Minimize MicroCarb

MicroCarb (Carbon Dioxide Monitoring Mission)

Overview     Spacecraft    Development Status     Launch    Sensor Complement    References

MicroCarb is a CNES microsatellite mission with the goal to monitor the fluxes of carbon dioxide (CO2) at the surface between the atmosphere and the oceans and vegetation. A better knowledge of the carbon flux is needed to: 1) 2)

• Understand the functioning of the vegetation (yearly cycle, response to meteorological anomalies)

• Identify and quantify the terrestrial ecosystem Carbon sinks and sources at yearly scales (where are the Carbon sinks/sources; how do they evolve with the climate changes)

• Quantify the oceanic Carbon sources and sinks at yearly scales and their responses to the announced climate changes

• Contribute to the measurement of Carbon emission linked to fossil fuels use.

The idea of MicroCarb is to develop a mission able to compete with large satellite ones in terms of performances while keeping the cost as low as possible. The cost-competitive definition of space systems relies on a consistent balance between satellite performances, system deployment costs and mission user requirements. In particular, the consistency between satellite product and launch service is a requisite in order to optimize customer value-for-money. 3)

The MicroCarb mission is considered a successor to other CO2 missions such as GOSAT/Ibuki of JAXA or OCO-2 of NASA, and offers similar performances at an improved affordability. Carbon dioxide measurement is based on a dispersive spectrometer working in 4 spectral bands in the SWIR (Short Wave Infrared) domain. Measurements are performed in nadir viewing conditions over land, and aiming at the sun glint over the oceans. Additional measurement modes are used for instrument calibration. 4) 5) 6) 7) 8) 9)

The study performed by Airbus DS (formerly EADS Astrium SAS) for CNES has demonstrated that the definition of an ambitious carbon mission, with objectives and performances comparable with those of larger missions, can be envisaged with a microsatellite based on the Myriade Evolutions platform product, at a very affordable cost.

The current global surface network comprises less than 200 stations, unevenly distributed around the world. Because of the sparse number of monitoring stations, the flux inversion problem is highly underdetermined. Inversions thus make use of additional information in their calculation, such as a priori – or first guess - flux estimations.

Spaceborne measurements can provide global coverage, enabling to characterize regional gradients in XCO2 to solve for regional surface fluxes using atmospheric inversion systems as described in the previous section. Satellites have the potential to change the inversion paradigm from the current, data-poor conditions to a data-rich system in the near future.

The two currently flying spaceborne instruments, GOSAT and OCO-2, have been designed specifically for the monitoring of CO2. GOSAT also measures CH4. The observations from GOSAT were invaluable to develop the radiative transfer tools that relate the measured spectra to the CO2 and CH4 columns (Figure 3). Still, some problems in the measurements as well as insufficient spectral resolution did not permit to observe atmospheric signals other than the largest amplitude events. While GOSAT allowed us to investigate the largest XCO2 and XCH4 anomalies, a sensor with higher resolution and higher accuracy is needed in order to detect and quantify smaller-scale anomalies. The OCO-2 mission is making important steps to improve measurement coverage and accuracy. However OCO-2 does not measure CH4 nor any other gas that may be used to understand the origin of CO2 concentration anomalies.

The rise of atmospheric CO2 concentration is one of the main contributors to the global warming. This augmentation is mainly due to anthropogenic emissions. Indeed, only half of anthropic CO2 is absorbed by the ocean and land biomass, while the rest is stored in the atmosphere. Atmospheric CO2 increased by around 118 ppm in concentration between 1750 and 2013, and – as shown in Figure 1 - its yearly average value has reached 400 ppm in 2015. 10)

CO2 is the greenhouse gas with the highest contribution to climate change. While its concentration raised in the atmosphere, the mean temperature at Earth surface has increased by 0.9º between 1901 and 2012.


Figure 1: Carbon dioxide concentration in the atmosphere from 1958 to 2013 (image credit: CNES)


Figure 2: Annual global temperature anomalies from 1950 to 2012 (image credit: CNES)

It is essential to continue the monitoring of CO2 from space. The instrument development must benefit from the experience of previous sensors but the continuity of measurements is also essential.


Figure 3: Data processing flow and associated tools (image credit: CNES)

Scientific objective: The scientific objective of the MicroCarb mission is the monitoring and the characterization of the CO2 surface fluxes, that is the exchanges between the sources (natural or anthropogenic) and the sinks (the atmosphere, the ocean, the land and the vegetation). The annual global fluxes of CO2 represent a quantity of the order of 200 Giga tons of carbon. The emissions due to human activity bring an additional quantity of 10 Giga tons, with the effect of destabilizing the natural balance. This surplus is half absorbed by the vegetation, the land and the oceans, the other half being at the origin of the increase of the atmospheric concentration in greenhouse gases (CO2 is the main of these gases), at the origin of the climate change. MicroCarb aims to be a precursor of a future operational system able to monitor accurately the global fossil emissions. 11)

The objective of the MicroCarb mission being to supply a measurement of the CO2 concentration of an extreme precision (of the order of 1 ppm, which is 0.3 %), the spectrum in luminance observed has to be of very high quality: it is then required to have high values for the spectral resolution and for the signal to noise ratio. For a concept of dispersive spectrometer, as implemented, the required resolving power is between 25000 and 42000.

A sampling mission: The transport model used for reconstructing the fluxes has a spatial resolution of 2.5º x 3.75 º (or 250 x 400 km at the equator): This resolution can regionally be improved down to 1º x 1º. This model is able to handle 4 dimensions that is the time dimension in addition to the 3 spatial dimensions: it is then able to assimilate data spread over the time. MicroCarb is thus sized to allow to sample every cell of this model in a minimum of time (in fact one week) but not to insure a regular coverage of every single point of the globe.

It will nevertheless be able, as part of an exploratory program, to perform spectral imaging over specific areas (typically urban area), with a ground resolution of 2 x 2 km2, instead of the nominal resolution of 40 km2.

Nadir scanning: Over land surfaces, the satellite will perform acquisitions at nadir. A scan mechanism will authorize to point the line of sight on either side of the satellite track with an amplitude of ± 200 km, thus increasing the acquisition of not correlated measurements.


Figure 4: Illustration of the scanning mode at nadir (image credit: CNES)

Solar glint tracking: Over the seas, the water being dark in the spectral domain of the near infrared and thus not reflecting the sunlight, MicroCarb will aim at Glint, which is the reflection spot of the sun, instead of nadir. This capacity of tracking the Glint permits to obtain a sufficient level of flux coming in the instrument and thus authorizes the measurement of the concentration of the atmospheric CO2 over the oceans.


Figure 5: Distribution between nadir and glint measurements (example), image credit: CNES

Legend to Figure 5: The figure shows a possible distribution between Glint and Nadir modes. Orbits in blue are in Glint (orbits mainly on sea), while orbits in yellow are in Nadir mode. It is also possible to have part of an orbit in nadir pointing and another part in glint. Nadir pointing is made by the satellite along the pitch axis and thanks to the scan mechanism, along the roll axis.

Target pointing: The last observation mode consists in permanent acquisitions on a fixed target. This mode is in particular intended to allow the verification of the accuracy of the concentration assessment by comparison with the measurements performed by ground stations (belonging to the TCCON network). This operative mode will also be used to complete high resolution cartography over specific areas with dimension of dozens of km of surface. In this mode the movement around the pitch axis is provided by the satellite, while the movement the roll axis is provided by the scan mechanism internal to the instrument.


Figure 6: Illustration of the target pointing mode (image credit: CNES)


Figure 7: Overview of observation modes (image credit: CNES) 12)




The MicroCarb minisatellite is being developed on a Myriade platform, which is entirely reused with adaptations limited to standard mission activities. In particular, the standard architecture offers the dependability and agility needed to ensure pointing in glint and target modes with no need for modification, despite the highly required pointing angles. The satellite is fully compatible with a launch as a passenger in the external (microsatellite) position on the Soyuz ASAP-S structure.

The Myriade Evolutions minisatellite product line objectives are to maximize mission performances within the limited resources. The requirements call for:

- Satellite mass: 170 kg

- Satellite power: 180 W

- Mass memory: 800 Gbit

- Telemetry data rate: 156 Mbit/s

- Propulsion: 80 m/s

- Design life: 5 years.

The MicroCarb satellite mass is estimated to be about160 kg, including 5 kg of hydrazine (Ref. 10). The size of the satellite is 600 x 800 x 1000 mm with a power average of 110 W.

Performances offered to the payloads:

- Mass: up to 80 kg

- Power: 60 W permanent (orbit with eclipse)

- Pointing: accuracy < 5 x10-3 º, stability < 2 x10-2 º

- Telemetry rate: 400 kbit/s

- High rate telemetry: 16.8 Mbit/s

The MicroCarb payload has a mass of 63 kg, a size of 600 x 800 x 400 mm, an average power of 55 W and a data transmission requirement of 400 Gb/day.


Figure 8: Artist's rendition of the MicroCarb minisatellite (image credit: Airbus DS)

OBC (On-Board Computer) upgrade: The main obsolete item was the Central On-Board Computer processor T805. In order to deal with this obsolescence without redeveloping a brand new central computer, it has been decided to emulate the processor in an ASIC called LENA (Figure 9), developed under CNES contract. This ASIC foundry is now finished and it has successfully been tested in the overall computer and with the generic Myriade On-Board Software.

On top of this ASIC, the overall On-Board Computer has been renewed in order to:

- double the CPU capacity

- increase the RAM

- Provide additional interfaces for flexibility to payloads, on top of the OS-link native link: (MIL-1553, SpaceWire, BRIO bus, UART)

- upgrade TM/TC boards.


Figure 9: CPU-NG board with LENA ASIC (image credit: CNES)

On top of these standard Myriade platform evolutions, a specific one is added for MicroCarb: the high capacity mass memory. The MicroCarb instrument is rather simple i.e. with no complex processing. Atmospheric absorption spectra as recorded on the detector are almost fully downlinked to the ground for further L1 processing. Therefore, the amount of data generated by the payload is around 400 Gbit/day, which is huge for a microsatellite.

The previous capacity of the generic Myriade mass memory (16Gbit) was definitely not sufficient to meet MicroCarb needs. Hence, it was decided to develop a "combo" version of the On-board Computer, merging the OMER-E2 computer with a specific UPM-1T mass memory card. This UPM-1T card is inherited from on-going development held by Steel for Myriade Evolution platform. It will provide a mass memory capacity of 800 Gbit at EOL, with a power consumption as small as 3 W in average (for mass memory only, 10 W for overall OBC-Combo), which complies with very tight MicroCarb power budget.

AOCS upgrade: The AOCS evolutions are mainly driven by mission performance requirements. The first one is the agility required by the mission. Indeed, despite the implementation of a Sight-Changing Mirror in the instrument allowing for across-track agility, the along-track agility is challenging. Myriade platform had 3 very small wheels (0.12Nms Teldix) aligned with satellite axis for normal operations, and an additional one for safe mode. MicroCarb inertia being increased with respect to generic Myriade bus, the agility allowed by 1 wheel was not sufficient to perform target mode in particular around pitch axis. It has then been decided not to change the wheels but to use 4 wheels in skewed configuration in order to:

- increase pitch agility

- allow 4/3 hot redundancy.

The pyramid is oriented towards pitch axis with a 45° angle tilt, allowing to augment torque/momentum capacity by more than 2.5 with respect to a configuration with only one wheel on this axis (Figure 10). Even with one wheel failed, it will be possible to perform the target mode.


Figure 10: Normalized torque capacity with skewed configuration (image credit: CNES)

In addition to wheels configuration modification, it has been decided to move towards a gyroless AOCS in order to:

- manage gyro obsolescence

- save space inside the platform

This evolution is made possible by the availability of new star trackers such as Hydra-M from Sodern which provides better robustness to Moon-blinding and to temperature constraints, as well as better measurement performances than current baseline Myriade's Star Tracker.

In order to meet geolocalization needs coming from the mission (around 400 m overall), and possibly to implement an autonomous guidance subsystem, it is required to get a precise on-board orbit coming from embarked GNSS receiver. The most adequate receiver identified for MicroCarb, in particular for what concerns low power consumption is the Skyloc receiver from Syrlinks.

All these hardware modifications will have to be backed with On-Board Software evolutions to manage in particular the gyroless AOCS mode, as well as its associated FDIR (Failure Detection, Isolation and Recovery) and a specific safe mode with two wheels instead of one.

Propulsion upgrade: The Myriade bus is equipped by default with hydrazine propulsion module provided by Airbus Defense and Space. It will have to be modified for MicroCarb for two reasons:

- debris risk mitigation rules

- REACH (Registration, Evaluation and Authorization of CHemicals) evolution compliance (TBC).

The French Space Operations Act voted in 2010 will be, after a "best effort" phase, fully applicable by end of 2020 to all satellites operated from France. It requires to passivate the satellite after its operational life and to put it on an orbit leading to an atmospheric reentry within 25 years (this is applicable for very small satellites that represent a casualty risk smaller than 10-4 which is the case of MicroCarb). The propellant budget has been computed in order to account for the orbit decrease (from 649 km altitude mission orbit to typically 620 km altitude) at end of life.

But the Myriade design did not allow to passivate the tank at the end of life. Indeed, pressurant gas is trapped upstream a membrane even after propellant drain. Therefore, a microperforator will be added on the tubing between the tank and the gaz fill and drain valve. This microperforator under development in Lacroix (with CNES funding) will be qualified by end of 2016 (Figure 11).


Figure 11: Illustration of the microperforator design (image credit: CNES)

The REACH issue is still TBC. Indeed, hydrazine does not yet belong to forbidden material list but it is on the candidate list. It might be inserted in the forbidden list in the coming years which will make difficult or even impossible to use current propulsion system. Alternative solutions are under analysis in order to get a full REACH compliance. We will take the opportunity of these modifications to improve the performances of the propulsion sub-system, in particular for what concerns the total available ΔV.

Power subsystem upgrade: Here again, the required evolutions are linked with equipment obsolescence and debris risk mitigation, but can be the opportunity to improve the performances of the subsystem. An existing ABSL battery with Sony HC cells is no longer available, it is therefore envisaged to use a new battery, still to be selected, which will take benefit from the latest Li-Ion technology improvements. Hence, it is expected to get additional power storage capacity within the same mass/volume budgets, allowing to cope with MicroCarb demanding power budget, in particular in cold cases.

The last evolution on power subsystem is the modification of the PCDU (Power Conditioning and Distribution Unit) that will have to be modified to allow for electrical passivation at end of life. This modification is required by the French Space Operations Act to avoid battery recharging (along with explosion risks) after satellite switch off. A specific relay will be activated to completely disconnect the battery from solar arrays and thus to forbid any recharging. The solar cells can also be upgraded for the next Myriade missions while keeping the existing PCDU. However, CNES intends to use for MicroCarb a solar array in storage that fits the mission needs.

RF communications subsystem upgrade: The single evolution implemented on this subsystem is a new X-band emitter implementation. This new emitter under development by Sirlinks for the Myriade Evolution platform is able to reach high data-rate compatible with the MicroCarb needs. Indeed, in order to download 400 Gbit/day with a limited number of passes (typically 4 to 5), the data-rate has to reach roughly 150Mbit/s which is possible with the selected equipment. Moreover, this equipment is fully compatible with UPM-1T mass memory board and no development is therefore necessary. The power consumption is, however, quite high (>50 W) which puts constraints on the bus accommodation due to high dissipation.

The external satellite accommodation for MicroCarb is described in Figures 13 and 14. All the appendices (brackets, sensors, baffles, antennas and solar array) take most of the space on the platform walls. Remaining surfaces for thermal radiators are very limited but fulfill the heat rejection needs. The star tracker optical head is positioned on payload module deck in order to reduce thermoelastic distortion between AOCS reference and payload line of sight.

Two S-band antennas are placed on Earth (nominal operations) and zenith (safe mode) faces. One X-Band antenna is placed on Earth face while GNSS antenna is pointing towards zenith with a slight tilt angle (18°) in order to avoid maskings coming either from payload or star-tracker baffles. Three sun sensors are accommodated all around the satellite in order to get a 4π steradian coverage for safe mode.


Figure 12: Earth and solar array faces external accommodation (image credit: CNES)


Figure 13: Zenith and cold faces external accommodation (image credit: CNES)


Development status:

• In April 2016, CNES awarded a contract to Airbus DS to design and build the optical instrument for MicroCarb. 13)

• MicroCarb program decided: The decision was announced by the French government at the COP-21 in Paris, on Dec. 8, 2015.

• The MicroCarb project is in Phase B as of 2016.

• Organization actors: MicroCarb has been defined by CNES in collaboration with French research laboratories from CNRS and CEA.

- Laboratoire des Sciences du Climat et de l'Environnement (F. M. Breon, PI)

- LMD (Laboratoire de Météorologie Dynamique)

- Institut Pierre Simon Laplace

- Laboratoire Atmosphères, Milieux, Observations Spatiales, and others

• Funding is provided by the French program "Investment for Future".


Figure 14: Overview of the MicroCarb mission timeline (image credit: CNES)


Launch: A launch of MicroCarb is planned for 2020 from Kourou as co-passenger or auxiliary passenger on a Soyuz or a Vega European launcher.

Orbit: The choice of the orbit is dictated by the scientific objectives while taking into account the optimization for launch opportunities as piggy bag and the rules governing the space debris mitigation. The selected orbit is a Sun-synchronous orbit with an altitude of 650 km and LTDN (Local Time at Descending Node) at 10:30 hours. The choice of the local time allows optimizing the solar flux (reduction of the reflection angle). The choice of the altitude optimizes the homogeneity of the coverage at the horizon of one week. The system still remains compatible with a change of the local time (13:30 hours).


Figure 15: Coverage obtained on a cycle of 21 days and a sub-cycle of 7 days (image credit: CNES)



Sensor complement:

The objective of the MicroCarb payload is to measure the solar light reflected by the Earth surface in the near infrared. The solar spectrum is modified by the atmospheric CO2 molecules (CO in option) as shown in Figure 16. Note: The methane band was recently removed. Hence, MicroCarb will no longer measure CH4. 14)


Figure 16: Passive payload principle and gas absorption spectra as inputs of the instrument (image credit: CNES, Ref. 10)

The instrument will be able, thanks to a very high spectral resolution, to precisely measure the absorption in 4 bands. As an additional option, another band for O2 and a band gathering H2O and CO and it will then be possible to derive the CO2 concentration in the air column below the satellite.

The atmospheric sounding instrument for MicroCarb is a dispersive spectrometer, using a reflexive grating for spectral bands dispersion. The main design characteristics (requirements) of the instrument are as follows (Ref. 4):

• High signal-to-noise ratio combined with a high spectral resolution in order to achieve accurate CO2 measurements

• A spatial resolution better than 50 km2 over several across-track pixels in order to maximize the odds of cloud-free pixels acquisition

• A polarization-free design (lower than 0.1% in both nadir and glint modes), allowing to improve signal-to-noise ratio in particular over the oceans

• An extensive on-ground characterization and in-flight calibration concept to reach the required measurement accuracy

• A built-in cloud imager to allow discrimination of cloud-contaminated pixels.

Spectral bands

B1: 0.76 µm (O2)
B2: 1.61 µm (CO2)
B4: 2.06 µm (CO2)
B5: 1.27 µm (O2)

XCO2 measurement accuracy

Bias < 0.1 ppm; Random noise < 1 ppm

Resolution power (λ/Δλ)

≥ 25 000 for each band

IFOV (Instantaneous Field of View)

3 IFOVs: size 4.5 km (cross-tracvk) x 9 km (along-track) simultaneously acquired at nadir

Swath width

13.5 km (which results from 3 soundings of 4,5 km width each after processing)

Spectral sampling

> 2.8

Pointing modes

Nadir: over land
Glint: over oceans
Target: over ground stations (TCCON)

SNR (Signal-to-Noise Ratio)

200 (B4), >500 (B1)

Table 1: MicroCarb instrument requirements

The simple and compact architecture baselined for the sounder as well as the reuse of off-the-shelf components wherever possible allows to define an instrument compatible with both a microsatellite concept with a launch mass lower than 200 kg and an affordable implementation budget. The instrument requirements call for a mass of < 70 kg with an average power demand of 55 W, and it globally fits within a 80 cm x 60 cm x 40 cm volume.


The measurement relies on the utilization of a passive SWIR (Short Wave InfraRed) spectrometer which analyzes the solar light reflected by the Earth. This light crosses the atmosphere 2 times, during which it is partly absorbed by the gaseous species present in the atmosphere. The solar spectrum is then modified and absorption rays appear at the wavelengths specific to the molecules encountered. The depth of these rays is directly led by the quantity of absorbing molecules.

The measurements are then limited to the part of the orbit with sufficient solar reflected flux (high latitudes are excluded, with low impact on the scientific benefit).

Clouds and aerosol presence needs to be considered: clouds will block out the Earth surface, then annealing any measurement, while aerosols will reflect and scatter the solar light, then usually bringing to underestimate the actual quantity of CO2. High values of spectral resolution and Signal to noise ratio are necessary in order to restitute the spectra with the required accuracy.

Instrument concept and requirements: The definition of the instrument concept is driven by the requirement for compactness and by the radiometric and spectral performances. The spectrometer relies on a dispersive concept, using a unique blazed (echelle) grating element at different orders of diffraction. These orders are fit to the wave lengths of the measurement bands.

An original device permits to multiplex the different diffracted channels on a single detector. One dimension of the detector is dedicated to the spectral dimension of each band. The other dimension of the detector permits both to image the field of view, as limited by the spectrometer entrance slit, and to place side by side different bands. Binning of the different pixels along the spatial axis in each band permits to improve the SNR.

The projection on ground of this slit is close to 0,4 km (along track) x 12 km (cross track), and is separated in 3 IFOVs (Instantaneous Field of Views). The spectrometer forms sharp monochromatic images of this slit on the detector array for the 4 bands as illustrated in Figures 17 and 18. The measurements are then integrated during 1.5s together with the satellite ground track motion. After this integration, the measurements downloaded to the ground represent a spatial resolution of 4.5 km (cross track) x 9 km (along track).

The detector is a 1k x 1k HgCdTe matrix (Sofradir NGP). Cooling of the focal plane at 150 K is achieved thanks to a passive system with a cryogenic radiator directed towards cold space and protected by a shield from the sun and Earth illumination.


Figure 17: Acquisition and measurements principle, part 1 (image credit: CNES)


Figure 18: Acquisition and measurements principle, part 2 (image credit: CNES)

An entrance telescope forms the image at the level of the spectrometer entrance slit. That telescope is shared with an imager (operating at 0.625 µm) permitting to achieve cloud detection.

Calibration sources are implemented and will permit to check the stability of the instrument in orbit or re calibrate if needed.

An electronic box permits to read out the detector, control and monitor the instrument, and format the telemetry data. All the data from the detectors are downloaded , no processing is implemented on–board.

Background: 15)
The measurement principle is based on the inversion of the spectral content of the area sounded. The instrument observes the Earth's atmosphere through three very narrow spectral windows. Its basic task is to accurately measure the spectral radiance reaching the TOA (Top Of Atmosphere). The light analyzed is from the sun, once bounced back off the Earth's surface at the targeted sounding point and absorbed by atmospheric gases—including CO2—and possibly scattered by atmospheric aerosols (Figure 19).

Carbon dioxide gas has absorption lines in the thermal infrared at 1.61 µm (band B2) and 2.06 µm (band B4). The sun's radiation at these wavelengths, reflected by the Earth back to the satellite, therefore contains the molecule's signature. It is the depth of the absorption lines that contains the information on CO2 concentration. An additional spectral band in the oxygen band at 0.76 µm, noted band B1, provides surface pressure data on spectrum inversion. This band also provides information on the contribution of atmospheric aerosols and fine clouds to the radiation collected by the onboard instrument. Data from this third band are taken into account when the CO2 spectra are inverted to enhance accuracy.

Above land, the satellite acquires measurements with a nadir line of sight. Above oceans, water being dark in the near-infrared and therefore not reflecting sunlight in a lambertian way; MicroCarb will aim at the glint, i.e. the sun's specular reflectance. This capability of following the glint enables a large enough flux to be obtained at the instrument entrance, thus allowing atmospheric CO2 concentration to be measured above oceans.

The observation system is complemented by a two-dimensional imaging function at a wavelength of 0.625 µm to observe the sounded area. This 2D map of the sounded field accompanies each item of spectral data acquired by the instrument, and will provide data upon clouds.


Figure 19: Typical TOA reflectance spectra (image credit: CNES)


Spectrometer architecture and budgets (Ref. 10):

The payload allocations are very tight for this kind of instrument:

- the volume is limited by the launcher compatibility (smallest case being the Soyuz-ASAP external position)

- the mass is limited by both structural constraints of the platform and the launcher compatibility: 70 kg max

- the power is limited by the solar array capacity and the platform consumption: 55 W max.

The payload designed by Airbus Defense and Space (Figure 11) meets all these requirements with adequate margins.


Figure 20: Main instrument components and layout on the Myriade platform (image credit: CNES)

*The instrument is composed of:

1) a pointing and calibration system: at the entry of the instrument, this system allows to change the line of sight of the instrument in order to point targets off track, in a ±25º range, and also allows to point towards calibration sources (lamps and sun through a specific slit)

2) a telescope to collimate the light coming from the Earth or from calibration sources

3) a spectrometer able to decompose the light according to its wavelength

- a large detector to measure the O2 and CO2 spectra

- a visible detector to image the ground in order to detect the clouds

4) a passive cooling system based on a two-stage circular radiator protected from external fluxes by a baffle

5) video electronics dedicated to each detector

6) one main electronic box in charge of power conditioning and sequencing of all the electronics and communication with the spacecraft bus.

All the optical parts are supported by a SiC (Silicon Carbide) optical bench attached to the platform panel with struts and flector. The use of SiC provides a very good stability in orbit which is mandatory for this kind of instrument. The temperature reached by the passive cooling is close to 150 K for the detectors and 225 K for the spectrometer.


The MicroCarb mission is a challenging mission for a microsatellite (actually a minisatellite at 160 kg). The mission requires good agility and very good pointing accuracy and geolocalization performances. Thanks to an innovative instrument concept based on a single detector for spectrum measurement and an efficient passive cooling, it has been possible to stay within the allocations of a 160 kg class satellite while meeting or even improving the performances of much bigger satellites currently in orbit or to be launched. The Myriade upgraded platform is able to embark this instrument with a low cost and with high performances on all domains.

Table 2 shows the comparison in mass between CO2 measuring spacecraft in orbit or to be launched, together with gas and targeted accuracy showing that MicroCarb will be by far the smallest satellite for this purpose, while providing equivalent or better measurement than these other projects.

Thanks to its small size and price, MicroCarb satellite can be a very good precursor to a constellation of satellites orbiting the Earth that would provide better spatial and temporal resolutions.



Measured greenhouse effect gas

Targeted accuracy on CO2

GOSAT (launched in 20129

1750 kg

CO2 + others

4 ppm

OCO-2 (launched in 2014)

450 kg


1 ppm

TanSat (launch in Dec. 2016)

500 kg


4 ppm

MicroCarb (launch in 2020)

160 kg


1 ppm

Table 2: Mass comparison between CO2 measuring spacecraft


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2) Clémence Pierangelo on behalf of Microcarb team: C. Deniel, F. Bermudo, V. Pascal, P. Moro, D. Pradines, S. Gaugain, F.-M. Bréon,"CNES concepts for microsatellites for CO2 observations," Satellite Hyperspectral Sensor Workshop, Miami, Virginia Key, Florida, USA, March 29-31, 2011, , URL:

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4) Eric Maliet, Charles Koeck, Claire Roche, Eric Beaufumé, Bruno Millet, François Bermudo, "Greenhouse gas monitoring missions from space," Proceedings of the 63rd IAC (International Astronautical Congress), Naples, Italy, Oct. 1-5, 2012, paper: IAC-12-B1.2.4

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7) "Towards a European Operational Observing System to Monitor Fossil CO2 emissions," European Commission, October 22, 2015, URL:

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9) Réjane Ibos, Jean Jaubert, Didier Pradines, Arnaud Varinois, "MicroCarb Micro-Satellite: Mission and system analysis for pointing modes definition and constraints management," Proceedings of the 14th International Conference on Space Operations (SpaceOps 2016), Daejeon, Korea, May 16-20, 2016, URL:

10) Arnaud Varinois, Didier Pradines, Francois Buisson, "MicroCarb: A microsatellite for atmospheric CO2 monitoring," Proceedings of the 14th International Conference on Space Operations (SpaceOps 2016), Daejeon, Korea, May 16-20, 2016, URL:

11) MicroCarb Mission," CNES, Dec. 8, 2015, URL:

12) Francois Buisson, Didier Pradines, Veronique Pascal, Denis Jouglet, "An introduction to MicroCarb, first European program for CO2 monitoring," International Working Group on Green house Gases Monitoring from Space, IWGGMS-12, Kyoto Japan, June 7-9, 2016, URL:

13) "CNES selects Airbus DS to build MicroCarb payload to map CO2 levels," Airbus DS Press Release, April 13, 2016, URL:

14) Information provided by Francois Buisson of CNES

15) Veronique Pascal, Christian Buil, Elodie Cansot, Jacques Loesel, Laurie Tauziede, Clemence Pierangelo, François Bermudo, Mathieu Olivier, Mickael Dubreuil, "A new space instrumental concept based on dispersive components for the measurement of CO2 concentration in the atmosphere," Proceedings of the ICSO (International Conference on Space Optics), Ajaccio, Corse, France, Oct. 9-12, 2012, paper: ICSO-129, 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 (

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