportunity:

In 2014, The Aerospace Corporation proposed an idea for a secondary payload to fill approximately 1U of unused volume on the ISARA spacecraft. The primary ISARA mission required a 3U bus to accommodate the reflectarray antennae/solar panel structure, but used less than 2U of spacecraft volume. To fill the remaining volume, a combination of two readily available compact uncooled IR cameras was chosen, and a visible camera similar to those flown on prior AeroCube missions, but with greater low-light sensitivity. The Space and Missile System Center's Advanced Development program office (SMC/AD) was interested in gaining experience with flying COTS camera hardware and funded the secondary payload effort. 2)

The sensor capabilities matched specific nighttime remote sensing science goals of The Aerospace Corporation's Space Science Applications Laboratory, including exploring the utility of the near infrared for nighttime cloud detection and combining cloud and nightlight sensors on a single payload. 3)

Payload development was greatly speeded by use of the 5-camera controller card technology for the OCSD/AC-7 satellite. Some added software was necessary for this card to control the new cameras. Power conditioning boards were also necessary for the IR cameras. As mentioned above, two camera cards were necessary, as the main payload had two star sensors, a nadir-pointed fisheye camera, and a reflectarray deployment fisheye camera. Redundant boards also ensured there was less risk to the main reflectarray experiment. The new imaging instruments were as isolated as possible from the primary experiment.



ISARA is a 3U bus to host two payloads, namely the ISARA (Integrated Solar Array and ReflectArray) antenna as primary payload and the CUMULOS (CubeSat Multispectral Observation System), an experimental remote sensing payload of The Aerospace Corporation.

A nominal five month Space Flight Demonstration will be used to confirm a 100 Mbit/s data rate and verify antenna performance to TRL 7 (Technology Readiness Level 7). The spacecraft is a 3U CubeSat carrying a Ka-band payload that includes a low power transmitter, HGA (High Gain Antenna), standard gain reference antenna and RF antenna select switch. A Ka-band ground station will verify high data rate by SNR (Signal-to-Noise) measurement and measure the antenna performance. The HGA gain will be measured by switching between the HGA and an on-board SGA (Standard Gain Antenna), while the spacecraft will be slewed on orbit to measure the antenna patterns. The on-orbit data will be compared to measurements that were taken prior to launch.


Figure 1: ISARA spacecraft configuration with 3U CubeSat and Solar Array with Integrated Reflectarray Antenna (image credit: NASA/JPL)

The reflectarray antenna consists of three panels, electrically tied together through hinges, which have an array of printed circuit board patches on them. The size of the patches are adjusted so that the phase of the reflected feed illumination collimates the radiation in much the same way a parabolic dish reflector would. Unlike a parabolic dish, however, the reflectarray panels are flat, which enables them to be folded down against the CubeSat. On the opposite side of the printed reflectarray antenna, solar cells have been added. This makes the overall antenna/solar array panel assembly slightly thicker, but the cells are stowed in the "dead space" between the launch rails that would have otherwise been left empty. This combination of antenna and solar cells makes for a very efficient use of CubeSat volume, leaving plenty of room for payloads such as science instruments or imaging systems. 4)

The ISARA technology will be validated in space during the mission to measure key reflectarray antenna characteristics, which include how much power can actually be obtained over its field of view. ISARA contains a transmitter and an avionics subsystem that features a GPS (Global Positioning System) receiver and a high precision attitude control system designed to orient the CubeSat to enable accurate antenna beam pointing. Once in orbit, ISARA will deploy its solar array and reflectarray antenna. It then will use its attitude determination and control system to stabilize itself. An ultra high frequency (UHF) communications system will be used to make initial contact with the satellite and perform in-orbit checkout procedures.

During the in-orbit test, ISARA's reflectarray antenna will transmit a signal that will be received by a ground station located at NASA/JPL ( Jet Propulsion Laboratory) in Pasadena, California. The spacecraft's location and orientation telemetry data will be analyzed to reconstruct the antenna signal pattern, which will then be compared against pre-flight ground measurements.

ISARA contains a transmitter and an avionics subsystem that features a high precision ADCS (Attitude Determination and Control Subsystem) along with a suite of ADCS sensors and actuators. A high accuracy MAI-400 ADCS is used to achieve the required 0.2° pointing accuracy. The standard bus avionics that are essentially identical to the OCSD (Optical Communication and Sensor Demonstration) 3U CubeSat,include a primary flight computer, two UHF radios and a GPS receiver for navigation. ISARA has a mass of ~5 kg.


Figure 2: ISARA avionics stack (image credit: NASA/JPL, The Aerospace Corporation)



Figure 3: ISARA 3U spacecraft showing the primary reflectarray and the secondary remote sensing payloads (image credit: The Aerospace Corporation, NASA/JPL)

The stowage volume and spacecraft power provided by the ISARA technology also enabled the ISARA mission to carry a secondary payload known as CUMULOS (CubeSat Multispectral Observation System), an experimental Aerospace Corporation remote sensing payload. CUMULOS is composed of a 0.4-0.8 µm visible camera, a 0.9-1.7 µm short-wavelength infrared camera, and an 8.0-13.5 µm long-wavelength infrared, microbolometer camera.

The CUMULOS sensors provide a small-aperture, large field-of-view, remote sensing payload suitable for testing the performance of passively-cooled commercial sensors for weather and environmental monitoring missions. CUMULOS is designed for point-and-stare imaging and will allow almost simultaneous 3-band coverage of regions 230 x 180 km in size, at ground sample distances from 180 to 600 m from an orbital altitude of 600 km. Remote sensing applications to be investigated include: cloud cover detection, surface temperature measurement, hotspot detection (including fires, gas flares, and volcanic activity), and detection of nighttime lights.

At the end of the validation mission, the reflectarray antenna technology will be available for use on other missions that need high bandwidth telecommunications. The ISARA technology will enable CubeSats and other small satellites to serve as viable platforms for performing missions that were previously only possible on larger and more costly satellites. For a modest increase in mass, volume and cost, the high data rate this technology enables will pave the way for high value science missions and formation flying missions that use distributed CubeSats and small satellites.


Launch: The ISARA mission was launched on November 12, 2017 on the Cygnus Orbital ATK CRS OA-8 Mission to the ISS on the upgraded Orbital ATK Antares 230 vehicle. The launch site was MARS (Mid-Atlantic Regional Spaceport) at NASA's Wallops Flight Facility in Virginia. 5) 6)

Orbit : Near-circular orbit, altitude of ~400 km to ISS, inclination =51.6°.

For the OA-8 mission, Orbital ATK is using the Enhanced Cygnus PCM (Pressurized Cargo Module) to deliver cargo to the space station. The cargo capability of the Enhanced Cygnus, developed by Thales Alenia Space, is more than 3500 kg with a total volumetric capacity of 27 m3 (the ascent cargo mass is 3,350 kg). The supply shipment includes:

- 1240 kg of crew supplies. Fresh fruit and vegetables are among the goodies riding inside a refrigerator on Cygnus spacecraft.

- 740 kg of science investigations

- 132 kg of spacewalk equipment

- 851 kg of vehicle hardware

- 34 kg of computer resources

The Orbital ATK CRS-8 (OA-8) launch carried another historic NanoRacks mission to the ISS. With a completely full ENRCSD (External NanoRacks Cygnus Deployer), a virtual reality camera, and educational research, this mission marks over 600 NanoRacks payloads delivered to the ISS since 2009. 7)

This mission is enabling a unique virtual reality opportunity with National Geographic's VUZE camera. Integrated and launched via NanoRacks, VUZE will allow for the recording of the new National Geographic series "One Strange Rock," in which the astronaut crew will record a series of virtual reality pieces for incorporation into a larger documentary about natural history and the solar system. This is National Geographic's first time launching with NanoRacks.

Additionally, OA-8 is the fourth mission in which NanoRacks is providing opportunities for CubeSat deployment from Cygnus after the vehicle departs from the station. The NanoRacks ENRCSD is installed on the exterior of the Cygnus service module with the capability to deploy satellites after Cygnus' completion of its primary ISS resupply mission.

On this ENRCSD mission, NanoRacks has 14 satellites ready to be deployed with customers including the NRO Office of Space Launch, Asgardia, Spire, Tyvak, NASA/JPL, and NRL (Naval Research Laboratory) in Washington, D.C. Included in this External Cygnus manifest are also The Aerospace Corporation's AeroCube B/C satellites, water-based propulsion CubeSats.

The External Cygnus Deployment Program was developed with the customer in mind. The lifespan of CubeSat deployed from the Cygnus vehicle at 500 km adds approximately two-years additional lifetime compared to our ISS NRCSD deployment program.

Cygnus carried the following CubeSats:

• ISARA, a NASA/JPL 3U CubeSat demonstration mission of a Ka-band reflect array antenna.

• EcAMSat (E. coli AntiMicrobial Satellite), a 6U CubeSat of NASA/ARC to investigate space microgravity effects on the antibiotic resistance of E. coli.

• Lemur-2 x 3, a 3U CubeSat of Spire Global (global ship tracking).

• CHEFsat (Cost-effective High E-Frequency Satellite), a 3U CubeSat of NRL (Naval Research Laboratory) to test COTS technologies.

• Asgardia-1, a 2U CubeSat of Asgardia Space to demonstrate long-term data storage in orbit (500 GB). After leaving the ISS, the robotic Cygnus will boost itself into a 500 km orbit and deploy Asgardia-1.

• OSCD x 2 (Optical Communication and Sensor Demonstration), a 1.5U CubeSat of The Aerospace Corporation.

• PropCube-2 (Fauna), a 1U CubeSat of NPS (Naval Postgraduate School) for ionospheric calibration measurements.

• TechEdSat-6, a 3U CubeSat, developed by students of SJSU (San Jose State University), the University of Idaho, and NASA/ARC (Ames Research Center). TechEdSat 6 is the latest in a series of CubeSats testing an "exo-brake" deorbit system, a drag device that uses aerodynamic forces — and not propulsion — to re-enter the atmosphere. The technology could eventually allow some space station research samples to return to Earth sooner, and at less expense.

Cygnus arrived at the station on November 14. Expedition 53 Flight Engineers Paolo Nespoli of ESA and Randy Bresnik of NASA used the space station's robotic arm, SSRMS (Space Station Remote Manipulator System), to capture Cygnus. The crew then handed robotics off to controllers on the ground for the berthing operation. Eventually, Cygnus OA-8 was berthed to Node-1 (Unity, Figure 4). 8) 9)

Two newly arrived CubeSats will be transferred inside the space station to join three others for release into orbit through the Japanese lab module's airlock. These are: EcAMSat and TechEdSat-6.

Cygnus will remain at the space station until December 4, when the spacecraft will depart the station and deploy several CubeSats, among them ISARA, Lemur, CHEFSat, Asgardia-1, OCSD and ProCube-2 into a higher orbit of ~500 km. — After these deployments, the Cygnus spacecraft will reenter into Earth's atmosphere and disintegrate over the South Pacific Ocean, as it disposes of several tons of ISS trash.


Figure 4: Nov. 14, 2017: International Space Station Configuration. Five spaceships are parked at the space station including the Orbital ATK Cygnus-8, the Progress 67 and 68 resupply ships and the Soyuz MS-05 and MS-06 crew ships (image credit: NASA, Ref. 9)



Experiment complement: (ISARA, CUMULOS)

ISARA (Integrated Solar Array and Reflectarray Antenna)

ISARA (the payload name is the same as the mission name) is a new type technology providing a very significant reduction in stowed volume. For modest antenna sizes (~30-35 dB gain), the panels can be stowed entirely within the "dead space" between the bus and the launch canister (e.g. P-POD), so the antenna does not consume any payload volume. These antennas are mechanically simple, depending on a simple spring loaded hinge deployment mechanism, have relatively low mass density, and are expected to have low production cost. Perhaps the biggest limitation of the ISARA is scalability. Current technology limits the size to ~3-6 panels due to two factors: (1) tolerance accumulation of multiple hinged panels limits the size of a practical ISARA, and (2) there is a practical limit to how thin one can make a panel and still meet the flatness requirements, so stacking a large number of panels will consume CubeSat payload volume. Nonetheless, the inherent advantages of the ISARA make this a very useful CubeSat HGA technology for many applications. 10)


Figure 5: ISARA reflectarray antenna optics design (image credit: NASA/JPL)

The ISARA design is particularly unique because it incorporates 24 solar cells on the side of the panels opposite the reflectarray, so it can provide both prime spacecraft power and a high speed datalink. The ISARA design is comprised of three 33.9 cm x 8. 26 cm reflectarray panels designed to achieve 33.5 dB of gain at 26 GHz. As illustrated in Figure 5, the feed is mounted on the bus in an offset configuration with a projected aperture of 33 cm x 27 cm. The reflectarray panels are canted 14º relative to the bus so that the specular direction of the main beam is parallel to the bus axis.


Figure 6: ISARA CAD model and photographs of components (image credit: NASA/JPL)

Figure 6 shows a CAD model of the flight configuration along with photographs of the panels, feed and hinges. The deployment mechanism was adapted from the standard Pumpkin Inc. "Turkey Tail" 3U solar panel design. It is planned to make this a commercially available antenna design.

The requirement to maintain panel flatness with expected heating from the solar cells, Earth albedo, etc. drove the design process. Development of a substrate that provides the stiffness to keep the panels flat with the solar cells attached is challenging due the the CTE (Coefficient of Thermal Expansion) mismatch between the solar cells and the panel substrate material. A unique sandwich substrate material was developed using a co-cure process in which 48 mil graphite composite structural core is sandwiched between a pair of 15 mil Teflon based dielectric circuit boards. The outer circuit boards have a dielectric constant of 3.00 and low loss tangent (tan δ ~ 0.001), which is suitable for high efficiency reflectarray panels.

The electrical design of the reflectarray uses square patches arranged on a square grid with an element spacing of 0.46 wavelengths. The feed is a 4 x 4 element microstrip patch array designed to create approximately -10 dB edge taper in order to minimize spillover loss and minimize power incident on the bus. Circular polarization is formed by the feed patch design, whereas the reflectarray is a dual linearly polarized design.

Figure 7 shows the measured principal plane radiation patterns along with the calculated patterns obtained for the EM design. The -13 dB azimuth pattern sidelobes are caused by the large 1.1 cm gaps between the center panel and the two winglet panels, a result of the hinge design used to accommodate the 3U CubeSat bus. Preliminary measurements indicate that the flight antenna will achieve a >33.0 dB gain. The feed design presents one of the greatest challenges for this antenna. The circular polarization requirement imposes practical constraints on the feed array spacing which makes it difficult to achieve an optimal edge taper. In this design, the spillover + taper loss is ~ 2.0 dB. In addition, the requirement to package the feed into a thin, inexpensive printed circuit board package resulted in about 1.4 dB feed loss. Overall antenna bandwidth easily exceeds the required value of 100 MHz.


Figure 7: Measured ISARA EM (Engineering Model) antenna pattern at 26 GHz (image credit: NASA/JPL)

In summary, the ISARA antenna has a great practical value for 3U-6U class CubeSats that need a modest size HGA. The advantages of extremely low stowed volume, low production cost and a low mass perfectly match the CubeSat concept. The ISARA design demonstrates the viability of this concept, although it appears that some improvement in efficiency is possible, particularly in the feed. Nevertheless, the ISARA antenna design scalability is limited by the mechanical restrictions of panel flatness and hinge tolerance accumulation, so the technology is complementary with PRAs (Parabolic Reflector Antennas). Finally, for some missions the option to add solar cells to the reflectarray panel could be very useful.


ISARA operations:

After deployment from the spacecraft, ISARA will deploy its solar array/reflectarray antenna and use the ADCS to de-tumble and stabilize. The UHF system will be used to establish initial communications with the satellite and perform on-orbit checkout procedures. Once the nanosatellite health has been established, on-orbit testing of the Ka-band system can begin.

The Ka-band experiments will include the determination of three elements: data rate capability, antenna gain, and antenna pattern. In order to verify the data rate capability, the received signal will be measured and compared against the estimated receiver noise. The antenna gain will be measured by transmitting a signal and switching between the HGA and the standard gain antenna. Characterizing the antenna pattern involves a multi-pass operations procedure.


CUMULOS (CubeSat Multispectral Observation System)

CUMULOS is a is a secondary payload on the 3U CubeSat hosting the primary NASA/JPL ISARA mission. The CUMULOS payload was integrated on a noninterference basis and care was taken to ensure low risk to the primary payload mission. CUMULOS will research optimal methods for the operation of passively cooled COTS sensors and cameras and determine their suitability to perform weather and environmental monitoring missions (Ref. 2).

CUMULOS may be thought of as a miniature weather satellite with a special focus on lowlight studies. A primary engineering research goal is to study the use and performance of commercially available uncooled infrared (IR) cameras in space.

Three separate cameras comprise the CUMULOS payload: 1) a visible (VIS) CMOS camera, 2) a SWIR, InGaAs camera, and 3) a longwave infrared (LWIR), vanadium oxide microbolometer. The VIS camera uses an Aptina MT9M001C12STM CMOS chip mated to a ruggedized Schneider Xenoplan lens. The SWIR camera is a FLIR Tau SWIR 25 equipped with a vented lens from Stingray Optics. The LWIR camera is a FLIR Tau 640 using the vendor's lens choice. The visible and LWIR cameras are passively cooled. The SWIR focal plane is temperature stabilized using an internal TEC (Thermo-Electric Cooler).

The cameras underwent TVAC (Thermal Vacuum) and vibration testing independently, and with the integrated ISARA payload. Basic calibration tests such as darks, flat fields, linearity and MTF (Modulation Transfer Function) measurements were performed. 11)

Together, the sensors will be used as a small-aperture, staring payload suitable for testing the performance of passively cooled sensors to perform spaceborne weather and environmental monitoring missions. The sensor specifications are shown in Table 1. The host spacecraft was originally scheduled to be placed in 575 km circular, 97.7° inclination, sun-synchronous orbit with a 10:30 am equatorial crossing time by a Falcon 9 launch vehicle. - Late breaking decisions may enable an earlier launch on the OA-8 ISS resupply flight during Fall, 2017. In this option, after a 6-week dock, the upper stage would then place the host spacecraft into a 500 km circular orbit with 52° inclination. The orbit-dependent terms in Table 1 and Figure 5 will change a bit as a result.

Sensor parameters




Lens f number




Lens focal length (mm)




Pixel pitch (µm)




Spectral band (µm)




Data quantization (bit)




Integration time (ms)



not appl. 10 ms time constant, 30 Hz max

Sensor vendor (Type)

Aptima (Si CMOS)


FLIR VOx (microbolometer)

Array size

1280 x 1024

640 x 512

640 x 512

Nominal altitude

500 km


~150 m

~500 m

~320 m

Repeat cycle




Table 1: CUMULOS sensor specifications

Mission concept: CUMULOS is designed to be used as a staring sensor. The basic collection sequence involves taking an image triplet, one frame per camera, as fast as possible to cover a region of interest. Figure 8 shows the pixel and swath of each camera projected onto the Los Angeles region. CUMULOS will obtain near-simultaneous frames with the three cameras. The individual cameras can frame rapidly, but downlink constraints will direct our focus towards taking small numbers of frames from each camera on selected targets of interest. With our current groundstation capabilities we can downlink one to two raw-file image triplets per ground-station contact. During operations, we will downlink thumbnail images and then select which full-frame JPEGs or raw files to retrieve from the 8 GB on-board storage. More full frames may be downlinked if JPEG compression and/or pixel aggregation are used. Use of the SDR radio, currently being tested on AC-7A, increases data downlink rates by a factor of 4. Note that the ISARA antenna is not connected to a radio, so we can't take advantage of its high gain capabilities with CUMULOS.

CUMULOS will leverage the improved pointing capabilities of the current generation Aerospace Corporation CubeSat bus, and add multispectral capabilities, to advance the point-and-stare nighttime imaging experiments we previously initiated with the visible cameras on AeroCube-4, -5, and -8. The three cameras were chosen for nighttime sensitivity and, in the case of the microbolometer, to test an uncooled microbolometer as a cloud and land surface temperature sensor.

Remote sensing applications to be investigated include: cloud detection and characterization, land and water surface temperature measurement, urban heat island measurement, hotspot detection (fires, gas flares, and volcanic activity), and nightlight detection with both the VIS and SWIR sensors. Attempts will be made to image dynamic weather events. While the nominal repeat cycles for all cameras are listed in Table 1, pointing off-nadir will allow more frequent revisit times. Particular attention will be paid to imaging weather at night to research capabilities similar to the VIIRS DNB (Day/Night Band).

The visible and SWIR cameras will be capable of imaging the Earth's surface and clouds when illuminated by moonlight and the airglow. The SWIR 0.9 to 1.7 µm band spans many excited OH emission lines in the atmospheric airglow (the Meinel bands). Much more illumination falls in the SWIR band than in the weak visible emissions detected by the VIIRS DNB under zero moonlight conditions in prior work. 12)

We want to study the utility of the wide-open SWIR band for weather missions and gain experience that can be applied to future weather sensors. The thermal waveband will be used to track cold clouds in the upper atmosphere as well as forest fires on the Earth's surface. Comparisons between bands will aid in performance assessment. Comparisons of CUMULOS data to VIIRS, MODIS (Moderate-resolution Imaging Spectroradiometer), and DMSP (Defense Meteorological Satellite Program) data, as well as data from the Japanese Space Agency CIRC (Compact Infrared Camera) and related on-orbit microbolometers, will be conducted to validate performance.

Calibration verification and on-orbit performance analysis are key parts of the mission goal of testing performance of commercial sensors. Radiometric calibration will be obtained from observations of stars, the Moon, and the Earth, and will be tied to that of other space sensors. Stellar observations with the VIS and SWIR sensors will be used to measure the operational point spread function.


Figure 8: Pixel footprints and fields of view for the three CUMULOS cameras projected onto The Aerospace Corporation and the Los Angeles region. The cameras are co-boresighted (image credit: The Aerospace Corporation)


1) "Integrated Solar Array and Reflectarray Antenna (ISARA) for High Bandwidth Cubesats," NASA Facts, 2014, URL:

2) Dee W. Pack, David R. Ardila, Eric Herman, Darren W. Rowen, Richard P. Welle, Sloane J. Wiktorowicz, Bonnie W. Hattersley, "Two Aerospace Corporation CubeSat Remote Sensing Imagers: CUMULOS and R3," Proceedings of the 31st Annual AIAA/USU Conference on Small Satellites, Logan UT, USA, Aug. 5-10, 2017, paper: SSC17-III-05, URL:

3) Dee W. Pack, Brian S. Hardy, "CubeSat Nighttime Lights," Proceedings of the 30th Annual AIAA/USU SmallSat Conference, Logan UT, USA, August 6-11, 2016, paper: SSC16-WK-44, URL:

4) "Integrated Solar Array and Reflectarray Antenna for High Bandwidth CubeSats," NASA Facts, FS-2017-03-03-ARC, URL:

5) William Graham, "Antares launches with OA-8 Cygnus en route to the ISS," NASA, November 12, 2017, URL:

6) "NASA Space Station Cargo Launches Aboard Orbital ATK Mission," NASA, Release 17-087, 12 Nov. 2017, URL:

7) "NanoRacks Launches Full External Cygnus Deployer, New Customers, and more to Space Station on OA-8," NanoRacks, 11 Nov. 2017, URL:

8) Stephen Clark, "Cygnus arrives at space station with food, experiments and cache of CubeSats," Spaceflight Now, 14 Nov. 2017, URL:

9) Mark Garcia, "Cygnus Installed on Station With New Science Experiments," NASA, 14 Nov. 2017, URL:

10) Richard E. Hodges, Daniel J. Hoppe, Matthew J. Radway, Nacer E. Chahat, "Novel Deployable Reflectarray Antennas for CubeSat Communications," 2015 International Microwave Symposium (IMS), IEEE MTT-S, Phoenix, AZ, USA, May 17-22, 2015, DOI: 10.1109/MWSYM.2015.7167153

11) David Ardila, Dee Pack, "The Cubesat Multispectral Observation System (CUMULOS)," Calcon (Conference on Characterization and Radiometric Calibration for Remote Sensing," August 23, 2016, URL:

12) Steven D. Miller, Stephen P. Mills, Christopher D. Elvidge, Daniel T. Lindsey, Thomas F. Lee, Jeffrey D. Hawkins, "Suomi satellite brings to light a unique frontier of nighttime environmental sensing capabilities," PNAS (Proceedings of the National Academy of Sciences of the United States of America), Vol. 109, No 39, September 12, 2012, pp: 15706–15711, URL:

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 (

Spacecraft    Launch    Experiment Complement   References   Back to Top