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Old Tuesday, April 11, 2006
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Arrow Indian Space Report 2006, ISRO

http://www.isro.org/rep2006/Contentspage.htm

Space Transportation
http://www.isro.org/rep2006/Space%20Transportation.htm

Communication and Meteorological System
http://www.isro.org/rep2006/Communication.htm

Earth Observation System
http://www.isro.org/rep2006/EOS%20System.htm

SPECIAL NEWS:

CARTOSAT-1

CARTOSAT-1 was launched into a 617 km polar sun-synchronous orbit on May 5, 2005 on board PSLV-C6 from Satish Dhawan Space Centre SHAR. 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 Models (DEM). The data from CARTOSAT-1 are used for cartography, cadastral mapping updation, land use and GIS applications.

http://www.isro.org/rep2006/pic9.jpg

CARTOSAT-1 under test

The satellite has solid state recorder for data storage. Some of the new technological elements incorporated in CARTOSAT-1 include: improved star sensor, bus interface connecting control systems, star sensor, satellite positioning system and data handling, high efficiency Ga-As solar cells and new solar array drive mechanism. The launch of CARTOSAT-1 was preceded by integrated spacecraft test including thermo-vacuum test, vibration and acoustic tests before transportation to SDSC SHAR.

http://www.isro.org/rep2006/pic10.jpg

CARTOSAT-1 solar panel deployment test

The cameras on board the satellite were activated on May 7, 2005 and since then imaging operation is carried out regularly.

http://www.isro.org/rep2006/pic11.jpg

Phased array antenna employed in CARTOSAT-1

Technology Experiment Satellite (TES)

TES was launched on board PSLV-C3 in October 2001. The satellite is intended to demonstrate and validate technologies that could be used in the future cartographic satellite missions. Some of the technologies demonstrated in TES are 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, miniaturised TTC and power system and two-mirror-on-axis camera optics. TES also carries a panchromatic camera with a spatial resolution of 1 m.

CARTOSAT-2

CARTOSAT-2 is envisaged as an advanced remote sensing satellite carrying on board a single panchromatic camera capable of providing scene-specific spot imageries for cartographic and a host of other applications. The panchromatic camera is designed to provide better than 1 meter spatial resolution imageries with a swath of around 10 km. The satellite will have high agility with capability of steering along and across the track up to + 45 deg. It will be placed in a sun synchronous polar orbit of a nominal altitude of 630 km and could be brought to a special orbit of 560 km with revisit periods of 4 days and 1 day respectively. The 650 kg satellite is planned to be launched on board PSLV in 2006-07.

Some of the new technology elements incorporated on CARTOSAT-2 are two mirror-on-axis single camera using high-performance CFRP-based electro optic structure with 12k CCD, large size mirrors, JPEG like data compression, advanced solid state recorder, bus management unit housing telemetry, tele-command, attitude control, sensor processing, thermal management and power monitoring, high-torque reaction wheels, high-performance inertial systems and star sensors.

During the year, the flight structure of CARTOSAT-2 was realised, RCS elements integrated, electro-optic and light weighted mirrors have been integrated and the payload completed acceptance testing and data handling system and S-band and X-band RF systems were realised. Miniature Phased Array Antenna with single beam is under final stages of realisation. BMU hardware has been realised, high-torque wheels and DTG have been qualified and Dual Gimbal Antenna is in final assembly stage.


RISAT

Radar Imaging Satellite (RISAT) is a microwave remote sensing satellite carrying a Synthetic Aperture Radar (SAR) operating in C-band. SAR has its own illuminating source and does not depend on sunlight for taking the imagery. SAR payload is a planar active array antenna based on TR (Trans-Receiver Module Architecture) and measures 6 x 2 meter and weighs 900 kg. SAR, being an all weather-imaging sensor, is capable of taking images in cloudy and snow covered regions both during day and night. RISAT weighs about 1750 kg.

The satellite is planned to be launched on board PSLV in 2007-08. The new technology elements in RISAT include 160 x 4 Mbps bit rate data handling system, 0.3 Nm reaction wheels, SAR antenna deployment mechanism, 70 V power bus, thermal control of SAR antenna and phased array antenna with dual polarisation.

During the year, preliminary design review for electrical sub systems (BMU, RF elements, Power and Data handling) and AOCS elements (mission, sensors, AOCS, inertial elements) has been completed. Fabrication of qualification model of a tile has been realised. Baseline thermal control design has been arrived at. Procurement, testing and installation of 3D measuring instrument for integration and alignment of SAR antenna has been completed. Solar array configuration has been finalized and structural drawings are ready.


OCEANSAT-2

OCEANSAT-2 is envisaged to continue the services of OCEANSAT-1. OCEANSAT-2 will carry two payloads for ocean related studies, namely, Ocean Colour Monitor (OCM) and Ku-band Pencil Beam Scatterometer. An additional piggy-back payload called ROSA (Radio Occultation Sounder for Atmospheric studies) developed by the Italian Space Agency (ASI) is also proposed to be included. The major applications of data from OCEANSAT-2 are identification of potential fishing zones, sea state forecasting, coastal zone studies and inputs for weather forecasting and climatic studies.

OCEANSAT-2 is planned for launch by PSLV in 2007.

OCEANSAT-2 will be launched into a near polar sun-synchronous orbit of 720 km with equatorial crossing time of 12 noon. The repetitivity achievable will be two days.

OCM is a 8-band multi-spectral camera operating in the Visible – Near IR spectral range. This camera provides an instantaneous geometric field of view of 360 meter and a swath of 1420 km. OCM can be tilted up to + 20 degree along track. The Ku-band pencil beam scatterometer is an active microwave radar operating at 13.515 GHz providing a ground resolution cell of size 50 x 50 km. It consists of a parabolic dish antenna of 1 meter diameter which is offset mounted with a cant angle of about 46 degree with respect to earth viewing axis. This antenna is continuously rotated at 20.5 rpm using a scan mechanism with the scan axis along the +ve Yaw axis. By using two offset feeds at the focal plane of the antenna, two beams are generated which will conically scan the ground surface. The back scattered power in each beam from the ocean surface is measured to derive wind vector.
During the year, flight model OCM payload electronics has been realised, the camera assembly is in progress and scatterometer configuration was finalised. Fabrication of mainframe systems like Core power, RF systems BMU, and sensors have started and DC-DC converters for OCM, earth sensor, TME realised.


Second Launch Pad (SLP)

http://www.isro.org/rep2006/pic31.jpg

Air Breathing Propulsion
Air- Breathing rocket systems are the ones which use the atmospheric oxygen from their 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, the Air-Breathing systems become much lighter and more efficient leading to reduced overall costs. As the Air- Breathing systems have the capability to operate only during the atmospheric phase of flight, they always have to be adopted along with the conventional chemical rockets, for meeting the final orbital velocity requirements.

http://www.isro.org/rep2006/pic33.jpg

Supersonic combustion test

Air-Breathing engines like the turbojet engines used in aircraft have limitations of operating only up to a maximum of Mach number 3. To travel beyond these Mach number regimes, SCRAMJET propulsion is the only viable option. The development of SCRAMJET system is quite 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 the combustor.

As part of the advanced technology initiative in the area of Air-Breathing propulsion, the design, development, characterisation and realisation of the Supersonic Combustion Ramjet (SCRAMJET) has been successfully carried out through a series of ground tests and a stable supersonic combustion demonstrated for nearly 7 seconds with an inlet Mach number of 6 (six times the speed of sound). The breakthrough is significant in the context of this technology being in a very nascent stage of development the world over.

Reusable Launch Vehicle
Conceptual design of the auxiliary power system for reusable launch vehicle and initiation of studies for the development of 2000 kN thrust semi-cryogenic engine have been undertaken as part of developments related to technologies for reusable launch vehicles. Aerodynamic and baseline characterisation, reference trajectory for the mission, avionics configuration, structural design and fabrication process studies have also been completed.

Space-capsule Recovery Experiment (SRE)
http://www.isro.org/rep2006/pic32.jpg

INSAT-4A in its final stages of inspection
http://www.isro.org/rep2006/Insat4A.jpg

GSAT-4
GSAT-4 is envisaged as a technology demonstrator. The communication payload consists of multi-beam Ka-band bent pipe and regenerative transponder and navigation payload in C-band, L1 and L5 bands. GSAT-4 will also carry TAUVEX-II, a scientific payload comprising three Ultra-Violet band telescopes developed by Tel Aviv University and Israel space agency, ELOP, for surveying a large part of the sky in the 1400-3200 Å wavelengths.
http://www.isro.org/rep2006/pic8.jpg

Ka-band multiple beam antenna for GSAT-4

GSAT-4 employs several new technologies like bus management unit, miniaturised dynamically tuned gyros, lithium-ion battery, 70 Volt bus for Ka-band TWTAs and electric propulsion. GSAT-4 also incorporates technological experiments like on-board structural dynamic experiment, thermal control coating experiment and vibration beam accelerometer. With a lift-off mass of about 2180 kg, the spacecraft generates 276 W of power in summer solstice.

GSAT-4 is planned for launch by GSLV during 2006-07.

During the year, structural interfaces for TAUVEX were finalised and bonding of central cylinder completed. Thermal design and motorised deployment and pointing mechanism for Ka-band reflector finalised and design of TAUVEX steering mechanism completed.
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