Minimize ResourceSat-2


ResourceSat-2 is a data continuity mission of ISRO (Indian Space Research Organization) with improved spectral bands of the IRS-P6/ResourceSat-1. Each ResourceSat satellite carries three electrooptical cameras as its payload: LISS-3, LISS-4 and AWiFS. All the three imagers are multispectral pushbroom scanners with linear array CCDs as detectors. The ResourceSat data find their application in several areas like agricultural crop discrimination and monitoring, crop acreage/yield estimation, precision farming, water resources, forest mapping, rural infrastructure development, disaster management etc. ResourceSat-2 provides continuity and increases the observation timeliness (repetivity) in tandem with ResourceSat-1. 1) 2) 3) 4) 5)



Figure 1: Artist's view of the deployed configuration of the ResourceSat-2 satellite (image credit: ISRO)


The S/C mainframe is of IRS-1C/1D -P3 heritage (built by ISRO/ISAC, Bangalore). The S/C structure consists of two modules, the main platform and the payload module. The main platform is built around a central load bearing cylinder of 915 mm diameter and consists of four vertical panels and two horizontal decks. The bottom of cylinder is attached to an interface ring which interfaces with the launch vehicle. The vertical panels and the horizontal decks carry the subsystem packages.

The spacecraft is 3-axis stabilized using reaction wheels, magnetic torquers and hydrazine thrusters. Attitude is sensed with star sensors, Earth sensors, and gyros. Various attitude sensors, SPS (Satellite Positioning System) and data transmitting antennas are mounted on the outside surfaces of the equipment panels and the bottom deck. Two star trackers are mounted with skewed orientation on the top deck. The payload module in turn is comprised of a two-tier system, the payload module deck and the rotating deck.

The payload module deck accommodates LISS-3, AWiFS-A and AWiFS-B camera modules. The LISS-4 camera is mounted on a rotating deck which is attached to a PSM (Payload Steering Motor) which can rotate by ± 26º to provide an event monitoring capability. The entire payload module assembly is attached to a CFRP monocoque cylinder, which in turn is attached to the main cylinder of the main platform through a strut assembly for effective load transfer.


Figure 2: ResourceSat-2 spacecraft as view from -yaw (left) and as viewed from +yaw (right), image credit: ISRO

The overall S/C size is about 2 m in diameter and 2.1 m in height. The total S/C mass at launch is ~1200 kg, including fuel for five years of operation. Power is provided by a solar array generating 1250 W (EOL), the array is articulated into the sun; in addition there are 2 NiCD batteries with a capacity of 24 Ah each. The platform is three-axis stabilized [2 star sensors in loop, magnetic bearing reaction wheels, RCS (Reaction Control System) with 12 nozzles, 8 with 1 N thrusters, 4 nozzles with 11 N thrusters], the pointing accuracies are ±0.15º, the stability is 3 x 10-4 º/s. An onboard solid-state recorder (SSR) provides 400 Gbit capacity to store about 60 minutes of LISS-4 data. The S/C design life is 5 years.

RF communications: TT&C communications in S-band with downlink data rates of 1-16 kbit/s; modulation: PCM/PSK/PM. The uplink data rate is 100 bit/s. The TT&C transponder transmits the telemetry data, receives the telecommand signals, demodulate the ranging tones and re-transmits them to ground with a fixed turnaround ratio of 240/221 for two-way ranging (Doppler measurement). Uplink frequency: 2071.875 MHz, downlink frequency: 2250 MHz.

The payload data are transmitted in X-band at a data rate of 105 Mbit/s. The BDH (Baseband Data Handling) system consists of two separate chains, one for LISS-3 and AWiFS data, and the second chain for LISS-4 data. The LISS-4 data are transmitted on carrier-1 at 8125 MHz and LISS-3 + AWiFS data are transmitted on carrier-2 at 8300 MHz.

Mainframe system
S/C mass

- Al and Al honeycomb structure with CFRP elements for main platform and payload modules
- ~1200 kg

Thermal control
Payload instruments

Passive, semi-active and active elements like OSR (Optical Solar Reflectors), MLI (Multi-Layer Insulation), heat pipes, tape/foil heaters etc,.
5ºC ± 5º
20ºC ±3º

Power system
Solar array
Power electronics

- 6 Solar panels (1.4 x 1.8 m2 each) generate 1250 W of power at EOL
- 2 x 24 Ah NiCd batteries
- Two Raw buses 28 to 42 V; discrete and hybrid DC-DC converters

Attitude sensors

S/C pointing capability

- Earth sensors, digital sun sensors, star trackers, 4π sun sensors, gyroscopes AD accuracy 0.1º with Earth sensors 0.006º. with star trackers
- 4 reaction wheels (5 Nms); 8 x 1 N & 4 x 11 N hydrazine thrusters; 2 magnetic torquers
- Pointing accuracy: ≤ 0.05º (3σ); drift rate: ≤ 5 x 10-5 º/s (3σ)
- Spacecraft is steerable up to ±26º in cross-track

Table 1: Overview of ResourceSat-2 spacecraft parameters


Figure 3: Stowed configuration of ResourceSat-2 (image credit: ISRO)


Figure 4: Photo of the PSLV-16 integrated payloads of ResourceSat-2, X-Sat and YouthSat (image credit: ISRO) 6)


Launch: ResourceSat-2 was launched on April 20, 2011 on the PSLV-C16 launcher from SHAR (Satish Dhawan Space Centre, Sriharikota), India. The secondary payloads on this mission are: 7) 8)

• XSAT of NTU, Singapore

• YouthSat of ISRO and Roskosmos

Orbit: Sun-synchronous orbit, Altitude = 817 km, inclination = 98.78º, period = 101.35 minutes, local time of equator crossing at 10:30 AM on descending node. The ground track is maintained within ± 1 km, repeat cycle of 24 days. A phasing of 180º is realized with regard to the ResourceSat-1 satellite. 9)



Mission status:

• ResourceSat-2 and its payload are operating nominally in 2013.

- On May 7, 2013, ResourceSat-2 acquired flood waters in the Wasit Governorate of eastern Iraq. 10)

• An international team (USGS, ISRO, Science Systems and Applications Inc., Sigma Space Corporation) and NASA) performed a ResourceSat-2 data quality assessment by comparing near-simultaneous surface observations based on image statistics between RS-2 (ResourceSat-2) AWiFS and Terra and Aqua MODIS sensors. 11)

RS-2 AWiFS geometry assessment:

- Completed using the IAS (Image Assessment System) which was developed for radiometric and geometric characterization and calibration for the Landsat program.12)

- The RS-2 AWiFS data acquired over Sioux Falls, SD and Pueblo, CO were used for this study (a total of 4 AWiFS images over Sioux Falls and 2 images over Pueblo were used in this study).

- The positional accuracy was assessed by using the I2I registration assessment tool by comparing the RS-2 AWiFS imagery against the GLS-2005 (Global Land Surface-2005) dataset as a reference image (a total of 44 GLS images over Sioux Falls, SD Valley, and 17 images over Pueblo, CO were mosaicked and used as a reference).

Geometry assessment summary:

- RS-2 AWiFS preliminary analysis show discrepancies compared to the reference GLS dataset (this was confirmed by IAS and visual inspection)

- The RS-2 AWiFS data obtained from ISRO did not include GCP corrections to improve geometric quality, so we are working closely with ISRO to reevaluate the positional accuracy of RS-2 AWiFS data acquired outside India (Ref. 11).

• ResourceSat-2 and its payload are operating nominally in 2012. 13) 14)

• The ResourceSat-2 commissioning phase ended in late June 2011. On July 1, 2011, the mission became operational. 15)

• The first images of ResourceSat-2 were acquired on April 28, 2011 by ISRO.


Figure 5: LISS-4 sample image (Mx mode, 6 m) of the Sharjah International Airport of the United Arab Emirats observed on May 8, 2011 (image credit: ISRO/NRSC)


Figure 6: AWiFS image of part of the Krishna Basin, India, acquired on May 4, 2011 (image credit: ISRO/NRSC, Ref. #

Legend to Figure 6: The Krishna River (upper part of the image) is one of the longest rivers in central-southern India, about 1,300 km in length. It flows from west to east and empties in the Bay of Bengal in the state of Andhra Pradesh on the east coast of India. Ecologically, this is one of the most dangerous rivers in the world, in that it causes heavy flooding and soil erosion during the monsoon season.


Figure 7: AWiFS image of the Ganges–Brahmaputra basin, a river delta of Bengal, consisting of Bangladesh and the state of West Bengal, India (image credit: ISRO)

Legend to Figure 7: The Ganges-Bramaputra river delta is the world's largest delta, and empties into the Bay of Bengal. It is also one of the most fertile regions in the world, thus earning the nickname The Green Delta. It covers more than 105,000 km2. Between 125 and 143 million people live on the delta, despite risks from floods caused by monsoons, heavy runoff from the melting snows of the Himalayas, and tropical cyclones. A large part of the nation of Bangladesh lies in the Ganges Delta, and many of the country's people depend on the delta for survival. The total river basin covers an area of 1.7 million km2, distributed between India (64%), China (18%), Nepal (9%), Bangladesh (7%) and Bhutan (3%).


Figure 8: LISS-3 first-day image of Dubai, Palm Islands and Environs (image credit: ISRO, Ref. 17)

• Immediately after the injection of the satellite, the two solar panels were deployed. The three Imaging Cameras have been oriented towards Earth. All operations and health checks required prior to switching on the three Imaging Cameras have been satisfactorily completed (Ref. 7). 16)

- An orbital trimming maneuver was conducted successfully on April 22, 2011, and ResourceSat-2 is now placed in the final orbital configuration in a sun-synchronous polar orbit with perigee of 813 km; apogee of 825 km and inclination of 98.78º.



Sensor complement: (LISS-4, LISS-3, AWiFS, HIP-1)

The sensor complement is identical to that of the ResourceSat-1 mission. There are two AWiFS cameras, AWiFS-A and AWiFS-B, providing a combined swath width of 740 km. The data quantization of all sensors has been improved to 10 bit. In addition, the MS swath of LISS-4 has been increased to 70 km (from 23.9 km on ResourceSat-1). Radiometric improvements have been carried out in all the payloads of ResourceSat-2 using either DPCM (Delta Pulse Code Modulation) or MLG (Multi Linear Gain).

17) 18)


All the three cameras are observing in the ‘pushbroom scanning’ concept using linear arrays of CCDs (Charge Coupled Devices). In this mode of operation, each line of image is electronically scanned and contiguous lines are imaged by the forward motion of the satellite.





Spatial resolution or IFOV (Instantaneous Field of View)

≤ 5.8 m

23.5 m

56 m (nadir)
(70 m a swath edge)

Spectral bands (µm)

B2: 0.52-0.59, (green)
B3: 0.62-0.68, (red)
B4: 0.77-0.86 (NIR)
B3-default band for mono

B2: 0.52-0.59, (green)
B3: 0.62-0.68, (red)
B4: 0.77-0.86, (NIR)
B5: 1.55-1.70 (SWIR)

B2: 0.52-0.59, (green)
B3: 0.62-0.68, (red)
B4: 0.77-0.86, (NIR)
B5: 1.55-1.70 (SWIR)

Swath width

70 km in PAN and MS mode

141 km

740 km

Detector line arrays x No of elements

1 x 12,288 PAN mode
3 x 12,288 MS mode

4 x 6,000

4 x 2 x 6,000

Data quantization

10 bit

10 bit (VNIR),
10 bit (SWIR)

10 bit

Square wave response at Nyquist

> 20

B2> 0.40, B3> 0.40
B4> 0.35, B5> 0.20

B2> 0.40, B3> 0.40
B4> 0.35, B5> 0.20

Power consumption

216 W

70 W

114 W

Instrument mass

169.5 kg

106.1 kg

103.6 kg

Date rate

105 Mbit/s

52.5 Mbit/s

52.5 Mbit/s

Table 2: Summary of the ResourceSat-2 instrument parameters


Figure 9: ResourceSat-2 three tier imaging and swath coverage (image credit: ISRO)


LISS-4 (Linear Imaging Self-Scanning Sensor-4):

The LISS-4 multispectral high-resolution camera is the prime instrument of this sensor complement. LISS-4 is a three-band pushbroom camera of LISS-3 heritage (same spectral VNIR bands as LISS-3) with a spatial resolution of 5.8 m and a swath of 70 km. LISS-4 can be operated in either of two support modes: 19)

• Multispectral (MS) mode: Data is collected in 3 bands corresponding to pre-selected 4096 contiguous pixels with a swath width of 23.9 km (selectable out of 70 km total swath). Note: the new swath width of LISS-4 is 70 km for band 3 - but in mono mode only.

• Mono mode: Data of the full 12 k pixels of any one single selected band, corresponding to a swath of 70 km, can be transmitted. Nominally, band-3 data (B3) are being observed and transmitted in this mode.

LISS-4 features in addition a ±26º steering capability in the cross-track direction permitting a 5-day revisit cycle. The optoelectronic module of LISS-4 is identical to that of the PAN camera of IRS-1C/1D. The CCD array features 12,288 elements for each band. The instrument has a mass of 169.5 kg, power of 216 W, and a data rate of 105 Mbit/s. The detector temperature control is implemented using a radiator plate coupled to each band CCD through heat pipes and copper braid strips.


Figure 10: Photo of the LISS-4 camera (image credit: ISRO)

The LISS-4 camera is realized using the three mirror reflective telescope optics (same as that of the PAN camera of IRS-1C/1D) and 12,288 pixels linear array CCDs with each pixel of the size 7 µm x 7 µm. Three such CCDs are placed in the focal plane of the telescope along with their individual spectral bandpass filters. An optical arrangement comprising an isosceles prism is employed to split the beam into three imaging fields which are separated in the along track direction. The projection of this separation on ground translates into a distance of 14.2 km between the B2 and B4 image lines. While B3 is looking at nadir, B2 is looking ahead and B4 is looking behind in the direction of velocity vector. Detector type: THX31543A of Thomson.

LISS-4 calibration: An in-flight calibration scheme is implemented using LEDs (Light Emitting Diodes). Eight LEDs positioned in front of the CCD (without obstructing the light path during imaging). These LEDs are driven with a constant current and the integration time is varied to get 16 exposure levels, covering the dynamic range in a sequential manner. This sequence repeats in a cyclic form.


LISS-3 (Linear Imaging Self-Scanning Sensor-3):

LISS-3 is a medium-resolution multispectral camera. The pushbroom instrument is identical to LISS-3 on IRS-1C/1D (with regard to lens modules, detectors, and electronics) in the three VNIR bands, each with a spatial resolution of 23.5 m. The resolution of the SWIR band is now also of 23.5 m on a swath of 140 km. The optics design and the detector of the SWIR band are modified to suit the required resolution; B5 uses a 6,000 element Indium Gallium Arsenide CCD with a pixel size of 13 µm. The SWIR CCD is a new device employing a CMOS readout technique for each pixel, thereby improving noise performance. The VNIR CCD array features 6,000 elements for each band. The instrument has a mass of 106.1 kg, a power consumption of 70 W, and a data rate of 52.5 Mbit/s.

The in-flight calibration of the LISS-3 camera is carried out using 4 LEDs per CCD in the VNIR bands and 6 LEDs for the SWIR band. These LEDs are operated in pulsed mode and the pulse duration during which these LEDs are ON is varied in specific steps. Each LED has a cylindrical lens to distribute the light intensity onto the CCD. Each calibration cycle consists of 2048 lines providing six non zero intensity levels.


Figure 11: Photo of the LISS-3 camera (image credit: ISRO)


AWiFS (Advanced Wide Field Sensor):

AWiFS is a wide-angle medium resolution (56 m) camera with a swath of 740 km (FOV=±25º) of WiFS heritage. The pushbroom instrument operates in three spectral bands which are identical to two VNIR bands (0.62 - 0.68 µm, 0.77 - 0.86 µm) and the SWIR band (1.55-1.70 µm) of the LISS-3 camera. The AWiFS camera is realized using two separate optoelectronic modules which are tilted by 11.94º with respect to nadir. Each module covers a swath of 370 km providing a combined swath of 740 km with a side lap between them. The wide swath coverage enables AWiFS to provide a five-day repeat capability. The optoelectronic modules contain refractive imaging optics along with band pass interference filter, a neutral density filter and a 6000 pixels linear array CCD detector for each spectral band.

The in-flight calibration is implemented using 6 LEDs in front of each CCD. For the VNIR bands (B2, B3, B4), the calibration is a progressively increasing sequence of 16 intensity levels through exposure control. For the SWIR band, the calibration sequence is similar to that of LISS-3 through a repetitive cycle of 2048 scan lines.


Figure 12: Photo of the AWiFS camera assembly (image credit: ISRO)


PDHS (Payload Data Handling System):

The PDHS receives the digital data from each camera in bit parallel - byte serial mode, formats it with auxiliary data, modulates it on the RF carrier and transmits to the ground. Like ResourceSat-1 spacecraft, ResourceSat-2 also has two separate downlink chains in X-band, both operating at 105 Mbit/s data rate. Unlike ResourceSat-1, where each chain was dedicated to LISS-4 and LISS-3/AWiFS, in ResourceSat-2, there exists flexibility of downlinking payload data through any one of the chains. The PDHS of the ResourceSat-2 spacecraft essentially consists of two subsystems – BDH (Baseband Data Handling) and the X-band data transmission system (Ref. 18).

BDH subsystem: The BDH receives LISS-3, LISS-4 and AWIFS payload data, formats them suitably along with auxiliary information and send the data to X-band or SSR system for downlink transmission or recording, respectively.

BDH for LISS-4 camera: The LISS-4 camera features three bands B2, B3, B4, the output is encoded according to DPCM (Differentially Pulse Code Modulation). DPCM encodes ten bit pixel information into seven bits. BDH for the LISS -3 formatter receives seven bit DPCM encoded data, multiplexes the different band data, and formats them into frames along with auxiliary information.

The frame data is RS (Reed Solomon) encoded, randomized, and differentially encoded for transmission. There are different modes by which the LISS-4 data may be downloaded. Like its predecessor ResourceSat-1, there exists downloading of data either in mono or 23 km Mx mode. Mono mode provides 70 km of swath and any one of the band may be selected for download. In the 23 km Mx mode, all three bands for a swath 23 km from a selected position in 70 km may be downloaded. An additional 70 km Mx mode exists in ResourceSat-2, when compared to ResourceSat-1. In this mode one of the band data is transmitted in real-time and other two are recorded for later down-loading through both chains of RF. In case of ground station non-visibility, all the three bands may be recorded and played back according to station availability.


Figure 13: Block diagram of the PDHS (image credit: ISRO)


HIP-1 (Hosted Indian Payload):

HIP-1 is an (auxiliary) AIS (Automatic Identification System) payload of COM DEV International Ltd., Cambridge, Ontario, Canada. The objective is to collect AIS signals from the ground segment and to transmit the information to ground stations. 20) 21)

• HIP-1 is a payload of Resource Sat-2 (ISRO)

• Two polarizations / 4 channels

• S-band data downlink (frequency: 2.280 MHz, output power = 5 W, modulation = QPSK, data rate = 16 Mbit/s).

A MoA (Memorandum of Agreement) has been signed between Antrix/ISRO and COM DEV Canada according to the following terms:

- An AIS payload of COM DEV will be a hosted payload on-board the ResourceSat-2 spacecraft

- COM DEV will supply the VHF receiver & data processing S/W – ISRO will supply the S-band transmitter,VHF antennas, an S-band antenna and a filter

- COM DEV will supply to ISRO AIS data of all ships over Indian waters & all Indian flag ships over Global seas for usage by Indian users

- The AIS data will be received by ISRO ground station (ISTRAC) & COM DEV G/S (Svalbard). COM DEV will install processing S/W at ISRO G/S to process the data and send it to COM DEV, Canada

- ISTRAC will disseminate the AIS data and make it available to various Indian users.

AIS payload:

• Operating in the VHF maritime band (160 -162 MHz)

- standardized digital communication protocols

- each station transmits and receives over two radio channels to avoid interference problems

• Transmissions use 9.6 kbit/s with GMSK/FM modulation

• Uses SOTDMA (Self-Organizing Time Division Multiple Access) technology to meet this high broadcast rate and ensure reliable ship-to-ship operation

- Each station determines its own transmission schedule (slot), based upon data link traffic history and knowledge of future actions by other stations.


Figure 14: Photo of the HIP-1 payload (image credit: COM DEV)


Figure 15: Schematic view of the AIS payload (image credit: COM DEV, ISRO)


AIS Payload Operations:

• Payload operations are independent of ResourceSat-2 hosted payload operations

• Payload operated as per COM DEV requirement

• Data processing locally and sent to DOC (Data Operation Center), Canada

• Data is to be acquired in 39 minutes per orbit (40 %) or 100% based on requirement

• 10 segments / orbit. (1 acquisition unit = 99 seconds)

• Data acquisition over pre-determined segments of an orbit uplinked as acquisition profile

• Acquisition profile to be uplinked for every orbit

• Receivers will be switched on/off based on the profile command (1/0)

• Profile holds good till another profile is uplinked

• Data to be downloaded over 2/3 stations: Svalbard, Bangalore (ISTRAC), TBD

• Download over stations by issuing S-band on & off command from the receiver.


Figure 16: High level system level interface of HIP (image credit: ISRO, COM DEV)

Applicable standard

MSC.74(69) Annex 3, IEC 61993-2 (Draft), ITU-R M.1371-1

Radio frequencies

AIS1: 161.975 MHz
AIS2: 162.025 MHz

Channel spacing

12.5 kHz/25 kHz

Output power

12.5 W/2W


GMSK (Gaussian Minimum Shift Keying)

Bit rate

9600 bit/s ±30 ppm


SOTDMA, (UTC Indirect, Synchronization to base station)

Time slot

2250 slots/min (1 slot = 256 bit)

Table 3: AIS specifications


2.280 GHz

Output power

5 W


QPSK (Quadra-Phase Shift Keying)

Data rate

16 Mbit/s

Table 4: S-band Tx specifications

1) Marappa Krishnaswamy, “Future Remote Sensing Missions of ISRO,” Proceedings of the 59th IAC (International Astronautical Congress), Glasgow, Scotland, UK, Sept. 29 to Oct. 3, 2008, IAC-08.B1.1.6

2) M. Venkata Rao, J. P. Gupta, Ram Rattan, K. Thyagarajan, “ResourceSat-2: a mission for Earth resources management,” Proceedings of SPIE, 'GEOSS and Next-Generation Sensors and Missions,' Vol. 6407, Panaji, Goa, India, Nov. 13-17, 2006, DOI:10.1117/12.697973,

3) Virender Kumar, “Indian Remote Sensing Satellites - Current and Future Missions,” PECAD 2007 (Production Estimates and Crop Assessment Division), July 16, 2007, URL:

4) Timothy J. Puckorius, “Indian Remote Sensing Satellites - Current & Future ResourceSat Missions,” Proceedings of JACIE 2007 (Joint Agency Civil Commercial Imagery Evaluation Workshop, March 2007, URL:

5) Deviprasad Karnik, “ResourceSat-2 Mission Status,” JACIE (Joint Agency Commercial Imagery Evaluation Workshop, Fairfax, VA, USA, March 16-18, 2010, URL:


7) “PSLV-C16 Flight Successful: RESOURCESAT-2, YOUTHSAT and X-SAT Satellites Functioning Satisfactorily,” ISRO Press Release, April 25, 2011, URL:


9) Brochure of PSLC-16, ISRO, URL:

10) “Food Waters over Wasit Governorate, Republic of Irak,”UNITAR/UNOSAT, May 9, 2013, URL:

11) Gyanesh Chander, Amit Angal, Aparajithan Sampath, A. Senthil Kumar, Taeyoung (Jason) Choi, Xiaoxiong (Jack) Xiong, Greg Stensaas, “ResourceSat-2 AWiFS Preliminary Data Quality Assessment,” 12th Annual JACIE (Joint Agency Commercial Imagery Evaluation) Workshop , St. Louis, MO, USA, April 16-18, 2013, URL:

12) “PSLV-C16 Successfully Launches RESOURCESAT-2, YOUTHSAT and X-SAT Satellites,” ISRO Newsletter, April-December 2011, URL:

13) M.Venkata Rao, “Present and Future Earth Observation (EO) Satellites,” User Interaction Meeting, NRSC (National Remote Sensing Center), Hyderabad, India, Feb. 16-17, 2012, URL:

14) D. Gowrisankar, ISRO delegation, “Recent Applications of ResourceSat-2,” Proceedings of the 49th Session of UNCOPUOS-STSC (UN Committee on the Peaceful Uses of Outer Space-Scientific and Technical Subcommittee), Vienna, Austria, Feb. 6-17, 2012, URL:

15) Information provided by Rajeev Kumar Jaiswal of ISRO/HQ, EOS/NNRMS Programme Office, Bangalore, India

16) Space India, Newsletter, ISRO, April-December 2011, URL:

17) V. S. Hedge, “ResourceSat-2: Continuing global services in Earth Observation,” 54th UN-COPOUS (United Nations Committee on the Peaceful Uses of Outer Space), Vienna, Austria, June 1-10, 2011, URL:

18) “ResourceSat-2 Data User's Handbook,” ISRO/NRSC, Dec. 2011, Doc. No.: NRSC:SDAPSA:NDC:DEC11-364

19) R. S. Ramayanam, “Indian Remote Sensing Satellites ResourceSat-1 (IRS P6) & CartoSat-1 (IRS P5),Data Availability,” URL:

20) Elliott Coleshill, “AIS: Technology Development to Commercialization,” NSAW (National Space Awareness Workshop), Ottawa, Canada, Nov. 19, 2010, URL:

21) “Automatic Identification System on-board ResourceSat-2,” National User Meeting, SB-AIS, ISTRAC, Bangalore, September 25, 2010

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.