Minimize SARAL

SARAL (Satellite with ARgos and ALtiKa)

SARAL is a cooperative altimetry technology mission of ISRO (Indian Space Research Organization) and CNES (Space Agency of France). In this setup, CNES is providing the payload module consisting of the AltiKa altimeter, DORIS, LRA, and Argos-3 DCS (Data Collection System), and the payload data reception and processing functions, while ISRO is responsible for the platform, launch, and operations of the spacecraft. A CNES/ISRO MOU (Memorandum of Understanding) on the SARAL mission was signed on Feb. 23, 2007.

The overall objectives are to realize precise, repetitive global measurements of sea surface height, significant wave heights and wind speed for: 1) 2) 3)

• The development of operational oceanography (study of mesoscale ocean viability, coastal region observations, inland waters, marine ecosystems, etc. )

• Understanding of climate and developing forecasting capabilities

• Operational meteorology.

The SARAL mission is considered to be complementary to the Jason-2 mission of NASA/NOAA and CNES/EUMETSAT (it is also regarded a gap filler mission between Envisat and the Sentinel-3 mission of the European GMES program). The combination of two altimetry missions in orbit has a considerable impact on the reconstruction of SSH (Sea Surface Height), reducing the mean mapping error by a factor of 4. 4) 5) 6)

AltiKa, the altimeter and prime payload of the SARAL mission, will be the first spaceborne altimeter to operate at Ka-band.

Background: The AltiKa concept, based on a wideband Ka-band altimeter (35.75 GHz, ~500 MHz) concept, was initially proposed in 2002 as a CNES altimetry minisatellite mission (150 kg) on the Myriade platform. Feasibility studies were also made to accommodate AltiKa on the TopSat platform of SSTL (Surrey Satellite Technology Ltd.). In Dec. 2005, CNES approved the development of the AltiKa payload since an opportunity arose to embark the instrument on a cooperative mission of ISRO and CNES, namely OceanSat-3. However, early in 2006, the OceanSat-3 launch was postponed to the period 2011/12, beyond the schedule objective of AltiKa. As a consequence, CNES and ISRO established an alternative option, based on a dedicated minisatellite using a new SSB (Small Satellite Bus) platform to be developed as ISRO. 7) 8) 9)


Figure 1: Overview of current (mid 2009) and future altimetry missions (image credit: CNES) 10)


Spacecraft bus and payload module development at ISRO:

The minisatellite, as provided by ISRO, involves nothing less but the development of a new spacecraft bus. The general spacecraft architecture consists of two modules: namely the introduction of a new modular bus (under development at ISRO as of 2007), referred to as SSB (Small Satellite Bus), and PIM (Payload Instrument Module). Two SSB designs are under development: 11) 12)

1) The first one is being developed for a minisatellite series with a total launch mass of about 450 kg, including a payload mass of ~ 200 kg.

2) The second one is considered for a microsatellite series with a total launch mass of around 100 kg, including a payload mass of 20-30 kg

In 2012, ISRO refers to the former SSB as the IMS-2 (Indian MiniSatellite-2) bus. The IMS-2 bus evolved as an operational minisatellite class platform with complete redundancy in the mainframe subsystems. The IMS-2 development is an important milestone, it is envisaged at ISRO/ISAC to be a work horse for different type of applications / operational future missions. The first mission of the IMS-2 implementation is SARAL. 13)

The design layout is such that the bus module and the payload module of each series may be integrated and tested separately (thus reducing the interdependency during the realization between both modules). IMS-2 is also designed to accommodate different types of payloads with minor modification from mission to mission. IMS-2 is developed with the intention to permit a multiple payload launch by PSLV using the DLA (Dual Launch Adaptor), which caters to minisatellites in the class of 450-600 kg.

The structure of the bus is built with aluminum honeycomb panels. It consists of 3 horizontal decks, namely the bottom deck, top deck and payload deck, and four vertical equipment panels. The bottom deck has the interface ring (with Merman band interface 937VB) bolted to it. The design employs a number of stiffness measures to avoid any resonant frequencies of the launcher in both lateral and longitudinal directions.

The IMS-2 system design includes all general platform services functions such as the EPS (Electric Power Subsystem) with battery and solar arrays, the AOCS (Attitude and Orbit Control Subsystem), TT&C (Telemetry, Tracking & Command) subsystem, RCS (Reaction Control Subsystem), the thermal subsystem for bus (a passive system is used), and mechanisms (for solar panel deployment), etc. Most of the systems have redundancy/large margins or space capacity.


Figure 2: Overview of the SARAL spacecraft configuration (image credit: ISRO/CNES)





LEO, sun-synchronous

Mission specific


- Design life

5 years
Full redundancy


- Structural configuration
- Mass
- Bus dry mass
- Onboard propellant
- Platform size

Aluminum honey comb sandwich structure with 4 vertical panels and 2 horizontal decks
450 kg (minisatellite class)
~180 kg
21 kg
~ 1 m x 1 m x 0.6 m


- Solar array power @ EOL
- Platform power
- Payload power

850 W
200 W
250 W

AOCS (Attitude and Orbit Control Subsystem)

- Attitude control
- Attitude knowledge
- Attitude control error
- Drift rate
- Spacecraft pointing agility
- Spacecraft pointing modes

3-axis stabilized with reaction wheels / RCS system
as low as 0.02º (3σ)
as low as ± 0.1º (3σ)
as low as ± 10-4 º/s (3σ)
Inertial, solar, nadir, point tracking, maneuverable

RF communications

- TC uplink communications
- TM downlink communications
- Payload data downlink
- Protocol standard

Hot redundant S-band receivers, 4 kbit/s
Cold redundant S-band transmitters, 4 kbit/s
X-band, 105 Mbit/s


- Payload mass
- Payload volume (available)
- Payload mechanical interface

200 kg max
0.9 m x 0.9 m x 2 m
Four pod interface


- Payload data storage capacity
- Payload TM/TC interface
- Payload science/video interface
- Payload power interface

64 Gbit storage (max)
MIL-STD-1553B interface, digital
LVDS (Low Voltage Differential Signaling)
Raw bus 28-33 V


- Launch vehicle interface
- Missions ongoing
- Bus delivery time

PSLV – DLA compatible
20 months (typical)

Table 1: Overview of IMS-2 platform capability

The minisatellite bus module has a standard simple interface for the payload module. The new bus derives its shape from previous IRS configurations with cuboid structure. The bottom deck of the minisatellite bus is measuring 900 mm x 900 mm providing an interface with launch vehicle. The launcher interface uses a Merman clamp band, 937VB. The top deck is of the same size as the bottom deck featuring four corner points extending as pillars to provide a four-point interface for the payload module.

The PIM (Payload Instrument Module) consists of a set of CFRP (Carbon Fiber Reinforced Plastic) based panels with appropriate interfaces for mounting onto the main platform and for mounting of the payloads and associated elements. The payload-related systems like data handling, SSR (Solid State Recorder), etc., are mission specific functions.


Figure 3: General configuration of the PIM (image credit: ISRO)

The PIM is also of square shape and of the same cross-section size as that of the bus with four corners (payload interface pods) interfacing with main bus. The PIM, unlike the bus module, has the freedom to grow vertically; the only limitation is the available volume within the heat shield enclosure of the launch vehicle and allowable frequency constraints. 14)


Figure 4: Functional block diagram of the IMS-2 bus (image credit: ISRO, Ref. 13)


SARAL spacecraft:

Structure: The structural configuration of the IMS-2 bus is a cuboid of size: ~1m x 1 m x 0.6 m. Use of an aluminum honeycomb sandwich construction. The face sheet is aluminum and the core is consists of an aluminum honeycomb structure. The structure consists of two horizontal decks, namely a bottom deck and a top deck, and four vertical decks, EP01 to EP04.


Figure 5: Schematic view of the IMS-2 bus structure (image credit: ISRO)

AOCS: The spacecraft is 3-axis stabilized. Attitude is sensed by a miniature star sensor providing an attitude knowledge of < 30 µarcsec about all axes. This attitude information is also used to update the inertial angle information of the gyros. The gyros are also of a miniaturized version. Further attitude sensors are 4 sun sensors (4π FOV) and a miniature 3-axis magnetometer. - Actuation is provided by 4 reaction wheels (5 Nms) arranged in tetrahedral configuration, and 2 magnetorquers. The latter one are used for the momentum dumping of the wheels. The monopropellant RCS (Reaction Control Subsystem) uses a single tank (21 kg of propellant) with two blocks of 1N thrusters. It is mainly used for orbit maintenance.

The star sensor is a single integrated sensor package consisting of a detector, preamplifier and an FPGA, which acts as intelligent video processor. An IRU (Inertial Reference Unit) is used for attitude referencing in all phases of spacecraft operations. The IRU consists of cluster assembly where three numbers of two-degree-of freedom MDTG (Multiplexed Digital Trunk Group) mounted on a cluster and suspended with 4 space qualified vibration isolator separately.

- Pointing accuracy = 0.1º (3σ)

- Drift rate: ± 10-4 º/s (3σ)


Figure 6: Photo of the reaction wheel assembly (image credit: ISRO)

EPS: The EPS employs a single bus, a DET (Direct Energy Transfer) system, with an unregulated bus voltage of 28-33 V. An average power of ~500 W is provided with 2 articulated solar panels (total area of 3.88 m2) with UTJ solar cells. Maximum power of 850 W. The power output of the solar array is regulated by the battery charge conditions. A Li-ion battery with 46 Ah capacity is used for eclipse phase operations. The power conditioning and the power distributing converters have full redundancy.


Figure 7: Power consumption chart for SARAL (image credit: ISRO)

The BMU (Bus Management Unit) with the OBC (OnBoard Computer) take care of all data handling functions using the MIL?STD?1553B standard interface with all onboard subsystems. The payload data handling subsystem employs serial interfaces to the baseband data handling formatter. The formatter receives the payload data packets, annotates these with the housekeeping data, and deposits them onto the SSR. All the hardware required for BMU is optimized and implemented using four cards of size 31 cm x 31 cm. The CPU is built around the MAR31750 processor, with the MMU MAR31751 device for memory expansion. Figure 8 shows the BMU/OBC hardware.


Figure 8: Photo of the BMU and OBC hardware (image credit: ISRO)

RF communications: There is no real-time data transmission requirement for SARAL. The SSR has a capacity of 32 Gbit. The TT&C data are transmitted via S-band. The TC uplink modulation scheme is FM/PSK/PCM and the uplink data rate is 4 kbit/s. The TM data is BPSK modulated, the transmit power is 1 W. A near omnidirectional TT&C antenna is used.

The payload data handling system consists of BDH (Baseband Data Handling) system and the SSR (Solid State Recorder). The data handling system collects, formats, and stores all data for later downlink. All links, both up and down, are encrypted to prevent unauthorized access to the data. It interfaces with the payloads and acquires the data from payloads through LVDS interface. The read payload data will be formatted as per CCSDS Transfer Frame format. The playback data is RS (Reed Solomon) coded, randomized, convolution coded and given to the X-band system for transmission to the ground. The SSR memory capacity is variable and is based on mission requirement. The maximum capacity of SSR is 64 Gbit.

The SARAL payload data are transmitted in X-band at data rates of 32 Mbit/s. The transmitter uses a SSPA (Solid State Power Amplifier) with an EIRP output of ~4 W. A shaped beam antenna with a gain of +4.5 dBi at ±65° along with 4W SSPA provides the necessary link margin.

In addition, the UHF link is used to collect the data from the ground segment with the Argos-3 onboard instrument while the L-band is used to transmit the collected data to the data centers.


Figure 9: The SARAL spacecraft configuration (image credit: ISRO, CNES)

The SARAL spacecraft has a mass budget of about 407 kg. The IMS-2 has a total mass of 199 kg, while the total payload mass is 147 kg (with 5% margin). The design life is 5 years.


Launch: The SARAL minisatellite was launched on Feb. 25, 2013 from SDSC-SHAR (Sriharikota, India) on the PSLV-C20 launcher of ISRO. 15)

Orbit: Sun-synchronous near-circular dawn-dusk orbit, altitude of ~781 km, inclination of 98.538º, orbital period of 100.6 minutes, LTAN (Local Time on Ascending Node) = 18:00 hours, repeat cycle = 35 days (No of orbits within a cycle = 501).

The six secondary payloads manifested on this flight were:

• BRITE-Austria (CanX-3b) and UniBRITE (CanX-3a), both of Austria. UniBRITE and BRITE-Austria are part of the BRITE Constellation, short for "BRIght-star Target Explorer Constellation", a group of 6.5 kg, 20 cm x 20 cm x 20 cm nanosatellites who purpose is to photometrically measure low-level oscillations and temperature variations in the sky's 286 stars brighter than visual magnitude 3.5.

• Sapphire (Space Surveillance Mission of Canada), a minisatellite with a mass of 148 kg.

• NEOSSat (Near-Earth Object Surveillance Satellite), a microsatellite of Canada with a mass of ~74 kg.

• AAUSat3 (Aalborg University CubeSat-3), a student-developed nanosatellite (1U CubeSat) of AAU, Aalborg, Denmark. The project is sponsored by DaMSA (Danish Maritime Safety Organization).

• STRaND-1 (Surrey Training, Research and Nanosatellite Demonstrator), a 3U CubeSat (nanosatellite) of SSTL (Surrey Satellite Technology Limited) and the USSC (University of Surrey Space Centre), Guildford, UK. STRaND-1 has a mass of ~ 4.3 kg.

The University of Toronto arranged for the launch to carry three small satellites for universities as part of its Nanosatellite Launch Services program, designated NLS-8: BRITE-Austria, UniBRITE and AAUSat3. The three NLS satellites used the XPOD (Experimental Push Out Deployer) separation mechanism of UTIAS/SFL for deployment.

The STRaND-1 nanosatellite was deployed with the ISIPOD CubeSat dispenser of ISIS (Innovative Solutions In Space).


SARAL-AltiKa is intended as a gap filler mission between the RA-2 onboard Envisat (ESA, launched in 2002, and lost in 2012) and the SRAL onboard Copernicus/Sentinel-3 (to be launched in 2014). As such, SARAL-AltiKa will fly on the same orbit as Envisat of ESA (allowing to re-use the mean sea surface fields in the data processing, and to have sea level anomaly monitoring with high quality from the start of the mission), to ensure a continuity of altimetry observations in the long term. On the other hand, the local time of passage over the equator will be different due to specific cover requirements for the instruments constellation of the Argos system.


Figure 10: Artist's rendition of the SARAL spacecraft in orbit (image credit: CNES)



Mission status:

• Feb. 2014: The SARAL spacecraft and its payload are operating nominally. 16)

• Sept. 2013: The SARAL GDR (Geophysical Data Record) products are routinely generated since July 2013, and delivered to all users since September 2013 in version 'T'. GDR dissemination to all users on the AVISO ftp server. 17)

- OGDR (Operational Geophysical Data Record) and IGDR products have been distributed to all users from June 25th; GDR products are available to PIs since August 2, 2013.

- Some algorithms are still to be tuned: neural network used for radiometer data ground processing, Sea State Bias computation, altimeter wind speed and ICE2 retracking.

- According to users presentations, the main message of this meeting is the easiness to use the data (thanks to the ground segment operationnality and the expertise of the users). The level of quality achieved by the products in terms of accuracy, data latency and availability is such that the Saral/AltiKa data are now operationnaly integrated in several forecast systems.

• July 11, 2013: EUMETSAT contributes, as a partner in the SARAL mission, by adding the near real time product service capability. 18) 19)


Figure 11: Preview: the first waves' height map made from ALTIKA measurements (image credit: CNES) 20)

• The final orbit of the SARAL spacecraft was reached on March 13,2013. The cycle No 1 was started on March 14, 2013. 21)

• The subsystems of the SARAL platform were switched on between February 25 and 26, 2013. All the instruments are nominal. The first days of instrument commissioning indicate good performances, as expected. 22)



Sensor complement: (AltiKa, DORIS, LRA, Argos-3)

AltiKa (Altimeter in Ka-band):

The AltiKa project of CNES is based on a wideband Ka-band altimeter (35.75 GHz, 500 MHz), which will be the first oceanography altimeter to operate at such a high frequency. The high-resolution AltiKa altimeter has a dual-frequency radiometric function which allows the altimetry measurements to be corrected for the effects due to the signal passing through the wet troposphere. This is coupled with the DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite) tracking system and an LRA (Laser Retroreflector Array) for the measurement of precision orbits. 23) 24) 25) 26) 27) 28) 29)

The key feature of the altimeter payload has been the selection of Ka-band (35.75 GHz) for the altimeter avoids the need for a second frequency (necessary when using the Ku-band) to correct the ionospheric delay; the configuration allows the same antenna to be shared by the altimeter and the radiometer. This single antenna solves the accommodation problem of a conventional altimetry payload on a minisatellite (150 kg class). The Ka-band concept allows also the improvement of the range measurement accuracy by a factor of 3:1 due to the use of a wider bandwidth and a better pulse-to-pulse echo decorrelation.

The AltiKa design and development is a partnership of CNES, scientific laboratories (LEGI/CNRS, IFREMER, CLS, etc.) and industry, with TAS-F (Thales Alenia Space-France) as prime instrument contractor. The AltiKa instrumentation consists of an integrated altimeter/radiometer instrument. It is composed of the following elements:

• ORA (Offset Reflector Antenna) shared by the altimeter and the radiometer functions

• AMU (Altimeter Microwave Unit). The objective is to gather all analog support tasks of the altimeter operations (bandwidth expansion, frequency translations, local oscillator generation, high power amplification, transmitter/receiver/antenna duplexing, low noise amplification, deramp processing, bandwidth filtering, IF processing).

• RMU (Radiometer Microwave Unit). The objective is to gather all analog support tasks of the radiometer operations (low noise amplification, bandwidth filtering, high gain amplification, power detection, low pass filtering).

• DPU (Digital Processing Unit). The objective is to gather all the (hardware and software) processing functions of the instrument (digital chirp generator, time FFT, altimeter echo processing, radiometer signal processing, instrument interface handling with the platform computer).

• RCU (Radiometer Calibration Unit). The objective is to assure the interconnection and switching between the antenna, the radiometer receivers, and the radiometer calibration loads or horn. The RCU is in charge to the connection of the radiometer receivers either to the nadir measurement path or to calibration paths: a sky horn pointing to deep space for cold reference and a load at ambient temperature for hot reference. The RCU was developed by COMDEV-UK.


Figure 12: Functional block diagram of the integrated AltiKa instrument (image credit: CNES, TAS-F)

The altimeter design principle is of Poseidon heritage (Ku-band instrument flown on the Jason missions) and is based on the classical deramp technique for pulse compression Four key evolutions on AltiKa have improved significantly the radar performance compared to conventional Ku-band altimeters:

1) The larger bandwidth from 320 MHz (of Ku-band instruments) to 480 MHz (Ka-band) provides a vertical resolution improvement from 0.5 m to 0.3 m, providing also the same magnitude of improvement in the range accuracy.

2) The shorter decorrelation time of the sea echoes at Ka-band permit an increase in the PRF (Pulse Reception Frequency) for averaging efficiently more echoes in the same integration time. Hence, the PRF has been doubled with respect to the Ku-band (Poseidon) instruments. AltiKa provides a PRF of about 4000 Hz adjustable along the orbit to cope with altitude variations in the surface profile.

3) The antenna has a smaller beamwidth due to the increase in signal frequency, thus providing a smaller footprint in the target area. At an orbital altitude of 800 km, the 6 dB footprint is around 8 km for AltiKa, compared to 30 km for Poseidon. Hence, more accurate measurements in the coastal regions can be expected (better discrimination in transition zones).

4) An innovative echo tracking concept is being employed based on an internally stored DEM (Digital Elevation Model) of the sub-satellite track (ocean and land surfaces) and on the use of the real-time satellite altitude information provided by the DORIS navigator software DIODE. These features help in providing altimetric measurements on surfaces where conventional closed-loop tracking solutions have difficulties to keep the echoes within the narrow range window.

The range measurement accuracy versus wave height is illustrated in Figure 13. The improvement for AltiKa compared to Poseidon-2 is in the order of 3.


Figure 13: Comparison in range measurement accuracies in Ka- and Ku-band (image credit: CNES)

Center frequency

35.75 GHz

Pulse bandwidth

480 MHz

Pulse length

107 µs

PRF (Pulse Repetition Frequency)

~ 4 kHz

SSPA (Solid?State Power Amplifier) output power

2 W (peak)

LNA (Low Noise Amplifier) noise figure

3.9 dB

SNR (Signal-to-Noise Ratio) for 6.5 σο (sigma naught)

11 dB

Antenna gain

49.3 dB

RF (Radio Frequency) losses (Tx & Rx)

2.2 dB

Atmospheric losses

3 dB

Table 2: Key parameters of the AltiKa instrument

Radiometer design: The instrument is a total power radiometer with a direct detection capability. It consists of two RF receivers, centered on 37 and 23.8 GHz, and a calibration unit enabling the connection of the receivers either to a sky horn pointing to provides a cold space reference, or to a load at ambient temperature (hot reference).

In the nominal mode, the radiometer receivers measure the antenna temperatures (RM1 to RM5). In the internal mode, the receivers are either connected to a sky horn pointing to deep space or to a load at ambient temperature. This internal calibration can be performed every few seconds.

Center frequencies

37 GHz (Ka-band)
23.8 GHz) (K-band)

Integration time

200 ms

Radiometric resolution

< 0.5 K

Radiometric accuracy

< 3 K

Dynamic range

120 -300 K (3 K calibration)

Antenna gains

K-band = 0 45.9 dB
Ka-band = 49.4 dB

Antenna beam efficiencies

K-band = 93.0 %
Ka-band = 97.7%

Table 3: Key radiometer parameters and performances


Figure 14: Illustration of the AltiKa antenna (CAD model), image credit: CNES

The critical technologies for AltiKa development concern the Ka-band functions except the radiometer receivers that are taken from the receivers of the Megha-Tropiques mission (ISRO/CNES). This includes:

• The multi-frequency antenna

• The Ka-band SSPA (Solid State Power Amplifier)

• The Ka-band LNA (Low Noise Amplifier)

• The Ka-band radiometer calibration unit

• The Ka-band altimeter duplexer equipment (ADE)

The AltiKa antenna (Figure 14) is a fixed offset reflector (1 m aperture diameter, 0.7 m focal length, 0.1 m offset) with a tri-band feed (35.5 - 36 GHz, 23.6 - 24 GHz, 36.5 - 37.5 GHz). The feed includes an OMT (Ortho-Mode Transducer) device for the separation of the altimeter and radiometer channels which use perpendicular polarizations, and a diplexer for the separation of the radiometer (K-band, Ka-band) channels.

The characteristics of the SSPA are the following: gain of 35 dB, useful bandwidth of 500 MHz, output power of 2 W (33 dBm). The power dies are being built in D01PH technology of OMMIC, France. The output combiner is in waveguide technology to minimize losses. All RF components of the SSPA are provided with a pulsed power converter to minimize power consumption and dissipation, and to decrease the junction temperatures of the components.


Figure 15: RF synoptic of the pulsed SSPA (image credit: CNES)

The real-time telemetry data rate of AltiKa (altimeter+ radiometer) is about 43 kbit/s.

RCU (Radiometer Calibration Unit). The RCU consists of two separate channels operating in the K- and Ka-bands. Two ferrite switches are provided in each channel to allow selection of one of the three different operational paths, corresponding to each of the operational modes. Each channel uses a very low VSWR waveguide load, which acts as the “hot” calibration source. Additionally, the Ka-band channel contains a bandpass filter to improve the isolation between the RCU channels and the altimeter.

The ADE (Altimeter Duplexer Equipment) consists of a single ferrite switch on the transmit path and four ferrite switches in the receive path. The transmit and receive paths are connected via a ferrite circulator which also provides a directional path to and from the antenna port. Two cross-guide couplers provide the calibration path. The RCU and the ADE are developed at COM DEV, UK.


Figure 16: View of the RFU instrumentation (image credit: COM DEV)


Figure 17: CAD view of the integrated AMU (Altimeter Microwave Unit), image credit: CNES


Mass (kg)

Volume (mm)

Power consumption (W)

ORA (Offset Reflector Antenna)


1230 x 1010 x 905


DPU (Digital Processing Unit)


230 x 300 x 250

< 29

AMU (Altimeter Microwave Unit)


325 x 305 x 250

< 39

RMU (Radiometer Microwave Unit)


180 x 170 x 50

< 4

RCU (Radiometer Calibration Unit)


300 x 240 x 80

< 3








< 75

Table 4: AltiKa instrument budgets


Ka channel

K channel





Radiometer integration time
(following pulse frequency and radar mode)

180 to 210 ms

200 ms

180 to 210 ms

200 ms

Antenna beam efficiencies





Sensitivity: (including antenna reflector contribution)

< 0.19 K

< 0.4 K

< 0.17 K

0.3 K

Absolute accuracy

< 0.44 K

< 2 K

< 0.4 K

< 2 K

Absolute accuracy
(including antenna reflector contribution)

< 1.3 K

< 3 K

1.0 K

< 3 K

Instrument linearity

> 99.92%

> 99.84%

> 99.94%

> 99.84%

Table 5: Main radiometer characteristics & performances (Ref. 26)


DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite):

DORIS is a dual-frequency tracking system (400 MHz and 2 GHz) based on network of emitting ground beacons spread all over the world. The DORIS on-board package is composed of:

• A dual-frequency antenna (omnidirectional antenna located on the nadir face of the satellite). The antenna has a mass of 2 kg and a size of 420 mm (length) and 160 mm in diameter.

• A BDR (DORIS Redundant Box) which is composed of two DORIS chains in cold redundancy accommodated inside the same electronic box. Each DORIS chain includes a MVR (Mesure de Vitesse radiale) unit achieving beacon' signal acquisition and processing, navigation, Doppler measurements storage and formatting, electrical satellite interfaces management functions, and a USO (Ultra-Stable Oscillator) delivering a very stable 10 MHz reference which is also used by the altimeter. BDR has a mass of 18 kg and a size of 390 mm x 370 mm x 165 mm.


Figure 18: View of the DORIS BDR and antenna (image credit: TAS-F)


LRA (Laser Retroreflector Array):

LRA is provided by CNES. The objective of LRA is to calibrate the precise orbit determination system and the altimeter system several times throughout the mission. The LRA is a passive system used to locate the satellite with laser shots from ground stations with an accuracy of a few millimeters. The reflective function is done by a set of 9 corner cube reflectors, with a conical arrangement providing a 150º wide field of view over the full 360º azimuth angle. 30) 31)

According to CNES optomechanical specifications, the LRA has been developed by Thales SESO (Société Européenne de Systèmes Optiques), Aix en Provence, France (SESO is a Thales group subsidiary as of 2011). The corner cube reflectors were provided with a very stringent dihedral angle error of 1.6 arcsec and an accuracy within ±0.5 arcsec.

During the development phase, SESO has performed mechanical, thermal and thermo-optical analyses. The optical gradient of each corner cube, as well as the angular deviations and PSF (Point Spread Function) in each laser range finding direction, have been computed. The mechanical and thermal tests have been successfully performed. A thermo-optical test has successfully confirmed the optical effect of the predicted in-flight thermal gradients. Each reflector was characterized to find its best location in the LRA housing and give the maximum optimization to the space telemetering mission.


Figure 19: Photo of the LRA with nine corner cubes (image credit: SESO, CNES)

Mass, dimensions

1.4 kg, 165 mm Ø x 67 mm height

FOV (Field of View)

> 150º

For each corner cube, cone with optical performances


Number of corner cubes


Clear aperture of corner cubes

30 mm

Table 6: Main characteristics of LRA

Corner cubes: The mean error is 0.17 arcsec and the maximum error is 0.42 arcsec! Due to this high accuracy, the real optical pattern will be very close to the model and within the required performances. The PSF has been characterized and analyzed for each corner cube. This verification has permitted to confirm their position and orientation. The qualitative and quantitative verifications have been made by comparing the measured PSFs with the simulated analysis values. The Figure 20 illustrates the analyses made.


Figure 20: Illustration of measured and simulated PSF values (image credit: SESO)




30 mm Ø x 24 mm height

Clear aperture of the corner cube

30 mm

Index of refraction at λ = 532 nm


Operational dihedral offset angle

1.5 arcsec


Ag coating

Radius of curvature of front face surface


Wavefront error

< 40 nm rms

Table 7: Main characteristics of the corner cubes



Argos-3 (Data Collection System):

Argos-3 of CNES, manufactured by TAS (Thales Alenia Space). The objective is to collect data from remote terminals in the ground segment referred to as PPTs (Platform Transmitter Terminals).

The Argos-3 onboard package represents the newest generation of the Argos system. The major improvement of the new Argos-3 system is that it will now be able to send orders to its terminals whereas before the onboard instruments were only capable of receiving data (up to Argos-2 inclusive). The MetOp-A spacecraft of EUMETSAT (launch Oct. 19, 2006) is carrying the first Argos-3 instrument demonstrator package. In comparison to previous generations, system performance is enhanced via a unique downlink and a high data uplink (4800 bit/s versus 400 bit/s), while insuring complete compatibility with existing systems in the ground segment. Thanks to digital processing, the new instrument is lighter and more compact than its predecessors on analog basis. Argos-3 is capable of receiving messages from over 1000 PTTs (Platform Transmitter Terminal) simultaneously within the satellite's FOV (Field of View). 32)

The Argos-3 onboard instrument is composed of the following components:

• The RPU (Receiver Processor Unit) providing the following functions:

- Processing of the received uplink signals

- Downlink management

- Interfaces with the receiver, the TxU and the satellite

• The TxU (Transmitter Unit) is sending the emissions (messages) to the PTTs in the ground segment including error-free message acknowledgement signals.

• The harness for the RPU to TxU connection

The RPU (16 kg, 36 W) and TxU (8kg, 26 W) boxes have a cold internal redundancy that can be activated by TC level. In the same way, the USO (Ultra Stable Oscillator) has a cold redundancy. RPU has dimensions of 365 mm x 280 mm x 365 mm, TxU has dimensions of 100 mm x 280 mm x 310 mm.

RPU (Receiver Processor Unit). The RPU onboard a spacecraft processes received uplink signals @ 401.6 MHz, measures the incoming frequency, time-tags the message, creates and buffers mission telemetry, manages the downlink and acts as interface between the receiver, the TxU (Transmitter Unit) and the satellite. Featuring fully digital processing, the RPU stores messages and either relays them in real-time to the nearest regional antenna - or in deferred time to a global center (maintained by NOAA, Eumetsat). A backup RPU is included as part of the device.


Figure 21: Illustration of the Argos-3 onboard instrument package (image credit: TAS-F)


Figure 22: Block diagram of the Argos-3 payload on SARAL (image credit: CNES)


Figure 23: SARAL project organization (image credit: CNES)



Ground segment:

According to the CNES-ISRO agreement: 33) 34) 35)

• CNES is responsible for the production, the archiving and the distribution of near-realtime altimetry products (OGDR: Operational Geophysical Data Record) and delayed products (GDR: Geophysical Data Record, IGDR, S-IGDR and S-GDR) to users outside India.

• Production of the mission preliminary and precise orbits is realized by CNES, from DORIS system data, completed by the laser system data, for the precise orbit. The operational upkeep of DORIS components and system is ensured by CNES.

• CNES uses EUMETSAT support for the operation of ground stations in Sweden, as well as to produce, archive and distribute near-realtime products to users outside India

• CNES supplies the near-realtime data processor to EUMETSAT and ISRO, as well as a support for its integration, test and operation

• CNES supplies the processor for delayed products to ISRO, as well as a support for its integration, test and operation

• ISRO is responsible for the production, the archiving and the distribution to Indian users of near-realtime and delayed-time altimetry products

• ISRO is responsible for the command-control operations of the satellite.

• All housekeeping and scientific telemetry as well as auxiliary data are archived by CNES and ISRO

• CNES and ISRO are responsible for the product enhanced value and the support to their respective users.

• CNES is responsible for the coordination of AltiKa with the other altimetry missions. The enhanced value products of DUACS (Data Unification and Altimeter Combination System) generated by CNES are archived and distributed under CNES responsibility.

• CNES is responsible for the expertise and the long term CalVal.


Figure 24: SARAL system overview (image credit: CNES)


Figure 25: The SARAL ground segment (image credit: CNES, Ref. 33)



3) J. Verron, F. Ardhuin, S. Arnault, P. Bahurel, F. Birol, P. Brasseur, S. Calmant, A. Cazenave, B. Chpron, J. F. Cretaux, P. De Mey, E. Dombrowsky, J. Dorandeu, L. Eymard, J. Lambin, J. M. Lefevre, B. Legresy, P. Y. Le Traon, F. Lyard, F. Mercier, E. Obligis, P. Sengenes, F. Seyler, N. Steunou, E. Thouvenot, J. Tournadre, “ARAL/AltiKa - An Altimetry mission in Ka-band,” 2010 OSTST (Ocean Surface Topography Science Team) meeting, Lisbon, Portugal, Oct. 18-20, 2010, URL:

4) P, Vincent, N. Stenou, E. Caubet, L. Phalippou, L. Rey, E. Thouvenot, J. Verron, “AltiKa: a Ka-band Altimetry Payload and System for Operational Altimetry during the GMES Period,” IEEE Sensors 2006, Oct. 22-25, 2006, EXCO, Daegu, Korea, pp. 208-234, URL:

5) P. Sengenes, “ALTIKA / SARAL mission overview & status,” ISRO-CNES AltiKa Joint Science and Application Workshop, 22nd – 24th April, 2009 - ISRO/SAC Ahmedabad - India

6) A. Guillot, J. Lambin, J. Verron, P. Sengenes, J. Noubel, N. Steunou, N. Picot, R. Gairola, R. Murthy, “The SARAL/ALtiKa Mission: A Ka-band Mission for Ocean Mesoscale Studies in 2012,” Proceedings of the Symposium '20 years of Progress in Radar Altimetry', Venice, Italy, Sept. 24-29, 2012, (ESA SP-710, Feb. 2013)

7) J. Verron, N. Steunou, P. Baruhel, P. Brasseur, A. Cazenave, L. Eymard, P. Y. Le Traon, F. Remy, P. Sengenes, J. Tournadre, E. Thouvenot, P. Vincent, “AltiKa: A Microsatellite Ka-band Altimetry Mission,” ESA Workshop, Venice, Italy, “15 Years of progress in Radar Altimetry Symposium,” March 13-18, 2006, URL:

8) P. Vincent, E. Thouvenot, N. Steunou, J. Verron, P. Bahurel, C. Le Provost, P. Y. Le Traon, E. Caubet, L. Phalippou, “AltiKa3 : A high resolution ocean topography mission,” Proceedings of IGARSS 2002 Symposium, Toronto, Canada June 24-28, 2002.

9) P. Vincent, “AltiKa: a ka-band altimetry payload to contribute in ocean and ice observing systems,” 34th COSPAR Scientific Assembly, The Second World Space Congress, Oct. 10-19, 2002, Houston, TX, USA.,

10) E. Thouvenot, “CNES program status,” Proceedings of the OSTST (Ocean Surface Topography Science Team) 2009 meeting, Seattle WA, USA, June 22-24, 2009, URL:

11) D. V. A. Raghava Murthy, P. Sengenés, “ISRO-CNES SARAL Mission,” 58th IAC (International Astronautical Congress), International Space Expo, Hyderabad, India, Sept. 24-28, 2007, IAC-07-B1.1.09

12) P. W. Bousquet, C. A. Prabhak, 58th IAC (International Astronautical Congress), International Space Expo, Hyderabad, India, Sept. 24-28, 2007, IAC-07-C2.1.08

13) D. V. A. Raghava Murthy, K. Suresh, K. Kalpana, P. Veeramuthuvel, M. Annadurai, Nitin D. Ghatpande, “SARAL - First mission on modular Multi Mission Mini Satellite Bus,” Proceedings of the 63rd IAC (International Astronautical Congress), Naples, Italy, Oct. 1-5, 2012, paper: IAC-12-B4. 6A.4

14) D. R. M. Samudraiah, D. V. A. Raghava Murthy, “Small Satellites planned by ISRO for Earth Observation,” 58th IAC (International Astronautical Congress), International Space Expo, Hyderabad, India, Sept. 24-28, 2007, IAC-07- B4.4.8

15) “PSLV - C20 successfully launches Indo-French satellite SARAL and six other commercial payloads into the orbit,” ISRO, Feb. 25, 2013, URL:

16) V. K. Dadhwal, “Recent Indian Space Miissiions: Update Feb 2014,” Proceedings of the 51st Session of Scientific & Technical Subcommittee of UNCOPUOS, Vienna, Austria, Feb. 11-22, 2014, URL:

17) “Saral, first verification workshop : main conclusions,” AVISO News, Sept. 5, 2013, URL:[tt_news]=1506&cHash=4f310d5ecff477de0dc9943125caa101

18) “The SARAL/AltiKa data are planned to be made available on EUMETCast, from 23 July 2013, as an early dissemination to users,” EUMETSAT, July 11, 2013, URL:

19) “SARAL/AltiKa Products Handbook,” CNES/EUMETSAT/ISRO, Issue 2, Rev. 2, June 18, 2013, URL:



22) “SARAL/AltiKa LATEST NEWS,” CNES, March 8, 2013, URL:

23) Jacques Richard, Benoit Durand, Frederic Robert, Nicolas Taveneau, Nathalie Stenou, Pierre Sengeres, “ALTIKA Instrument for Space Altimetry with Improved Performances and Ocean Sampling: Development Status and First Test Results,” Proceedings of IGARSS 2008 (IEEE International Geoscience & Remote Sensing Symposium), Boston, MA, USA, July 6-11, 2008

24) J. Richard, L. Phillippou, F. Robert, N. Stenou, E. Thouvenot, P. Senenges, “An Advanced concept of radar altimetry over oceans with improved performances and ocean sampling: AltiKa,” Proceedings of IGARSS 2007 (International Geoscience and Remote Sensing Symposium), Barcelona, Spain, July 23-27, 2007

25) J. Richard, E. Caubet, F. Robert, N. Stenou, E. Thouvenot, P. Senenges, “An Advanced concept of radar altimetry over oceans with improved performances and ocean sampling, AltiKa,” 58th IAC (International Astronautical Congress), International Space Expo, Hyderabad, India, Sept. 24-28, 2007, IAC-07-B1.3.06

26) Frédéric Robert, Jacques Richard, Benoît Durand, Nicolas Taveneau, Nathalie Steunou , Pierre Sengenès, “AltiKa, a Ka-band instrument for space altimetry with improved performances and ocean sampling: Instrument final test results,” Proceedings of the 2nd Workshop on Advanced RF Sensors and Remote Sensing Instruments 2009, Noordwijk, The Netherlands, Nov. 17-18, 2009

27) A. Guillot, J. Lambin, J. Verron, P. Sengenes, J. Noubel, N. Steunou, N. Picot, F. Robert, “The SARAL/AltiKa mission : a Ka-band mission for ocean mesoscale studies in 2012,” Proceedings of the 1st Workshop on Ka-and Earth Observation Radar, ESA/ESTEC, Noordwijk, The Netherlands, Oct. 8-9, 2012

28) Jacques Richard, Frédéric Robert, Nicolas Taveneau, Nathalie Steunou, Pierre Sengenès, “Integrated Altimeter / Radiometer AltiKa instrument for CNES/ISRO SARAL mission,” Proceedings of the 1st Workshop on Ka-band Earth Observation Radar, ESA/ESTEC, Noordwijk, The Netherlands, Oct. 8-9, 2012

29) “SARAL / AltiKa,” New Frontiers in satellite Altimetry, OSTST (2011 Ocean Surface Topography Science Team Meeting) 2011, San Diego, CA, USA, Oct. 19-21, 2011, URL:

30) Vincent Costes, Karine Gasc, Pierre Sengenes, Corinne Salcedo, Stephan Imperiali, Christian du Jeu, “Development of the Laser Retroreflector Array (LRA) for SARAL,” ICSO 2010 (International Conference on Space Optics), Rhodes Island, Greece, Oct. 4-8, 2010, URL:

31) Dennis Fappani, Deborah Dahn, Vincent Costes, Clement Luitot, “Thales SESO's hollow and massive corner cube solutions,” Proceedings of the ICSO (International Conference on Space Optics), Ajaccio, Corse, France, Oct. 9-12, 2012, Poster: ICSO-054

32) “Argos-3 on SARAL,” 43rd Argos OPSCOM, New London, CT, USA, June 2009, URL:

33) J. Noubel, P. Sengenes, “SARAL Project Overview - CNES Activities Progress Status,” 2nd SARAL-AltiKa Science Workshop, Ahmedabad, India, March 15-17, 2011, URL:


35) “Neelima Rani Chaube, Santanu Chowdhury, “SARAL Ground Segment & Data Products,” ISRO-CNES Joint SARAL-Altika Science & Application Workshop,” Ahmedabad, India, April 22-23, 2009

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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