Indian Space Capabilities

[In God We Trust]

ISRO conducts scramjet passive flight test

ISRO conducted the first unpowered flight test of the Scramjet engine that it is developing under the Reusable Launch Vehicle (RLV) technology demonstrator program.

The test was conducted at Sriharikota space-port using a sounding rocket and described by ISRO as a complete success.

The Advanced Technology Vehicle (ATV) - booster combination weighed 3 tons.

The booster accelerated the passive scramjet to Mach 6 and sustained Mach 6 +.05 and dynamic pressure 80 + 35 kPa for seven seconds. These conditions are required for a stable ignition of active scramjet engine combustor module planned in the next flight of ATV.


ATV-D01 on launch pad. Photo Credit: ISRO


ATV-D01 takes off. Photo Credit: ISRO

 

[blueoval79]

India plans to launch 10 satellites every year


Indian space scientists and engineers are bracing up to launch an average of 10 satellites per year to meet the rising demand for various space applications, including communications and remote sensing, a top space scientist said.

'We are planning to launch 10 satellites per year, beginning fiscal 2010-11. We have a series of satellites and launch vehicles at various stages of preparation,' Indian Space Research Organisation (ISRO) chairman K. Radhakrishnan told IANS.

Though the state-run space agency was to launch five satellites in this fiscal (2009-10), it could launch only three -- Oceansat-2, Risat-2 (radar imaging satellite) in association with Israeli Aerospace Industries, and Anusat, a micro-satellite. Oceansat-2 also carried six nano-satellites of foreign countries as additional payloads.

The launch of two satellites -- GSAT-4 and Cartosat-2B -- got delayed due to unavoidable reasons, one of them being further flight duration tests of 800 seconds (13.3 minutes) conducted for the indigenous cryogenic engine to be used for the first time in the heavy rocket GSLV-D3 (geo-synchronous satellite launch vehicle).

Hitherto, the space agency used Russian cryogenic engines in heavy rockets for launching above two-tonne class spacecraft.

'We have concluded our review meetings to launch satellites for communications and remote sensing. In the immediate, we are launching one satellite in April and another in May. Our target date for launch of GSAT-4 is mid-April and we are working towards it,' Radhakrishnan said.

The space agency is set to keep the window open April 15-19 for launching the 2.2-tonne GSAT-4 onboard GSLV-D3 from its Satish Dhawan space centre at Sriharikota in Andhra Pradesh, about 80 km north-east of Chennai.

The space centre is scheduled to move the 440-tonne rocket to the second launch pad at the spaceport April 7-8 with the technology demonstrator satellite (GSAT-4).

'Early May, we plan to launch the polar satellite launch vehicle (PSLV-C15) to carry Cartosat-2B, an Algerian satellite, and two micro satellites -- Youthsat from Canada and Studsat built by college students from Karnataka,' the chairman said.

The GSAT-4 will be launched into the geo-stationary transfer orbit (GTO) using the cryogenic upper stage of the GSLV-D3.

'As an advanced communication satellite, the GSAT-4 will have multibeam Ka-band regenerative transponders. It will also carry GPS (global positioning system) augmented navigation system in C, L1 and L5 bands as an additional payload,' Radhakrishnan, a rocket scientist, noted.

As part of its advance preparation, ISRO is also working on launching a Resourcesat-2, Risat-1 and Mega-Tropiques in the remote sensing area during the later part of this year.

'In the communications area, we are lining up three heavy satellites -- GSAT-5 and GSAT-6 from Sriharikota and GSAT-8P onboard the Ariane launch vehicle from Korou in French Guayana -- by this year-end or early 2011,' Radhakrishna said.

ISRO plans to put up Hylas satellite of its commercial arm Antrix before March 2011.

Noting that demand for multiple satellites in communications and remote sensing areas would increase in the coming years to meet the diverse needs of a booming economy, the chairman said the space agency was preparing to launch 10-12 satellites a year hereafter.

'In fiscal 2011-12 too, we plan to launch about 10 satellites, including Saral, Insat-3D, GSAT-9, GSAT-12, GSAT-10P, IRNSS 1& 2 (Indian Regional Navigation Satellite System), Astrosat and Aditya-1,' Radhakrishnan pointed out.

ISRO uses the Indian National Satellite (INSAT) series for telecommunication, television broadcasting and meteorological services and Indian Remote Sensing (IRS) satellites for resources monitoring and management.

The PSLV is used for launching remote sensing satellites into polar orbits and GSLV for launching communication and meteorological satellites into geo-synchronous transfer orbit.

'For launching four-tonne class satellites into GTO, we are developing GSLV-Mark III. We have already carried the static testing of the advance rocket's solid booster, which will be the third largest of its kind in the world,' he added.

India plans to launch 10 satellites every year

 

[Kinetic]

Indian Space Research Organisation (ISRO)



ISRO annual report 2010

Space Transportation

The Indian Space Programme started in a humble way with the launch of modest Rohini sounding rockets from Thumba near Thiruvananthapuram in the early 1960s. Initially, these sounding rocket launches were aimed at conducting scientific investigations over the geomagnetic equator passing over Thumba. Since then, India has made rapid strides in launch vehicle technology to achieve self reliance in satellite launch vehicle programme with the operationalisation of Polar Satellite Launch Vehicle (PSLV) and Geosynchronous Satellite Launch Vehicle (GSLV).

During the year two PSLV missions PSLV-C12 and PSLV-C14 putting RISAT-2 and Oceansat-2 in the precise orbits along with other small satellites as co-passenger payloads was successfully accomplished. ISRO is now gearing up for launch of GSLV-D3/GSAT-4 with indigenous Cryogenic Upper Stage (CUS) and PSLV-C15/Cartosat-2B launch.

PSLV-C12
In its fifteenth flight conducted from Satish Dhawan Space Centre (SDSC) SHAR, Sriharikota on April 20, 2009, PSLV-C12 successfully launched the 300 kg RISAT-2 and 42 kg ANUSAT, a satellite built by Anna University, Chennai, into a 550 km high polar Sun Synchronous Orbit inclined at an angle of 41 deg to the equator. PSLV-C12 was the fourth flight of the PSLV's ' core alone' version. In this flight, two new generation Avionic Systems Advanced Mission Computer (AMC) and Advanced Telemetry System (ATS) were inducted. Weighing 230 tonnes at lift-off, the vehicle was flown without the six 'strap-on motors' used in its standard configuration. PSLV is a four stage launch vehicle employing both solid and liquid propulsion stages. PSLV is the trusted workhorse launch Vehicle of ISRO.

PSLV-C12 lift-off



PSLV-C14
Polar Satellite Launch Vehicle (PSLV-C14) carrying 960 kg Oceansat- 2 satellite and six nanosatellites for International customers as auxiliary payloads, was successfully launched on September 23, 2009 into a polar Sun Synchronous Orbit of 720 km height. During this flight too, PSLV was flown in its 'core alone' version. This was the fifteenth consecuviely successful flight of PSLV.

With the successful launch of PSLV-C14, PSLV once again proved its reliability and versatility by launching 39 spacecraft (17 Indian and 22 for international customers) into a variety of orbits during 1994-2009 period.

Today, PSLV has emerged as a versatile, reliable and cost-effective launch vehicle. Its launch capability has been progressively enhanced from 850 kg to 1500 kg through continuous improvements in the launch vehicle.

PSLV-C14 lift-off carrying seven satellites

Geosynchronous Satellite Launch Vehicle (GSLV)
ISRO's Geosynchronous Satellite Launch Vehicle (GSLV), in its first operational flight (GSLV-F01), launched 1950 kg EDUSAT, India's first exclusive satellite for educational services, from Satish Dhawan Space Centre, SHAR, Sriharikota on September 20, 2004.

GSLV was declared operational after both its developmental test flights conducted in April 2001 and May 2003 were successful.

For the 49 metre tall, 414 tonne, GSLV first stage, GS1, comprises a core motor with 139 tonne of solid propellant and four strap-ons each with 40 tonne of hypergolic liquid propellants (UH25 and N204). The second stage has 39 tonne of the same hypergolic liquid propellants. The third stage (GS3) is a cryogenic stage with 12.5 tonne of Liquid Oxygen (LOX) and Liquid Hydrogen (LH2). The Composite Fibre Reinforced Plastic (CFRP) GSLV payload fairing is 4 m in diameter and is 8 m long.

All the GSLV Missions flown so far utilised cryogenic stage (CS) procured from Russia. The GSLV-D3 is the third developmental Mission of GSLV. The main significance of this mission is the usage of the indigenously developed Cryogenic Upper Stage (CUS) in place of bought out Cryogenic Stage (CS) from Russia.

PAM-G stage undergoing hot test

During the year, Advanced Mission Computer (AMC) and Advanced Telemetry System (ATS) packages were realised, qualified and assembled in the vehicle subsystems. These packages will be inducted for the first time into GSLV programme from GSLV-D3 flight onwards.

All qualification tests of 4m diameter Composite payload fairings were successfully completed. Also hot test of Payload Assist Module GSLV (PAM-G) was successfully completed in August 2009. Launch of GSLV D3 is scheduled during 2010.

GSLV-F06
Preparations for the flight of Geosynchronous Satellite Launch Vehicle (GSLV-F06) carrying INSAT-3D is in advanced stage of realisation. The GSLV-F06 is expected be launched during 2010-11.

Second stage of GSLV-D3 under preparation

Cryogenic Upper Stage Project (CUSP)
The major achievement during 2009 was the delivery of Cryogenic Upper Stage (CUS) in September 2009 after its successful flight acceptance testing during which CUS was hot tested for 720 seconds. The flight model of cryogenic engine was tested for duration of 200 seconds and test results met all the specified parameters.

Indigenous Cryogenic Upper Stage

The development of cryogenic engines involves mastering materials technology, operating rotary pumps and turbines that run at 42,000 rpm at cryogenic temperatures. The successful testing of CUS has enabled the country to achieve total self-reliance in launch vehicle technology.

The indigenous cryogenic engine develops a thrust of 73 kilo Newtons (kN) in vacuum with a specific impulse of 454 seconds and provides a payload capability of 2200 kg to Geosynchronous Transfer Orbit (GTO) for GSLV. The Engine works on 'Staged Combustion Cycle' with an integrated turbo pump running at around 42,000 rotations per minute (rpm). It is also equipped with two steering engines developing a thrust of 2 kN each to enable three-axis control of the launch vehicle during the mission. Another unique feature of this engine is the closed loop control of both thrust and mixture ratio, which ensures optimum propellant utilisation for the mission.

GSLV-Mk III
GSLV-Mk III is envisaged to launch a four tonne satellite into Geosynchronous Transfer Orbit. GSLV-Mk III is a three-stage vehicle with a 110 tonne core liquid propellant stage (L-110) and a strap-on stage with two solid propellant motors, each with 200 tonne propellant (S-200). The upper stage will be cryogenic with a propellant loading of 25 tonne (C-25). GSLV- Mk III will have a lift-off weight of about 629 tonne and will be 42.4 m tall. The payload fairing will have a diameter of 5 metre and a payload volume of 100 cubic metre.

L110 development stage

GSLV MkIII programme is presently in the hardware testing and qualification stage. The project has entered the phase of stage level tests for propulsion modules with the successful static test of S200 on January 24, 2010.

CE20 Integrated Turbopump Hot Test in progress

L110 development stage functional integration has been completed. Structural test facility for propellant tanks commissioned at SDSC, SHAR. Preparation and assembly of L110 stage for long duration hot test is progressing well at LPSC, Mahendragiri.

Indigenously developed turbo pump system of CE20 engine was successfully tested in integrated pressure fed mode for 60 seconds. First launch of GSLV Mk III is expected during 2011-12.

 

[Kinetic]

Space capsule Recovery Experiment (SRE-2)
SRE-2 is proposed to be launched onboard PSLV-C19 in of 2010 - 11. The main objective of this mission is to realise a fully recoverable capsule and provide a platform to conduct microgravity experiments.

SRE-2 carries six new payloads - Advanced Isothermal Heating Furnace (IHF) to study the effect of microgravity on liquid phase sintering of powder metallurgy products and processing Carbon nanotube, CCMB Bioreactor to study the effect of microgravity on gene expression of E-coli bacteria, Langmuir Probe for Electron density measurement, Dosimeter for orbital radiation measurement, JAXA payload for Cyanobacteria growth and Biopa payload to study growth and gene expression of seeds.

SRE-2 capsule has four major hardware: Aero Thermostructure (ATS), Spacecraft platform, deceleration and floatation system and six new payloads. New systems developed for SRE 2 include Carbon-Carbon Nose Cone, and indigenous Beacons.

Sounding Rockets
The department has developed a series of sounding rockets known as Rohini (RH) with diameters ranging from 200 to 560 mm and capable of carrying upto 200 kg payload to 300-400 km altitude for conducting scientific experiments. Two RH560-MkII, five RH300 MkII and four RH 200 motor systems were launched during the Annular Solar Eclipse of January 2010.

Semi Cryogenic Engine Development (SCED)
Semi-Cryogenic Engine development envisages the development of a high thrust engine producing 2000 kN (Vacuum) thrust with Liquid Oxygen and kerosene propellant combination for the Common Liquid Core in Unified Launch Vehicle (ULV). As part of semi-cryo engine development pre-project activities, five designs of single element pre-burner injector were realised and tested. Semi-cryo Project Report was prepared and clearance obtained. Conceptual design of the semi cryo engine has been completed.

Advanced Technology Vehicles
Research and development activities in semi-cryogenic propulsion stages, air breathing propulsion and re-usable launch vehicle technology are also being pursued vigorously by the department in an effort towards reducing the cost of access to space.

Air Breathing Rocket Systems use atmospheric oxygen from the surroundings and burn it with the stored on-board fuel for producing the forward thrust in contrast to the conventional chemical rocket systems, which carry both the Oxygen and fuel on board. As a result, air-breathing systems become much lighter and more efficient leading to reduced overall costs.

Air Breathing Propulsion, along with Reusable Launch Vehicle Technology will lower cost of space access drastically. Scramjet engine with supersonic combustion is identified as the most critical element in Air Breathing propulsion technology.

As the Air-Breathing Systems have the capacity to operate only during the atmospheric phase of flight, they always have to be adopted along with conventional chemical rockets for meeting the final orbital velocity requirements. Air-Breathing engines like the turbojet engines used in aircraft have limitations of operating only upto a maximum of Mach number 3. To travel from Mach number 3 to 6, a RAMJET is used. Beyond Mach number 6, SCRAMJET propulsion is the only viable option.

The development of a SCRAMJET System is complex and it involves a number of technological challenges, especially those related to the mixing of very high speed air (velocity around 1.5 km/s) with fuel, achieving stable ignition and flame holding in addition to ensuring efficient combustion within the practical length of combustor. Supersonic combustion was successfully achieved in ground testing.

During the year, hypersonic air intake models were studied in wind tunnels simulating high flight velocities and supersonic combustor configuration was firmed up for first Scramjet flight. Full engine simulation with combustion was also carried out.

Advanced Technology Vehicle (ATV)
The two stage vehicle with RH560 M motor for first stage (Booster Stage), RH560M motor for the second stage (sustainer stage) with all associated structural systems and payload is having a total length of 10.3 meters with a take-off mass of 3 tonnes.

The first flight aims at vehicle characterisation and performance evaluation. Booster and sustainer motors, structures, separation and destruct system were realised during the year.

Reusable Launch Vehicle Technology Demonstrator
As a first step towards realising a Two Stage To Orbit (TSTO) fully re-usable launch vehicle, a series of technology demonstration missions have been conceived. For this purpose, a Winged Reusable Launch Vehicle technology Demonstrator (RLV-TD) has been configured.

The RLV-TD will act as a flying test bed to evaluate various technologies, viz., hypersonic flight, autonomous landing, powered cruise flight and hypersonic flight using air breathing propulsion. First in the series of demonstration trials is the hypersonic flight experiment (HEX).

An artist’s view of RLV-TD

During the year, aerodynamic characterisation of technology demonstration vehicle was completed at NAL, VSSC and IITK. Trajectory design and Closed Loop Guidance algorithm from lift off to touch down was also completed. Besides, aerodynamic characterisation of ascent and descent configuration, lift off aerodynamic studies at IIT Kanpur and control surface deflection studies at hypersonic Mach numbers by in-house wind tunnel tests were completed.

Engineering model of Airframe and simulation models of avionics packages were realised. HS9 motor static test completed.

Advanced R&D Projects
Aerodynamic characterisation of advanced space transportation system needs higher capacity facilities. Towards this, 1m diameter hypersonic wind tunnel and 1 m diameter shock tunnel are in advanced stage of realisation. During the year, vacuum system for Hypersonic Wind Tunnel Project facility was commissioned. Besides, a Higher capacity shaker system is being indigenously realised for environmental vibration testing of future launch vehicle subsystems. And, to simulate the plasma environment faced by reentry modules like SRE-II and HSP Crew module, current 1 MW Plasma tunnel is being enhanced to 6 MW Plasma Tunnel.

Launch infrastructure
SDSC SHAR supported two launches of Polar Satellite Launch Vehicle PSLV-C12 on April 20, 2009 for RISAT-2 and ANUSAT and PSLV-C14 on September 23, 2009 for launching Oceansat - 2.

S200 at its test facility

Fluid mockup trials on Indigenous CUS were completed using filling software developed in house.

State of the art S-200 Solid Propellant Plant (SPP) with built in automation and safety features has been commissioned successfully at SDSC SHAR. This includes full commissioning of facilities for Hardware Insulation and Lining, Raw Material Preparation, Premix, Mixing and Bowl cleaning, Casting, Curing and Post Curing like Propellant Machining, Inhibition and Tilting and NDT. Static Test of S200 motor, the third largest in the worls was conducted successfully on January 24, 2010. Vehicle Assembly and Test Facilities (VATF), Range Instrumentation and Computer Systems (RICS) and Propellant Servicing Facilities (PSF) required for GSLV-Mk III project are nearing completion.

Human Spaceflight Programme
Proposal for a management plan for Human Spaceflight Programme (HSP) was prepared and pre-project activities were approved. The program envisages development of a fully autonomous orbital vehicle carrying two or three crew members to about 300 km low earth orbit and their safe return. It is planned to realise the programme in 2015-2016 time frame.

During the year, Crew Escape System (CES) aerodynamic configuration was finalised after CFD studies. Baseline documents were prepared for astronaut selection and astronaut training. Baseline configuration document for human centrifuge, spatial disorientation trainer, hypo/hyperbaric chamber, mission simulator and quarantine was prepared.

 

[Kinetic]

Communication and Meteorological Satellite System

Indian National Satellite (INSAT) system is a joint venture of the Department of Space, Department of Telecommunications, India Meteorological Department, All India Radio and Doordarshan. Established in 1983, INSAT is the largest domestic communication satellite system in the Asia Pacific Region with eleven satellites in operation INSAT-2E, INSAT-3A, INSAT-3B, INSAT-3C, INSAT-3E, KALPANA-1, GSAT-2, EDUSAT, INSAT-4A, INSAT-4B and INSAT-4CR. The overall coordination and management of INSAT system rests with INSAT Coordination Committee. The latest satellite in the series, INSAT-4CR was launched on September 2, 2007 using GSLV from Sriharikota giving further boost to INSAT capability, especially for Direct-To-Home (DTH) television broadcast.

Satellites in Service
INSAT-2E
The last of the five satellites in INSAT-2 series, located at 83 deg E longitude is now in its tenth year of service. It carries the following payloads:

* Seventeen C-band and lower extended C-band transponders providing zonal and global coverage with an Effective Isotropic Radiated Power (EIRP)
of 36 dBW.
* Under an agreement with the International Telecommunications Satellite Organisation (INTELSAT), six 36 MHz equivalent units of C-band capacity
on INSAT-2E which have been leased to INTELSAT earlier are being continued.

INSAT-3 Series
Of the five satellites, INSAT-3A through INSAT-3E, planned under INSAT-3 series, four satellites INSAT-3A, INSAT-3B, INSAT-3C and INSAT-3E have already been launched providing satisfactory service.

INSAT-3A
The multipurpose satellite, INSAT-3A, has satisfactorily completed six years of operation. It is located at 93.5 degree East longitude. The payloads on INSAT-3A are as follows:

* 12 Normal C-band transponders (9 channels provide expanded coverage from Middle East to South East Asia with an EIRP of 38 dBW, 3 channels provide India coverage with an EIRP of 36 dBW)

* 6 Extended C-band transponders provide India coverage with an EIRP of 36 dBW.

* 6 Ku-band transponders provide India coverage with an EIRP of 48 dBW.

* Very High Resolution Radiometer (VHRR) with imaging capability in the Visible (0.55-0.75 microns), Thermal Infrared (10.5-12.5 microns) and Water Vapour (5.7-7.1 microns) channels, provide 2x2 km and 8x8 km ground resolutions respectively.
*
A Charge Coupled Device (CCD) camera provides 1x1 km ground resolution, in the Visible (0.63-0.69 micron), Near Infrared (0.77-0.86 micron) and Shortwave Infrared (1.55-1.70 micron) bands.
*
A Data Relay Transponder (DRT) having global receive coverage with a 400 MHz uplink and 4500 MHz downlink for relay of meteorological, hydrological and oceanographic data from unattended land and ocean-based automatic data collection-cum-transmission platforms.
*
A Satellite Aided Search and Rescue (SAS&R) payload having global receive coverage with 406 MHz uplink and 4500 MHz downlink with India coverage, for relay of signals from distress beacons in sea, air or land.

INSAT-3B
Launched in March 2000, INSAT-3B is colocated with INSAT-2E at 83 degree East longitude. It carries 12 Extended C-band transponders and three Ku-band transponders that have coverage over the Indian region. INSAT-3B also incorporates a Mobile Satellite Services (MSS) payload with forward link between the hub and mobile station operating in CxS band and return link between the mobile station and the hub operating in SxC band.

INSAT-3C
Launched in January 2002, INSAT-3C is positioned at 74 degree East longitude. INSAT-3C payloads include 24 Normal C-band transponders providing an EIRP of 37 dBW, six Extended C-band transponders with EIRP of 37 dBW, two S-band transponders to provide BSS services with 42 dBW EIRP and an MSS payload similar to that on INSAT-3B. All the transponders provide coverage over India.

KALPANA-1
KALPANA-1 is an exclusive meteorological satellite launched by PSLV in September 2002. It carries VHRR and DRT payloads to provide meteorological services. It is located at 74 degree East longitude.

INSAT-3E
Launched in September 2003, INSAT-3E is positioned at 55 degree East longitude and carries 24 Normal C-band transponders provide an edge of coverage EIRP of 37 dBW over India and 12 Extended C-band transponders provide an edge of coverage EIRP of 38 dBW over India.

GSAT-2
Launched by GSLV in May 2003, GSAT-2 is located at 48 degree East longitude and carries four Normal C-band transponders to provide 36 dBW EIRP with India coverage, two Ku-band transponders with 42 dBW EIRP over India and an MSS payload similar to those on INSAT-3B and INSAT-3C.

EDUSAT
Configured for audio-visual medium employing digital interactive classroom lessons and multimedia content, EDUSAT was launched by GSLV in September 2004. Its transponders and their ground coverage are specially configured to cater to the educational requirements. The satellite carries a Ku-band transponder covering the Indian mainland region with 50 dBW EIRP, five Ku-band spot beam transponders for South, West, Central, North and North East regional coverage with 55 dBW EIRP and six Extended C-band transponders with India coverage with 37 dBW EIRP.

EDUSAT is positioned at 74 degree East longitude and is colocated with KALPANA-1 and INSAT-3C.

INSAT-4 Series

INSAT-4A
Launched in December 2005 by the European Ariane launch vehicle, INSAT-4A is positioned at 83 deg. East longitude along with INSAT-2E and INSAT-3B. It carries 12 Ku-band 36 MHz bandwidth transponders employing 140 W TWTAs to provide an EIRP of 52 dBW at the edge of coverage polygon with footprint covering Indian main land and 12 C-band 36 MHz bandwidth transponders provide an EIRP of 39 dBW at the edge of coverage with expanded radiation patterns encompassing Indian geographical boundary, area beyond India in southeast and northwest regions.

INSAT-4B
Configured with payloads identical to that of INSAT-4A, INSAT-4B was launched onboard the European ARIANE-5 launch vehicle on March 12, 2007. INSAT-4B carries 12 Ku-band and 12 C-band transponders to provide an EIRP of 52 dBW and 39 dBW respectively. Two Tx/Rx dual grid offset fed shaped beam reflectors of 2.2 m diameter for Ku-band and 2 m diameter for C-band are used.

INSAT-4B has augmented the high power transponder capacity over India in Ku-band and over a wider region in C-band. INSAT-4B has been colocated with INSAT-3A at 93.5 degree E longitude.

INSAT-4CR
INSAT-4CR was launched on September 2, 2007 on GSLV from Sriharikota. INSAT-4CR is identical to INSAT-4C with 12 Ku-band transponders with an EIRP of 51.5 dBW. It has been positioned at 74 deg E longitude co-located with INSAT-3C, KALPANA-1 and EDUSAT. INSAT-4CR is the third satellite in INSAT-4 series. It carries 12 high-power Ku-band transponders designed to provide Direct-To-home (DTH) television services, Video Picture Transmission (VPT) and Digital Satellite News Gathering (DSNG).

ANUSAT
ANUSAT is a 35 kg micro-satellite, designed by Anna University, Chennai. The main objective is to involve universities in building micro satellites as a means to promote and encourage intra-disciplinary technologies with the help of ISRO.

ANUSAT carries a digital store and forward payload for amateur communication. In addition, a number of technological payloads like digital receiver and turbo coder, MEMS-based gyro and magnetic field sensor were flown on board. Structure, solar panels, chemical battery, sensors and actuators were supplied by ISRO. The payloads and the other satellite subsystems were designed and fabricated at Anna University. The satellite was launched in April 2009 by using PSLV-C12 from SDSC SHAR, Sriharikota.

W2M
W2M satellite was developed and built for EUTELSAT, jointly with EADS - Astrium under a contract through ANTRIX. EADS Astrium was the prime contractor in charge of overall programme management and built the communications payload. ANTRIX, lSRO built the satellite bus, based on the flight proven I-3K model, responsible for integration and test of the spacecraft. ISRO was in charge of early in-orbit operations too. The satellite was launched on December 21, 2008 from Kourou using Ariane Launch Vehicle.

W2M carries 24 Ku-band transponders (and upto 32 depending on operational modes). W2M was designed to provide a wide range of services from television broadcasting to data networks and broadband.

W2M spacecraft control is with the customer Eutelsat, which is presently operating communication services through the spacecraft transponders. As per the present plan, 12 transponders will be used.

 

[Kinetic]

Forthcoming Satellites
GSAT-4
GSAT-4, envisaged as a technology demonstrator, carries a communication payload consisting of a multi-beam Ka-band bent pipe, regenerative transponder and a navigation payload in C, L1 and L5 bands.

GSAT-4 ready to enter CATVAC

GSAT-4 having propulsion system with four stationary plasma thrusters, Bus Management Unit (BMU), miniaturised dynamically tuned gyros, 36 AH Lithium ion battery, 70 V bus for Ka band TWTAs, on-board structural dynamic vibration beam accelerometer, are some of the new technologies developed for the mission. The satellite weighs around 2200 kg and has a payload power of 1600W. GSAT-4 will be positioned at 82 deg East longitude.

The satellite integration and test activities are in advanced stage. Spacecraft closed mode IST has been completed. The thermovacuum tests have been completed successfully and the Spacecraft Dynamic and CATF tests are in progress. The spacecraft is almost ready for shipment to SDSC SHAR.

GSAT-4 plasma thruster mounted on satellite structure

AVANTI HYLAS
Hylas is being developed and built for Avanti Screenmedia, UK jointly with EADS-Astrium under a contract through ANTRIX. EADS Astrium is the prime contractor in charge of overall programme management and will build the communications payload. ANTRIX, ISRO will build the satellite bus, based on the flight proven I-2K model with a lift off mass of around 2550 kg and payload power of 2000 W, integrate and test the satellite. ISRO will also be in charge of Launch and Early Orbit operations. Hylas is designed for an operational lifetime of 15 years and exploits generic, flexible payload equipment.

Avanti Hylas payloads are:

* Ku-Band transponders covering entire Western Europe through 15m deployable reflector

* Ka-band transponders providing eight spot beams through 2.6m x 1.6m

During the year, the satellite bus elements were realised. Integration Readiness Review was completed with the participation of M/s. Astrium. All bus elements except BMU and Inertial Systems have been integrated with the spacecraft. Disassembled mode IST is in progress. The satellite will be ready for shipment by mid 2010.

Hylas Spacecraft during integration

GSAT-5 PRIME
GSAT-5P is being planned as replacement for INSAT-3E and will carry 24 Normal C Band and 12 Extended C Band transponders with India Coverage. The spacecraft will be positioned at 55 deg East longitude with a mission life of 12 years.

The spacecraft weighs 2330 kg and payload power requirement is 1700W. Spacecraft configuration and equipment panel layouts are finalised. Payload subsystems and other subsystem packages are under advanced stage of realisation.

GSAT-5/INSAT-4D
Configured as an exclusive C-band communication satellite, GSAT-5/INSAT-4D will carry 12 normal C-band transponders and six extended C-band transponders with wider coverage in uplink and downlink over Asia, Africa and Eastern Europe as well as zonal coverage with a minimum of 35 dBW EIRP.

The spacecraft has a mission life of 12 years. The spacecraft weighs 2330 kg and has a power generation capability of 2000W. The layouts for all equipment panels are finalised. Fabrication of bus system elements have been initiated.

GSAT-6/1NSAT-4E
The primary goal of GSAT-6/INSAT-4E, which is a Multimedia broadcast satellite, is to cater to the consumer requirements of providing entertainment and information services to vehicles through Digital Multimedia consoles and to the Multimedia mobile Phones. The satellite carries a 5 spot beam BSS and 5 spot beam MSS. It will be positioned at 83 deg East longitude with a mission life of 12 years.

Stowed

Unfurled

Unfurlable antenna for GSAT-6

The satellite configuration is based on I-2K bus system with a liftoff mass of 2200 kg and payload power of 2300W. Power system is configured with a single bus providing 70V regulated bus for the TWTAs and 42 V regulated bus for the mainframe systems and other payload elements. Multi-junction solar cells for power generation and Lithium-Ion batteries for power storage have been used.

An indigenously developed Unfurlable Antenna(UFA) which provides five beams to cover the entire Indian land mass is the new element in the satellite. The scaled down model (2m dia) of the UFA with the same design and fabrication features has been developed to evaluate its RF performance. Fabrication of all platform systems hardware is in progress and payload subsystem elements are available. The launch is planned on-board GSLV during 2010.

GSAT-7/1NSAT-4F
GSAT-7 is a multi-band satellite carrying payloads in UHF, S-band, C-band and Ku-band. It is planned to be launched during 2011 onboard GSLV and positioned at 74 deg East. The satellite weighs 2330 kg with a payload power of 2000W and mission life of 9 years. Structural configuration of the satellite has been finalised and the layout work is completed, detailed design of UHF antenna mechanism is in progress and antenna shock analysis completed. The platform systems are under fabrication and payload subsystem procurement is in progress.

GSAT -8/1NSAT-4G
GSAT-8/INSAT-4G is a Ku-band satellite carrying 18 Ku band transponders. It will also carry a GPS Aided Geo Augmented Navigation (GAGAN) payload. The satellite is planned to be launched during 2010 with a mission life of 12 years and positioned at 55 deg E longitude. This I-3K satellite with a lift-off mass of 3150 kg and a payload power of 5300W will be launched on board ARIANE-5. Fabrication of bus systems is in an advanced stage.

GSAT-12
GSAT-12 is being realised as replacement INSAT-3B. Realisation of various sub systems is progressing satisfactorily. The satellite will carry 12 Extended C-band transponders and will be positioned at 83 deg East longitude with a mission life of 7 years. The bus system is based on I-1K platform with ASIC based BMU and 64 Ah Li-ion batteries. The satellite weighs 1375 kg with a payload power of 550W.

During the current year, the Configuration Design Review was completed and all layouts and interfaces were finalised. Payload realisation is in progress. Fabrication of bus systems is in progress and launch is planned onboard PSLV during 2010.

GSAT-9
GSAT-9 will carry 6 C band and 24 Ku band transponders with India coverage beam. The satellite is planned to be launched during 2011-12 with a mission life of 12 years and positioned at 48 deg E longitude. This I-2K satellite has a liftoff mass of 2330 kg and payload power of 2300W.

GSAT-10
GSAT-I0 will carry 12 Normal C-band, 12 Extended C-band and 12 Ku-band transponders. It will also carry GPS Aided Geo Augmented Navigation (GAGAN) payload. The satellite is planned to be launched during 2011 with a mission life of 15 years and positioned at 83 deg East longitude. This I-3K satellite with liftoff mass of 3435 kg and payload power of 4500 W will be launched on board ARIANE-5.

Configuration of both platform systems and payload has been finalised and procurement action for long lead items has been initiated. Fabrication of platform systems is already initiated.

INSAT-3D
INSAT-3D, a meteorological satellite, carries a 6-Channel VHRR and a 19 channel Sounder. VHRR provides information in the visible (0.6) and near infrared (1.6) with 1 km resolution; MWIR (3.9) with 4 km resolution; Water Vapour (6.7) with 8km resolution; and IR 10.8 and IR 12.0 with 4 km resolution. INSAT-3D Sounder has 18 infrared channels and a visible channel to help cloud detection during daytime.

Many geophysical parameters such as the Outgoing. Long wave Radiation (OLR), Quantitative Precipitation Estimation (QPE), Sea Surface Temperature (SST), Snow cover, Snow depth, Cloud Motion Vector, Water Vapor Wind (WVW), Upper Troposheric Humidity, Temperature, Humidity profile and Total Ozone, aerosols, etc., are expected to provide operational inputs for weather forecasting applications. The satellite has many new technology elements like star sensor, micro stepping Solar Array Drive Assembly (SADA) to reduce spacecraft disturbances and Bus Management Unit (BMU) for control and Telemetry /Telecommand function. It also incorporates new features of bi-annual rotation and image and mirror motion compensation for improved performance of the meteorological payloads.

An artist’s impression of INSAT-3D

The spacecraft weighs 2050 kg with power generation capability of 1200W. The subsystem fabrication is in advanced stage of realisation. FM Sounder payload testing is completed and FM Imager payload system level optimisation is in progress. Mainframe elements, structure along with north and south equipment panels are available. Many of the bus-system elements are in advanced stage of realisation and the launch is planned on-board GSLV in 2010-11.

SATELLITE NAVIGATION

GPS AIDED GEO AUGMENTED NAVIGATION (GAGAN)
The Indian Satellite Based Augmentation System (SBAS) is called GAGAN. The Technology Demonstration Phase (TDS) of GAGAN was successfully completed in August 2007. As apart of the TDS, eight Indian Reference Stations (INRESs) have been installed at eight Indian airports. They are linked to the Master Control Center (MCC) located at Kundanhalli near Bangalore. From MCC, the Indian Land Uplink Station (INLUS) transmits correction signals to the space segment having GAGAN navigation payload which translates these signals to the GPS LT bands for reception by a GPS SBAS receiver. In June 2009, the operational phase (FOP) of GAGAN was initiated. The GAGAN system is expected to be ready for testing in about 18 months.

The first GAGAN navigation payload has been fabricated and it is proposed to be flown on GSAT-4 which will be launched in 2010. Two more GAGAN payloads will be subsequently flown, one each on two geostationary satellites, GSAT-8 and GSAT-10. Preparation of sites for INRES installation and third INREE chain on TDS system is in progress.

INDIAN REGIONAL NAVIGATION SATELLITE SYSTEM (IRNSS)
IRNSS constellation consists of seven satellites. Three satellites will be placed in Geostationary orbit (GEO) at 34°E, 83°E & 131.5°E and two satellites each will be placed in the Geosynchronous orbit (GSO) with equatorial crossing at 55°E and 111.5°E with an inclination of 29° to the equator. Two spare satellites are also planned to be realised. IRNSS will have two types of signals, in L5 and S-Band. IRNSS provides two basic services a Standard Positioning Service (SPS) for common civilian users and a Restricted Service (RS) for special authorised users.

IRNSS Signal and Data structure have been prepared and reviewed. The signal and data structure has been prepared after extensive study by groups at the work centers.

Indian Regional Navigation Satellite System (IRNSS)



The civil construction work for the Navigation Control Centre at Bangalore and the Satellite Control Facility at Hassan is in progress. The navigation software for IRNSS is being indigenously developed at ISRO Satellite Centre. As a part of this activity, many modules have been developed and testing is in progress. Coverage Studies, Error Analysis, Up linking scheme for Navigation Parameters and Time Synchronisation have been carried out. Navigation Payload configuration is frozen and Preliminary Design Review (PDR) has been completed. The realisation of the Payload Engineering Model is progressing satisfactorily.

The spacecraft configuration has been finalised and the satellites of the constellation are being configured identically and each spacecraft weighs 1380 kg. Fabrication of six structural cylinders is completed. Most of the standard hardware is productionised. The spacecraft is basically configured with I-1K Bus to be compatible with launch onboard PSLV. After detailed analysis, it was found that it would be possible to launch two numbers of inclined orbit satellites in one flight of GSLV.

 

[ek_indian]

There is a thread about Indian space programs. You could have referred that.
There was absolutely no need for this one.

 

[Kinetic]

Earth Observations System

The Indian Earth Observation activities carried out in the institutional framework of the National Natural Resources Management System (NNRMS) under the aegis of the Planning Commission activities are widely acclaimed around the world for their application driven approach. With a host of payloads in the thematic series of Indian Remote Sensing Satellites (IRS) and the INSAT systems, the Indian EO system has been providing a variety of operational services to the user community in the country. These include thematic series of satellites in the land and water resources management; cartographic and large scale mapping applications; and the ocean and atmospheric research areas has been planned with a view to provide necessary continuity of operational services in an assured manner.

The Planning Committee of NNRMS (PC-NNRMS) oversees the end-to-end programme and provides necessary guidance for implementation of the programme. Nine high-power Standing Committees, viz, (i) Agriculture and Soils (ii) Bio-Resources and environment (iii) Geology and Mineral Resources (iv) Water Resources (v) Ocean and Meteorology (vi) Cartography and Mapping (vii) Urban Management (viii) Rural Development and (ix) Training and Technology constituted under NNRMS address the specific issues pertaining to applications of remote sensing in different thematic areas. Each of these Standing Committees is chaired by Secretary of the respective government departments and includes experts from major user departments/agencies. Many line departments have absorbed and adopted remote sensing technology and they are using the same for various activities. Further, various States have established State Remote Sensing Applications Centres and have been making use of IRS data for various developmental applications. In the recent times, there has also been increased emphasis for taking up of many societal applications with the participation of the community. Many academic institutions have introduced remote sensing and GIS as part of the educational curricula. Also, as part of the capacity building exercise, regular and periodic training programmes are conducted under NNRMS at various levels. Thus remote sensing has already been successfully institutionalised in the country.

Earth Observation Satellites
The Indian Remote Sensing satellite system has one of the largest constellations of remote sensing satellites in operation in the world today. Currently nine operational satellites are in orbit – TES, Oceansat-1, Resourcesat-1, CARTOSAT-1, CARTOSAT-2, CARTOSAT-2A, IMS-1, RISAT-2 and OCEANSAT-2. IRS series of satellites provide data in a variety of spatial, spectral and temporal resolutions. With these and the planned thematic series of satellites in the coming years, such as CARTOSAT-2B, RESOURCESAT-2, RISAT-1, Megha Tropiques, SARAL, CARTOSAT-3 and INSAT-3D, the Indian EO system is expected to continue to provide products and services enabling applications in several areas spanning from cartography to climate.

Indian EO Satellites currently in Operation

OCEANSAT-2
Oceansat-2 intended for ocean applications and a follow on to Oceansat-1 was launched on 23 September 2009 by PSLV-C14 from SDSC, SHAR. It has an Ocean Colour Monitor (OCM) and a Ku-band pencil beam Scatterometer. In addition, it also has a Radio Occultation Sounder for Atmospheric Studies (ROSA), developed by the Italian Space Agency (ASI). Considering that Oceansat-2 is a continuity mission to the earlier Oceansat-1, the same polar sun synchronous orbit of 720 kms with the local time of equator crossing of 1200 Hrs±10 minutes has been retained. OCEANSAT-2 will be used for identification of Potential Fishing Zones, sea state forecasting, coastal zone studies and provide inputs for weather forecasting and climatic studies.

Oceansat-2 undergoing dynamic balancing test

Ocean Colour Monitor (OCM): An 8-band OCM, similar to Oceansat-1 OCM with appropriate spectral bandwidth modifications in Band-6 and 7 based on the experience gained were carried in oceansat-2. As suggested by application scientists Band - 6 (0.66 0.68 micron) and Band-7 (0.745-0.785 micron) of OCM -1 was changed to 0.61-0.63 micron and 0.725-0.755 micron respectively to improve the assessment estimation accuracy of suspended sediment in coastal waters and to avoid oxygen absorption which led to improved accuracy of atmospheric correction. OCM, with 360 metres spatial resolution and a swath of 1420 kms, will provide a 2-day repetitivity.

First image from Oceansat-2

Scatterometer: This pencil beam Scatterometer works in Ku-band with a ground resolution cell of 50 kms x 50 kms, which will scan the earth surface conically, with a swath of 1400 kms. It provides the wind vector in the range of 4 to 24 meters/second with better than 20% accuracy in speed and 20 deg. in wind direction. The Scatterometer data will be used for deriving the global wind velocity (magnitude and direction) over ocean surface, which will go as on input for weather forecasting, monitoring of cyclones and hurricanes and their trajectory, monitoring of Polar Sea Ice changes and ocean state forecasting.

Ku-band Scatterometer of Oceansat-2

Radio Occultation Sounder for Atmospheric studies (ROSA): ROSA Payload designed and developed by ASI, Italy was flown in Oceansat-2 to study temperature and humidity of the atmosphere. ROSA consists of a Radio Occultation antenna along the satellite velocity vector (VA) and a Navigation antenna (POD).

Radar Imaging Satellite (RISAT-2)
A Radar Imaging Satellite (RISAT-2) with all weather capability and ability to penetrate clouds realised in association with Israel Aerospace Industries was launched onboard PSLV-C10 from SDSC, Sriharikota on April 20, 2009. RISAT-2 has the ability to enhance country's capability in the management of disasters.

CARTOSAT-2A
CARTOSAT-2A, the thirteenth in the Indian Remote Sensing (IRS) satellite series was launched on April 28, 2008 by PSLV-C9 from Satish Dhawan Space Centre (SDSC), SHAR, Sriharikota. CARTOSAT-2A, much similar to CARTOSAT-2, is an advanced remote sensing satellite capable of providing scene-specific spot imagery and carries a single panchromatic camera onboard capable of providing better than 1-meter spatial resolution imagery, with a swath of 9.6 km. The satellite has high agility with capability of steering along and across the track up to + 45° to facilitate imaging of any area more frequently. Data from the satellite could be used for cartographic applications at cadastral level, urban and rural infrastructure development and management.

IMS-1
IMS-1 was launched along with Cartosat-2A on April 28, 2008 by PSLV-C9 from Satish Dhawan Space Centre (SDSC), SHAR, Sriharikota. IMS-1 carries a Multi Spectral (MX) camera with 37 m resolution and 151 km swath and Hyper Spectral Camera (HySi) with 505 m resolution and 130 km swath. The data is regularly acquired and used for Natural resources monitoring and management like Agriculture, forest coverage and deforestation, urban infrastructure development, land use and wasteland mapping, coastal features mapping, coral reef mapping, landslide and mineral studies.

CARTOSAT-2
CARTOSAT-2, the twelfth in the Indian Remote Sensing (IRS) satellite series, is an advanced remote sensing satellite capable of providing scene-specific spot imagery. CARTOSAT-2, launched on January 10, 2007 by PSLV-C7, carries a single panchromatic camera onboard capable of providing better than 1-meter spatial resolution imagery, with a swath of 9.6 km. The satellite has high agility with capability of steering along and across the track up to + 450 to facilitate imaging of any area more frequently. It was placed in a sun synchronous polar orbit of a nominal altitude of 630 km with a re-visit of 4-5 days and can be brought to a special orbit of 560 km with revisit periods of 4 days and 1 day respectively.

Cartosat-2 satellite has been functioning well, providing operational services to the user community. The data from the satellite is being used for cartographic applications at the cadastral level, urban and rural infrastructure development and management, as well as applications in Land Information System (LIS).

Phased Array Antenna of Cartosat-2
developed at ISAC

CARTOSAT-1
CARTOSAT-1 was launched into a 617 km polar sunsynchronous orbit on May 5, 2005 on board PSLV-C6 from Satish Dhawan Space Centre (SDSC), SHAR, Sriharikota. The satellite carries two panchromatic cameras PAN (fore) and PAN (aft) with 2.5-meter resolution providing a swath of 30 km. The cameras are mounted with a tilt of +26 deg and -5 deg along the track with respect to nadir so as to provide stereo pairs of images that can be used to generate Digital Terrain Model (DTM) / Digital Elevation Model (DEM). Data from CARTOSAT-1 is used for the preparation of cartographic maps, cadastral mapping updation, land use and GIS applications. An onboard Solid State Recorder provides global data storage of areas not in the ground station visibility.

 

[Kinetic]

RESOURCESAT-1
Resourcesat-1, the tenth satellite in IRS series, was launched on board PSLV-C5 in October 2003. It was placed in an 820 km high polar Sun Synchronous Orbit. Resourcesat-1 carries three cameras:

* A high resolution Linear Imaging Self Scanner (LISS-4) operating in three spectral bands in the Visible and Near Infrared Region (VNIR) with 5.8 metre spatial resolution with 70 km (mono) and 23 km (multispectral) swath and steerable up to + 26 deg across track to obtain stereoscopic images and achieve five day revisit capability

* A medium resolution LISS-3 operating in three spectral bands in VNIR and one in Short Wave Infrared (SWIR) band with 23.5 metre spatial resolution with 142 km swath

* An Advanced Wide Field Sensor (AWiFS) operating in three spectral bands in VNIR and one band in SWIR with 56 metre spatial resolution and a combined swath of 730 km achieved through two AWiFS cameras

In addition, RESOURCESAT-1 has 120 Gigabits of on-board memory that allows for out-of-contact imaging. Uniqueness of this satellite is the availability of simultaneous multispectral data at three spatial resolutions from the same platform with scene coverage varying from 576 sq km to 19,600 sq km to 5,42,000 sq km.

The images are being used for advanced applications like vegetation dynamics, crop yield estimates, disaster management support, etc.

OCEANSAT-1
OCEANSAT-1, intended to study physical and biological aspects of oceanography, was launched onboard PSLV-C2 on May 26, 1999. It carries an Ocean Colour Monitor (OCM) and a Multifrequency Scanning Microwave Radiometer (MSMR). OCM operates in 402-422, 433-453, 480-500, 500-520, 545-565, 660-680, 745-785 and 845-885 nm bands with 360-meter spatial resolution and 1420 km swath. OCM data is collected over the Indian region and also over International ground stations.

Technology Experiment Satellite (TES)
TES was launched on board PSLV-C3 on October 22, 2001. The satellite was intended to demonstrate and validate technologies that could be used in the future cartographic satellite missions. Some of the technologies demonstrated in TES were: attitude and orbit control system, high torque reaction wheels, new reaction control system with optimised thrusters and a single propellant tank, light weight spacecraft structure, solid state recorder, X-band phased array antenna, improved satellite positioning system, miniaturized TTC and power system and two-mirror-on-axis camera optics. TES carries a panchromatic camera with a spatial resolution of 1 m and swath of 13 km. The satellite has been functioning well even after its intended mission life.

Forthcoming Satellites
CARTOSAT-2B
The Cartosat-2B satellite, a follow on of Cartosat-2A, weighing around 690 kg, is configured to provide multi-scene imaging capability during a pass. The advanced remote sensing satellite will be carrying onboard a single panchromatic camera providing scene specific spot imageries for cartographic and a host of other civilian applications. The satellite is highly agile having a capability of steering along and across the track up to ± 450. It will be placed in a sun synchronous polar orbit of a nominal altitude of 630 km with a re-visit period of 4-5 days. There is a provision to bring the satellite to a special orbit of 560 km with a revisit period of 1 day. The panchromatic camera is designed to provide better than 1 m spatial resolution imageries with a swath of 9.6 km. The satellite is designed for an operational life of 5 years. The spacecraft is under integration and will be launched by PSLV in the first quarter of 2010.

RISAT - 1
Radar Imaging Satellite (RISAT-1) mission will have a C-band Synthetic Aperture Radar (SAR) payload, operating in a multi-polarisation and multi-resolution mode. SAR, being an active sensor, operating in the microwave range of electromagnetic spectrum, provides target parameters such as dielectric constant, roughness, and geometry, and has the unique capability for day-night imaging, and imaging in all weather conditions including fog and haze and also provides information on soil moisture. The SAR payload is based on an active phased array technology using Transmit / Receive (TR) modules, which would provide necessary electronic agility for achieving the multi-mode capability, providing spatial resolutions of 1 m to 50 m, and 10 to 240 km swath modes to cater to different applications. The Local Time of RISAT is 06:00 hours at the descending node.

The development of complex technologies pertaining to phased array antenna of 6 m x 2 m size hosting 20736 radiative elements, 288 TR module pairs feeding the radiative elements, a number of power converters supplying power to all these elements, signal distribution and calibration network, range and azimuth compression and data compression as well as handling very high average DC power of 4.7 KW during payload operations etc., form part of the overall mission, hitherto not attempted in IRS satellites. Ground data processing systems with large computational requirements is under development. The satellite weighing around 1850 kg is in the final stages of development for launch by PSLV-XL during third quarter of 2010 into a 536 km orbit with 25 days repetitivity with an added advantage of 12 days inner cycle for CRS mode.

RESOURCESAT-2
Resourcesat-2 is a follow on mission to Resourcesat-1 to provide data continuity. Compared to Resourcesat-1, LISS-4 multispectral swath has been enhanced from 23 km to 70 km based on user needs. Suitable changes including miniaturisation in payload electronics have been incorporated in Resourcesat-2. Resourcesat-2 is slated for launch during 2010.

Megha-Tropiques
(Megha means cloud in Sanskrit and Tropiques means tropics in French) is aimed at understanding the life cycle of convective systems and to understand their role in the associated energy and moisture budget of the atmosphere in the tropical regions. ISRO and French National Space Centre (CNES) signed a Memorandum of Understanding (MOU) in 2004-05 to proceed with the development and implementation of Megha-Tropiques. The satellite will carry the following scientific instruments:

* Microwave Analysis and Detection of Rain and Atmospheric Structures (MADRAS), an Imaging Radiometer to be developed jointly by CNES and ISRO

* SAPHIR, a six channel Humidity Sounder

* SCARAB, a four channel Scanner for Radiation Budget Measurement

* GPS-ROS - GPS Radio Occultation System to provide vertical profiles of temperature and humidity of the earth's atmosphere

ISRO is building the Megha-Tropiques spacecraft using IRS platform and launch it using PSLV into 867 km orbit at an inclination of 20 degrees with respect to the equatorial plane. ISRO will also control the satellite in orbit and also receive, process and distribute the scientific data obtained from the satellite. All flight structure elements have been tested and assembled. Mainframe subsystems are in final stages of realisation. The electronic hardware for MADRAS payload is delivered for assembly. Testing of SCARAB and SAPHIR payloads is completed. The launch of Megha-Tropiques is planned during the fourth quarter of 2010.

SARAL
The Satellite for ARGOS and ALTIKA (SARAL) is a joint ISRO - CNES mission, and will be launched by PSLV into a sun-synchronous, 6 am - 6 pm orbit at an altitude of around 800 km. The Ka band altimeter, ALTIKA, provided by CNES operates at 35.75 GHz. A dual frequency total power type microwave radiometer (23.8 and 37 GHz) is embedded in the altimeter to correct tropospheric effects on the altimeter measurement. Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS) on board enable precise determination of the orbit. A Laser Retroreflector Array (LRA) helps to calibrate the precise orbit determination system and the altimeter system several times throughout the mission.

SARAL / ARGOS Data Collection System (DCS) represents a joint contribution of ISRO and CNES to the development and operational implementation of the global ARGOS Data Collection System. The main objective is to receive data from Data Collection Platforms and transmit these to the ARGOS Ground Segment, for subsequent transmission to the ARGOS Data Processing and Distribution Centre in Toulouse, France. In addition, ARGOS Payload allows the transmission of short messages directly to Data Collection Platforms equipped with a receiver.

SARAL payload will be accommodated in the mini-satellite bus ranging between 400-450 kg class, named as SSB-1 (Small Satellite Bus). SARAL will provide Data Products to the operational and research user communities, in support of Marine meteorology and sea state forecasting; Operational oceanography; Seasonal forecasting; Climate monitoring; and Ocean, Earth system and climate research. Preliminary Design Review has been completed. SARAL simulator has been delivered to CNES. Spacecraft Mainframe systems are under fabrication and payload delivery is expected in May 2010. The satellite launch is planned during 2011.

Ground Segment
ISRO Telemetry, Tracking and Command Network (ISTRAC) with its headquarters at Bangalore is providing TTC and mission control support to launch vehicle missions and near earth orbiting satellites through an integrated network of ground stations at Bangalore, Lucknow, Sriharikota, Port Blair, Thiruvananthapuram Mauritius, Tromso and Svalbard (Norway) & Troll (Antartica) and Biak (Indonesia), has a multimission Spacecraft Control Centre at Bangalore.

ISTRAC provides:

* Telemetry Tracking and Command (TTC) support to ISRO launch vehicle missions from Satish Dhawan Space Centre SHAR from lift-off till satellite injection, down range tracking support for satellite injection monitoring and Preliminary Orbit Determination (POD)

* TTC support including house-keeping data acquisition throughout the mission life for low earth orbiting satellites and their health monitoring and control operations

* Scientific payload data reception and processing for payload scientists ISTRAC also provides TTC support to international space agencies under commercial agreements through ANTRIX Corporation. ISTRAC has also established the SPACENET, connecting various ISRO Centres.

During the year, ISTRAC provided the launch, preliminary orbit determination and on-orbit support for the launch of RISAT-2 and OCEANSAT-2 satellites. It continued to track, monitor and control TES, Oceansat-1, Resourcesat-1, CARTOSAT-1, CARTOSAT-2, CARTOSAT-2A, IMS-1, RISAT-2 and OCEANSAT-2. Remote sensing payload operations were carried out during the year on IRS-1C and IRS-1D over Indian stations at Shadnagar, and also over 15 Foreign Data Reception Stations (FDRS). About 350 to 400 payload operations are carried out per month for each satellite. Payload operations of OCEANSAT-1 were carried out over Indian station. IRS-P3 payload was operated about 250 times per month over Shadnagar in India and Neustralitz (Germany), Wallops (USA) and Maspolamas (Spain). TES Payload (PAN) operations are regularly carried out over India.

Satellite Data Acquisition and Processing
The National Remote Sensing Centre (NRSC), Hyderabad is the nodal agency for satellite remote sensing data reception, archival, processing and dissemination in the country. NRSC acquires and processes data from all Indian remote sensing satellites like CARTOSAT-1, CARTOSAT-2, RESOURCESAT-1, IRS-1D, OCEANSAT-1, OCEANSAT-2 and IMS-1. NRSC Shadnagar Ground station acquires data from various Indian remote-sensing satellites and few foreign satellites. The station receives around 22 passes regularly at a station efficiency of 99%. As per the Remote Sensing Data Policy, NRSC is the national agency identified for acquisition/distribution of all the satellite data within India. Accordingly, NRSC is disseminating satellites data from Indian and foreign satellites to Indian users. During the year, more than 29,000 data products were disseminated to Indian as well as foreign users.

During the year, the ground segment has been upgraded for reception, processing and product generation. RISAT-1 and RISAT-2 data reception station and a small terminal for IMS satellite data reception have been established. Integrated Multi-mission Ground segment for Earth Observation Satellites (IMGEOS) is conceived, with an objective to have a highly reliable, easily adaptable system to future mission requirements using state-of-art technologies and world class infrastructure towards meeting the requirement of reduced turnaround time for the data product generation.

The preparatory activities for setting up of Oceansat-2 data reception at INCOIS, Hyderabad, a mobile transportable ground receiving station to RISAT-2 data for NTRO has been also developed. The Algiers ground station is being upgraded to receive ALSAT-2A/2B data. Installation and configuring of Resourcesat -1 data processing facility was taken up at Cuiaba station in Brazil as part of the ISRO-INPE (National Institute for Space research, Brazil) co-operative agreement.

Aerial Remote Sensing
The aerial remote sensing facility of NRSC offers value-added services like aerial photography and digital mapping, infrastructure planning, scanner surveys, aeromagnetic surveys, large scale base map, topographic and cadastral mapping, etc. Two aircraft with modern navigational aids, aerial cameras and sensors are available to carry out these activities.

NRSC has inducted the Large Format Digital Metric Camera for Aerial Services and Digital Mapping activities. The Ultracam D camera, with its maximum resolution of 3 cm is one of the leading frame type digital cameras and is expected to give a new impetus to digital photo-grammetric applications. Both the existing aircraft were modified for installation of LFDC system and the system was accepted after test sorties.

400 hours of flying was completed during Apr- Dec 2009 and is expected to touch 550 hrs by March 31, 2010. DMSAR flying over Bihar was completed for 85,000 sq kms (post flood). Aerial photography tasks covering Bangalore (2,500 sq kms), Kolkata (2,300 sq kms and Karimnagar district of A.P. (8,000 sq kms out of 15,000 sq kms) were completed. Under NUIS project, Aerial photography has been completed for 67 towns and planned to be completed for 146 towns. Both the existing aircraft were modified for installation of LFDC system and the system was accepted after test sorties. The test data sets were collected and analyzed in different resolutions of 5 & 10 cm Ground Sampling

LFDC system installed in NRSC aircraft

Distance (GSD) for Shadnagar site, 10 cm GSD for Kamareddy town (Nizamabad district, AP), and 30 & 50 cm GSD for part of Hyderabad. Processing of ALTM data of Sabari basin in AP (800 sqkm) and Mahanadi basin in Orissa (8000 sqkm) are in progress and planned to be completed by March 2010. ALTM - DC data survey for Kosi and Bhagmati basin, Bihar (12100 sq km) is in progress. 3D geospatial database generation for NIC in 1:1000 scale from 1:6000 scale aerial photographs for Hyderabad, Bangalore and Kolkata cities are in various stages of completion.

The recently procured Ultracam D Large Format Digital Camera has been successfully put into use during the search and rescue operations of the missing helicopter in Kurnool district for Government of Andhra Pradesh.

 

[Kinetic]

Space Sciences

Space Science and research has been an important element of Indian space programme. ISRO's space science endeavor is aimed at taking the benefits of science in the form of applications to the people of the country. In addition to space science research activities being pursued at PRL, SPL, NARL, SAID and SSIF at ISAC, specific individual, nationally coordinated and multi-institutional science payload instrumentation and science mission development projects in the atmospheric and space science areas are supported and implemented by ISRO based on the recommendations of ISRO's Advisory Committee for Space Sciences (ADCOS). Some of the main activities carried out by the department in space science are summarised below.

Chandrayaan-1
Chandrayaan-1, India's first mission to the Moon successfully launched on October 22, 2008, was aimed at high-resolution remote sensing of the Moon in the visible, near Infrared, low energy X-ray and high-energy X-ray regions, specifically to prepare a 3-dimensional atlas of both near and far side of the moon, conduct chemical and mineralogical mapping of the entire lunar surface for distribution of mineral and chemical elements.

The eleven payloads of Chandrayaan-1 have studied the moon from different perspectives and provided excellent quality of high resolution data. The analysis of the science data has begun.

Some of the significant results of Chandrayaan-1 mission are given below:

*
Data from Hyper Spectral Imager (HySI), Terrain Mapping Camera (TMC) and Moon Mineralogy Mapper (M3) confirmed the hypothesis of lunar magma ocean
* The data obtained from M3 has clearly indicated the presence of Hydroxyl and water molecules on the lunar surface.

Coulomb C crater as viewed
by TMC


Fresh Impact Crater
Damoieasu from HySI data

In the figure above, blue colour indicates 3 micron absorption associated with the presence of OH/H2O. Red indicates absorption at 2 micron due to the presence of iron-bearing minerals. The Green represents reflected brightness at 2.4 micron. During this particular observation, detection of volatiles is most prominent at higher cooler latitudes. The presence of volatiles appears to be a function of the surface radiation and thermal environment.

*
ChACE (Chandra's Altitudinal Composition Explorer: Quadrupole Mass Spectrometer) onboard Moon Impact Probe (MIP) indicated possible presence of water molecules along with other molecular species in the lunar environment.
*
Sub keV Atom Reflecting Analyser (SARA) has found the presence of atleast 20% of reflected solar wind particles as well as energisation of solar wind in lunar environment which has been observed for the first time.
*
Lunar Laser Ranging Instrument (LLRI) covered more than two and a half million valid elevation points and over 75 crater's topography and slope maps have been prepared.
*
Chandrayaan-1 X-ray Spectrometer (C1XS) observed a C class flare showing the Ca line at 3.6keV in addition to Mg, Al and Si lines. Also identified Mg, Al and Si lines during low illumination conditions of A class solar flare.
*
Radiation Dose Monitor (RADOM) has provided information on the radiation and particle flux dose on the way to moon and in the Earth-Moon radiation environment.

SARA measurements of Hydrogen flux on the Moon

C1XS spectrum showing for the first time well resolved signatures
of Calcium and Iron from lunar orbit

Chandrayaan-2
Chandrayaan-2 mission is planned to have an orbiter/lander/rover configuration. The mission is expected to be realised by 2012 - 13. The science goals of the mission is to further improve our understanding of origin and evolution of the Moon using instruments onboard Orbiter and in-situ analysis of lunar samples and studies of lunar regolith properties (remote & direct analysis) using Robots/Rovers.

Thirty six Indian payload proposals have been received for Orbiter and lander/ rover. Currently the Scientific Advisory Board (SAB) of Chandrayaan-2 is in the process of reviewing the payloads proposed for Orbiter.

ASTROSAT
ASTROSAT is a first dedicated Indian Astronomy satellite mission, which will enable multi-wavelength observations of the celestial bodies and cosmic sources in X-ray and UV spectral bands simultaneously. The scientific payloads cover the Visible (3500-6000 Å), UV (1300-3000 Å), soft and hard X-ray regimes (0.5-8 keV; 3-80 keV). The uniqueness of ASTROSAT lies in its wide spectral coverage extending over visible, UV, soft X and hard X ray regions.

An artist’s impression of Astrosat

The scientific objectives of ASTROSAT are: Multiwavelength studies of cosmic sources, monitoring the X-ray sky for new transients, all sky survey in the hard X-ray and UV bands, broadband spectroscopic studies of X-ray binaries, AGN, SNRs, clusters of galaxies and stellar coronae, studies of periodic and non-periodic variability of X-ray sources and monitoring intensity of known sources and detecting outbursts and luminosity variations.

The 1500 kg satellite is to be launched by the operational PSLV to an altitude of 650 km with 8-degree orbital inclination in 2010 from Satish Dhawan Space Centre, Sriharikota. The useful life of the mission is expected to be about 5 years.

ASTROSAT will carry a complement of astronomy instruments sensitive over a wide spectral range. The payloads onboard ASTROSAT are:
1. Three Large Area Xenon-filled Proportional Counters (LAXPCs) in 3-100 keV band for timing and spectral studies
2. Cadmium Zinc Telluride (CZT) array with coded mask aperture for hard X-ray imaging and spectral studies in 10-100 keV
3. Soft X-ray Telescope (SXT) with CCD camera for timing and variability studies in the X-ray bandwidth of 0.3 to 10 keV
4. Scanning X-ray Sky Monitor (SSM) for timescales and luminosity variations in 2-10 keV using proportional counter system
5. Ultra Violet Imaging telescope (UVIT) will cover visible, near ultra violet and far ultra violet bands, in 130-600 nm bands.
6. Charge Particle Monitor (CPM) is a 10 mm cube of CsI (Tl) crystal viewed by a Photodiode; it aims at detecting high-energy particles during the satellite orbital path and alerts the instrumentation from possible damage.

During the year, the Engineering Model of BDH package has underwent qualification level thermovac tests. The thermal analysis of all payloads, Data Handling and BMU packages has been completed. The status of payloads onboard ASTROSAT are: (i) The Qualification Model of one detector system of the SSM payload, with all live electronics, has been exposed to launch environment loads and successfully qualified. The electronics card fabrication for SSM is in progress, (ii) For UVIT, the fabrication of INVAR tubes, aluminum tubes and focal plane assembly parts for the Engineering Model is completed. Fabrication and testing of various sub-systems and payloads are progressing satisfactorily.

 

[Kinetic]

Planetary Science and Exploration (PLANEX) Programme
The National programme in the Planetary Science and Exploration, PLANEX (short and long-term strategy) initiated through ISRO's Advisory Committee for Space Research (ADCOS) is visualised to undertake research and related activities in the field of Planetary Science and Exploration.

During the year, analysis of the returned data from Chandrayaan-1 payloads TMC and HySi were in progress. Laboratory investigations of meteorites, simulation studies to understand natural and induced nuclear radiations from planetary surfaces are other areas of planetary sciences research conducted under the PLANEX program. Design and development of payloads based on nuclear techniques, for future planetary missions of ISRO is the new activity under this programme.

Two of the lunar swirls, Reiner gamma (centered at 7.90N, 3010) in the basalt and Airy swirl (180S, 5.70) in the highlands have been studied for their maturation trends. The images sent by Moon Impact Probe onboard Chandrayaan-1 were analysed to trace its path on the lunar surface.

On Sept. 12, 2008, around 0830 hrs. Local time, the Sulagiri meteorite fell in the Krishnagiri district of Tamil Nadu, India. Petrological, chemical, oxygen isotopic, noble gas and cosmogenic nuclide studies have been carried out to classify Sulagiri (LL6) and its exposure age (32 Ma).

The ninth PLANEX workshop on 'Exploration of inner solar system objects' was held at the Rajasthan University, Jaipur, during January 5-9, 2009, for M.Sc/B. Tech students. Currently 15 projects are running under PLANEX and 3 new projects are under review. About 15 publications in both national and international journals have appeared during the year.

The installation of the Multi-Collector Noble Gas Mass Spectrometer (MC-NGMS) has been completed. The sample preparation system has been modified and presently the instrument is being standardised. Initial results were presented at a conference in November 2009.

Indian RT-2 Experiment onboard Russian CORONAS-Photon Satellite
RT-2 is a low energy gamma-ray spectrometer experiment aimed to study the solar hard X-rays in the energy range of 15 keV to 150 keV. It was launched onboard Russian CORONAS-Photon mission on 30 January 2009 from Russia. The main goal of the mission is to study solar hard electromagnetic radiation in the wide energy range from extreme UV up to high-energy gamma radiation (~ 2000 MeV). The primary instruments of the mission are high-energy radiation spectrometer NATALYA-2M (developed by Russia) and the low energy gamma ray spectrometer RT-2 (developed by India).

The RT-2 system comprised 3 detector modules namely RT-2/S, RT-2/G (Phoswich detectors), RT-2/CZT (CZT and CMOS detector) and one processing electronics RT-2/E.

RT-2 instruments were switched on during February 20, 2009. Currently, all the three detectors (RT-2/S, RT-2/G and RT-2/CZT) are working satisfactorily.

RT-2/S and RT-2/G detectors discovered a Gamma Ray Burst (GRB 090618) on June 18, 2009. The light curves of Gamma Ray Bursts (GRBs) plot the number of gamma rays detected against time (Fig.2 and 3). The entire data is consistent with the data from other satellites (KONUS-RF, KONUS-WIND and SWIFT) which have co-discovered the Burst. Further analysis on the data received is in progress.

RT-2/G Light curve of GRB 090618

YOUTHSAT
YOUTHSAT is a joint scientific space mission between Indian Space Research Organisation (ISRO) and Russian Federal Agency. It is a micro satellite carrying scientific payloads with participation from universities at graduate, postgraduate and research scholar level and would participate from testing of the payloads in laboratory to the utilisation of the data from payloads. Participation of young scientists will inculcate interest in space related activities and provide opportunities for realisation of future scientific payloads at the university level. YOUTHSAT is scheduled to be launched as auxiliary satellite along with Indian remote sensing satellite during 2010 with an orbital altitude of 630 km at an inclination of 97.9º.

YOUTHSAT is a participatory scientific mission with payloads from both Russia and India. It would be carrying three scientific payloads one from Russia and two from India.

* The Russian payload is a Sun observing payload called SOLRAD (Solar Radiation Detector), which would detect and monitor the radiation
[Solar flares and X-rays (10-100 keV), Gamma rays (0.02-10.0 MeV)] from the Sun. This payload is developed by Moscow University.
* RaBIT (Radio Beacon for Ionospheric Tomography) consisting of a dual frequency beacon to measure the total electron content of the ionosphere. RaBIT payload is developed by VSSC.
* LiVHySI (Limb Viewing Hyper Spectral Imager) would observe the limb of the atmosphere at the altitude of 80-800 km to image the atmosphere and record the airglow thereby analysing for atmospheric constituents. LiVHySI is jointly developed by VSSC and SAC.

Youthsat Solrad payload testing

SOLRAD will monitor the source i.e, the Sun and the other two experiments will monitor the way in which near Earth space gets effected due to the explosive events in the Sun's “Space Weather” effects. Hence the cause and the effect could be studied uniquely by YOUTHSAT mission.

CAWSES-India programme
Climate and Weather of Sun-Earth System (CAWSES), an ongoing international scientific programme launched by SCOSTEP (Scientific Committee on Solar-Terrestrial Physics) during 2004-2008, is a cooperative effort to bring the world's scientists under one umbrella to study the Sun-Earth interactive phenomena covering all salient aspects.

CAWSES INDIA has been conceived as a national program of ISRO's initiative in line with the international program of CAWSES. CAWSES provides a platform to the Indian scientific community to come together, define common science objectives and make concerted and coordinated efforts of research in the domain of the Sun-Earth system. The Phase I of CAWSES that lasted for four years with four major themes, viz., (a) Solar influence on Climate (b) Atmospheric coupling processes (c) Space Weather: Science and Applications and (d) Space Climatology.

The first phase of the CAWSES-INDIA programme has been successfully completed by bringing together the atmospheric and solar Terrestrial Physics community and executing certain thematic campaigns and also compiling the large available database into an user friendly form. During this Phase, 24 projects were executed involving 15 organisations/institutions in the country. Besides, two major observational campaigns and two science workshops were conducted and several results from these efforts have been published in peer-reviewed journals. A monogram on scientific results of CAWSES Phase-I has been brought out as an ISRO publication. The scheme is unique in that it is supporting several young scientists to carry out frontline research utilising data from satellites and a host of advanced instrumentation leading to their Ph D programme. CAWSES Phase I spanned four years (2005-2008) covering the decreasing phase of the solar cycle 23.

Microgravity Science/ Experiment
Space capsule Recovery Experiment (SRE-2)
Subsequent to the successful SRE-1 mission, ISRO solicited proposals from scientists and technologists for possible experiments in the SRE-2 mission. The payloads/experiments finalised for SRE-2 would study

Engineering model of JAXA Bioreactor

*
Gravitational effects during liquid phase sintering of powder metallurgy products/ study on tapping phenomenal potential of Carbon nano tubes for composites using Isothermal Heating Furnace Mk II. This experiment is a collaborative effort between IIT, Kanpur and VSSC.
*
Biological effects of Microgravity on E-coli bacteria: A genomic and proteomics approach using Bioreactor developed by CCMB, Hyderabad.

*
Growth of Plant kingdom based microbials (cyanobacteria) under microgravity condition using, JAXA Bioreactor.

*
Effect of Microgravity and high energy radiation on Gene Expression in relation to growth, yield and quality of medicinal plants, vegetables and rice seeds using a Biopan: Kerala Agricultural University and University of Pune collaboration.

*
Space radiations aboard recoverable space capsule using Dosimeter developed jointly by PRL and VSSC.

*
Electron flux density using Langmuir Probe at an altitude of 100-30 km during re-entry of the space capsule jointly by ISAC and BARC.

Currently, the payload accommodation studies have been completed and power, command and telemetry requirements are finalised. Mission design with payload operations and safe mode strategies are worked out.

CRABEX
The Indian Coherent Radio Beacon Experiment (CRABEX) has been initiated to investigate the equatorial ionospheric large scale processes like EIA (Equatorial Ionization Anomaly), ESF (Equatorial Spread F) etc., and their interrelationships. A network of ground based stations receiving the 150 MHz and 400 MHz transmissions from the Low Earth Orbiting Satellites (LEOS) is setup along the 77-780E longitude, from Thiruvananthapuram (8.50N) to Delhi (28.80N) covering the trough and crest of the equatorial ionization anomaly region. This network (CRABNET) is shown below. Low Earth Orbiting Satellites (LEOS) like OSCAR, COSMOS, CNOFS, RADCAL, etc., which transmit coherent beacon transmissions at 150 and 400 MHz are used to derive ionospheric total electron content (TEC) along different intersecting ray paths.

Locations of CRABNET stations

The area of maximum ray intersections is also marked. This network is unique as it covers both the northern crest and the trough region of the EIA, thus making it the longest tomography chain in the world.

 

[Kinetic]

Among the forth coming projects GSAT-4, GSAT-6, GAGAN, INSAT-3D and IRNSS are most important communication satellite projects Specially GSAT-6, I think when modified it can have excellent military applications in terms of netcentric warfare.

Among EOS, RISAT-1 and CARTOSAT-3 will revolutionize the reconn capabilities of Indian armed forces.

 

[Nemesis]

Are you trying to show off India's space prowess to our Pakistani members? There is already a sticky thread on Indian Space developments, why on earth are you wasting bandwidth by opening another thread?

 

[Kinetic]

Are you trying to show off India's space prowess to our Pakistani members? There is already a sticky thread on Indian Space developments, why on earth are you wasting bandwidth by opening another thread?

I don't start ten threads every day! Check it out. Many will be interested in reading aspects of Indian space research thats why I posted this thread.

Stop thinking about bandwidth! That is not your concern! If the mods feel its not required than they can delete the thread. Your worthless post is a perfect example of wasting bandwidth! If you have nothing to do with the thread than why you need to post? !!!

 

[Chanakyaa]

@kinetic,

Great and Superb effort.
Will place my thanks once i am on my lappy.

Awesome info. I am saving it and placing on my blog soon.

Thanks a million, keep ur good work going...