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India's latest advancements in space technology
ISRO annual report 2011-2012
http://isro.org/pdf/AnnuaReport2012.pdf
Important milestones......
Space Transportation:
Semi-cryogenic Project: India developing 2000 kN thrust semi cryogenic engine for future Heavy Lift Unified Launch Vehicles.
Semi cryogenic Project envisages development of a 2000 kN semi cryogenic engine for the future heavy lift Unified Launch Vehicles (ULV) and Reusable Launch Vehicles (RLV). The semi cryogenic engine uses a combination of Liquid Oxygen and Isrosene as propellants which are eco-friendly and cost effective. Engine design, generation of fabrication drawing of sub systems and integration drawings have been completed. Preliminary Design Review of Engine Gimbal Control system have been completed and technical specification document of both Hydraulic Actuation System and Hydraulic Power System generated. Hypergolic igniter trials have been successfully demonstrated. Single element of pre burner and thrust chamber are realised. 3 tests have been completed for single element Semicryo pre-burner injector.
Reusable Launch Vehicle (RLV-TD): A series of technology demonstration missions have been conceived towards realising a Two Stage to Orbit fully re-usable launch vehicle. 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.
Major accomplishments of RLV-TD during the period are the second static test of HS9 motor with Secondary Injection Thrust Vector Control system, commissioning of Integration facility and structural qualification tests of all wing fuselage joints. Four National Expert Committees reviewed various design, testing and manoeuvre aspects. Apart from this, Reaction Control System jet interaction studies and aero characterisation for the vehicle were completed. Elevon and rudder deflection studies were carried out for vehicle and mission. Updated version of on-board software for Digital Auto Pilot Flight Requirements Document and data set documents were released based on National Committee recommendations. All Navigation, Guidance and Control hardware, ceramic servo accelerometer and Hybrid Data Second static test of HS9 motor Acquisition System (HDAS) were realised. Miniaturised Flush Air Data Systems (FADS) electronics was also realised and Advanced Vehicle Imaging System was introduced. The elliptical toroid tank for storing Secondary Injection Thrust Vector Control injectant was fabricated and subjected to hydraulic pressure test.
Air Breathing Propulsion Project (ABPP) : Air-Breathing propulsion along with Reusable Launch Vehicle technology is the technological key for low cost access to Space. Unlike conventional rockets which carry both oxygen and fuel onboard, Air breathing propulsion systems make use of atmospheric oxygen for combustion resulting in substantial improvement in payload fraction and thus reducing overall costs. VSSC has taken up a systematic R&D programme demonstrating stable supersonic combustion through a series of ground tests on the Air-Breathing Propulsion Technology and the flight demonstration is planned with the Advanced Technology Vehicle.
Development activities towards active scramjet engine and high-pressure gaseous fuel feed system are progressing well for the ATV D-02 Scramjet Gas Monitor Cabin Lights
High pressure gaseous fuel feed system RH 200 launch from TERLS range Characterisation. The flight is targeted in the first half of 2012. Aero-Thermo-Structural design of Engine module is completed. Engine fabrication is in progress. Complex AB Propulsion testing (air intake and combustor) and analysis (Computational Fluid Dynamics and Thermo Structural) are also conducted. High temperature scramjet combustor ground tests up to 1950 K were successfully carried out at FKPNITsRKP, Russia using Silicon Carbide (SiC) coated Carbon/Carbon leading edges. Detailed scramjet full engine CFD simulations (with and without combustion) were carried out for Mach number window 6.0±0.5 and confirmed discernable change in acceleration and engine flow starting. Integration mockup of high pressure gaseous hydrogen Fuel Feed System
with gas bottles / modules and AA2014 structure were carried out at LPSC. Substantial progress is made towards commissioning of Air Breathing propulsion test facilities at NAL, Bangalore and LPSC, Mahendragiri.
Human Spaceflight Programme (HSP): The government has provided funds for pre-project phase activities. During this phase, it is proposed to develop new and critical technologies required for Human Space flight Programme, which includes Crew Module (CM) systems, Environmental Control & Life Support Systems , Flight Suit, Crew Escape System and Service Module Systems.
GSLV mk III: The GSLV-Mark III vehicle, a heavy lift launch vehicle, designed for launching 4-5 ton communication satellites of INSAT-4 class is in the advanced stages of development. This vehicle is having three propulsion stages and is 42.4m tall with a lift-off weight of 630 ton. Two identical large solid strap-on boosters with 200 ton of solid propellant are attached on either side of the core stage which is a liquid stage with 110 ton of propellant loading. The next stage is the Cryogenic C25 Liquid Oxygen/Liquid Hydrogen (LOX/LH2) based cryogenic stage. The Carbon Fibre Reinforced Plastic (CFRP) payload fairing measures 5 m in diameter. Cryogenic Engine 20 (CE20) thrust chamber test article is ready and interfacing with test stand has been carried out. The avionic packages for proto equipment bay have been delivered for integration and Proto Equipment Bay harnessing was completed and powered. Telemetry, Tracking and Command checks have been completed.
GSLV mk II and GSLV mk I: The next two GSLV missions are planned to be conducted as developmental flights. Flight testing of GSLV-D5 with 3.4 m Payload Fairing and indigenous cryo stage is targeted for the middle of 2012 and GSLV-D6 with 4m Payload Fairing and indigenous cryo stage is planned in April 2013.
Space Capsule Recovery Experiment –2 (SRE-2) : SRE-2 Project was formed with the main objective of realising a fully recoverable capsule and to provide a platform to conduct microgravity experiments. Space Capsule Recovery Experiment capsule has four major hardware, namely Aero Thermo-structure (ATS), Space craft platform, deceleration and floatation system and payloads. New technology developments for SRE–2 include Carbon-Carbon Nose Cap, indigenous Ultra High Frequency Beacons, etc. Aero Thermo Structure with silica tile Thermal Protection System, qualification models of payloads, solar panels, parachutes and floats were realised. Mission Management Unit hardware is ready and On-board Software In Loop tests for de-boost phase completed.
Advanced Technology Vehicles (ATVP) : The Advanced Technology Vehicle (ATV) has the unique capability to take a payload of 200-400kg up to an altitude of 800 km. Ascent of the vehicle in a direct vertical profile makes it an excellent platform for space research, best suited for the studies of upper atmospheric features and short period transient phenomena / events in the atmosphere. ATV also provides a cost effective platform for the study of microgravity conditions with up to 10 minutes of microgravity at levels better than 100 g which can be used for microgravity experiments in fluid physics, combustion research, materials sciences, biology as well as to perform precursor experiments for launch vehicles, satellites and manned missions. Post flight data analysis for ATV D-01 was completed. Vehicle systems for ATV D-02 mission are getting ready.
Twelve RH200 flights with chaff payload were successfully conducted from Thumba Equatorial Rocket Launching Station Range for wind measurement. Two proof motor tests were conducted for the propellant design and evaluation of IIST Student Rocket Flight (Vyom), which is RH200 motor with revised grain design.
New modern Launch Control Centre (LCC) at Satish Dhawan Space Centre SHAR, Sriharikota which will be used for future launches.
New IRNSS satellite control centre with four 7.2 m antennas and one 11 m antenna has been installed at Byalalu, Karnataka.
Satish Dhawan Supercomputing Facility: 220 teraflop supercomputer unveiled by VSSC.
Titanium Sponge Production Plant: A Titanium Sponge Production Plant with a capacity of 500 TPA was set up jointly by ISRO and Government of Kerala at Chavara using the indigenous technology developed by Defence Metallurgical Research Laboratory (DMRL), Hyderabad.
6 MW Plasma Wind Tunnel Facility: This facility catering to the system level evaluation of
re-entry thermal protection systems for future missions like Reusable Launch Vehicle, Space Capsule Recovery Experiment, Human Spaceflight Programme etc. was fully commissioned in 2011 at a total budget outlay of Rs.21.50 Cr. Characterisation up to a power level of 3.8 MW is completed.
Thrust Chamber Test Facility for cryogenic engines: For testing of cryogenic engine thrust chambers, Thrust Chamber Test Facility has been commissioned at LPSC, Mahendragiri.
Space Science:
Chandrayaan-2 updates:
Chandrayaan-2 mission is planned to have an Orbiter/Lander/Rover configuration. The mission is expected to be
realised by 2014. It is an Indo-Russian collaborative mission. The scientific objectives of the mission are 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 and direct analysis) using Robotics/Rover.
Orbiter Craft (OC)
Chandrayaan-2 Structure configuration has been changed from I2K
to I3K configuration due to the revision of payload lift off capacity
by GSLV. This change will enable accommodating larger propellant
tanks. The mission strategy was revised to inject the satellite in a
lower initial orbit (170 X 16980km) with a higher lift-off mass of
3200kg and the Propulsion System Configuration changed to
increase fuel carrying capability of the satellite.
The other activities completed are: finalisation of all electrical and
mechanical interfaces including the payload interfaces; Preliminary
Design Reviews (PDRs) of Bus Systems (Power, Attitude Orbit
Control Electronics, Telemetry, Tracking and Command Baseband
Systems, RF Systems, Data Handling System, Structure, Thermal Control System, Propulsion System); all
systems accommodation studies and initial thermal analysis.
Rover
The activities completed so far are: configuration of Rover and Payloads, Preliminary Design of all subsystems
and PDR of all Rover subsystems. Lunar Terrain Test Facility has been established at ISITE for simulation of
reduced ‘g’ and Lunar soil.
Russian-GK Lander Craft (LC) Interfaces:
Three interface meetings took place with Russian delegates apart
from regular mail communication and teleconferences. OC-LC and LC-Rover Interfaces and Lander-Rover
communication scheme were finalised. Landing site identification has been initiated and schedules/sequence of
activities is worked out.
Indian MARS Mission
ISRO is planning to undertake a mission to the planet Mars during 2013 timeframe. The Project Report for Indian Mars Orbiter mission has been submitted for approval of Government of India. The tentative scientific objective for the Mars mission will be to focus on life, climate, geology, origin, evolution and sustainability of life
on the planet.
Scientific payloads have been short-listed by the ADCOS review committee. Baseline, solar array and reflector configuration of the satellite have been finalised. Frequency filing for communication subsystem is under progress.
Solar mission: ADITYA-1 space based Solar Coronagraph
ADITYA-1 is the first space based Solar Coronagraph intended to study the outermost region of the sun called Corona. ADITYA-1 in the visible and near IR bands will study the Coronal Mass Ejection such as the coronal magnetic field structures, evolution of the coronal magnetic field etc., and consequently the crucial physical parameters for space weather.
The activities of ADITYA-1 are: MoU signed with the IIA for development and delivery of solar coronagraph payload; preliminary design of the optical systems of ADITYA-1 finalized and design document generated; Preliminary Design Review of the optical design completed; Trade-off studies on the selection of detector system completed and the list of subsystem packages along with power and mass budget generated. Mechanical reconfiguration of the satellite is in progress.
Astronomy mission: ASTROSAT
ASTROSAT is the first dedicated Indian Astronomy mission, which will enable multi-wavelength observations of the celestial bodies, cosmic sources in X-ray, visible 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.
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.
Planetary Science and Exploration (PLANEX)
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.
The activities in the PLANEX program during the year are Centred around investigations on meteorites to understand early solar system processes, analysis of remote sensing data from lunar missions to understand surface features and surface processes on the Moon and development of laboratory prototypes of instruments for planetary exploration.
Unlike most other basins on the Moon, Orientale is relatively less flooded
by mare basalts, exposing much of the basin structure to view. The study concentrated to identify and estimate the mineral abundance in the Orientale basin based on the absorption features and the linear spectral unmixing hyperspectral techniques.
Two payloads for the Chandrayaan-2 mission, scheduled for launch in 2013 are under development. One of the payloads, X-ray Solar Monitor is for the orbiter and the second one, Alpha Particle X-ray Spectrometer is for the rover. A new technology of Wireless Sensor Network for Lunar and Planetary Exploration is also under development.
In addition to the two annual meetings, PLANEX Workshop and the PLANEX PIs annual review meeting, two data analysis workshops (both in collaboration with SAC, Ahmedabad) and a Brainstorming session on Mars Science and Exploration have been organised.
more to come......
ISRO annual report 2011-2012
http://isro.org/pdf/AnnuaReport2012.pdf
Important milestones......
Space Transportation:
Semi-cryogenic Project: India developing 2000 kN thrust semi cryogenic engine for future Heavy Lift Unified Launch Vehicles.
Semi cryogenic Project envisages development of a 2000 kN semi cryogenic engine for the future heavy lift Unified Launch Vehicles (ULV) and Reusable Launch Vehicles (RLV). The semi cryogenic engine uses a combination of Liquid Oxygen and Isrosene as propellants which are eco-friendly and cost effective. Engine design, generation of fabrication drawing of sub systems and integration drawings have been completed. Preliminary Design Review of Engine Gimbal Control system have been completed and technical specification document of both Hydraulic Actuation System and Hydraulic Power System generated. Hypergolic igniter trials have been successfully demonstrated. Single element of pre burner and thrust chamber are realised. 3 tests have been completed for single element Semicryo pre-burner injector.
Reusable Launch Vehicle (RLV-TD): A series of technology demonstration missions have been conceived towards realising a Two Stage to Orbit fully re-usable launch vehicle. 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.
Major accomplishments of RLV-TD during the period are the second static test of HS9 motor with Secondary Injection Thrust Vector Control system, commissioning of Integration facility and structural qualification tests of all wing fuselage joints. Four National Expert Committees reviewed various design, testing and manoeuvre aspects. Apart from this, Reaction Control System jet interaction studies and aero characterisation for the vehicle were completed. Elevon and rudder deflection studies were carried out for vehicle and mission. Updated version of on-board software for Digital Auto Pilot Flight Requirements Document and data set documents were released based on National Committee recommendations. All Navigation, Guidance and Control hardware, ceramic servo accelerometer and Hybrid Data Second static test of HS9 motor Acquisition System (HDAS) were realised. Miniaturised Flush Air Data Systems (FADS) electronics was also realised and Advanced Vehicle Imaging System was introduced. The elliptical toroid tank for storing Secondary Injection Thrust Vector Control injectant was fabricated and subjected to hydraulic pressure test.
Air Breathing Propulsion Project (ABPP) : Air-Breathing propulsion along with Reusable Launch Vehicle technology is the technological key for low cost access to Space. Unlike conventional rockets which carry both oxygen and fuel onboard, Air breathing propulsion systems make use of atmospheric oxygen for combustion resulting in substantial improvement in payload fraction and thus reducing overall costs. VSSC has taken up a systematic R&D programme demonstrating stable supersonic combustion through a series of ground tests on the Air-Breathing Propulsion Technology and the flight demonstration is planned with the Advanced Technology Vehicle.
Development activities towards active scramjet engine and high-pressure gaseous fuel feed system are progressing well for the ATV D-02 Scramjet Gas Monitor Cabin Lights
High pressure gaseous fuel feed system RH 200 launch from TERLS range Characterisation. The flight is targeted in the first half of 2012. Aero-Thermo-Structural design of Engine module is completed. Engine fabrication is in progress. Complex AB Propulsion testing (air intake and combustor) and analysis (Computational Fluid Dynamics and Thermo Structural) are also conducted. High temperature scramjet combustor ground tests up to 1950 K were successfully carried out at FKPNITsRKP, Russia using Silicon Carbide (SiC) coated Carbon/Carbon leading edges. Detailed scramjet full engine CFD simulations (with and without combustion) were carried out for Mach number window 6.0±0.5 and confirmed discernable change in acceleration and engine flow starting. Integration mockup of high pressure gaseous hydrogen Fuel Feed System
with gas bottles / modules and AA2014 structure were carried out at LPSC. Substantial progress is made towards commissioning of Air Breathing propulsion test facilities at NAL, Bangalore and LPSC, Mahendragiri.
Human Spaceflight Programme (HSP): The government has provided funds for pre-project phase activities. During this phase, it is proposed to develop new and critical technologies required for Human Space flight Programme, which includes Crew Module (CM) systems, Environmental Control & Life Support Systems , Flight Suit, Crew Escape System and Service Module Systems.
GSLV mk III: The GSLV-Mark III vehicle, a heavy lift launch vehicle, designed for launching 4-5 ton communication satellites of INSAT-4 class is in the advanced stages of development. This vehicle is having three propulsion stages and is 42.4m tall with a lift-off weight of 630 ton. Two identical large solid strap-on boosters with 200 ton of solid propellant are attached on either side of the core stage which is a liquid stage with 110 ton of propellant loading. The next stage is the Cryogenic C25 Liquid Oxygen/Liquid Hydrogen (LOX/LH2) based cryogenic stage. The Carbon Fibre Reinforced Plastic (CFRP) payload fairing measures 5 m in diameter. Cryogenic Engine 20 (CE20) thrust chamber test article is ready and interfacing with test stand has been carried out. The avionic packages for proto equipment bay have been delivered for integration and Proto Equipment Bay harnessing was completed and powered. Telemetry, Tracking and Command checks have been completed.
GSLV mk II and GSLV mk I: The next two GSLV missions are planned to be conducted as developmental flights. Flight testing of GSLV-D5 with 3.4 m Payload Fairing and indigenous cryo stage is targeted for the middle of 2012 and GSLV-D6 with 4m Payload Fairing and indigenous cryo stage is planned in April 2013.
Space Capsule Recovery Experiment –2 (SRE-2) : SRE-2 Project was formed with the main objective of realising a fully recoverable capsule and to provide a platform to conduct microgravity experiments. Space Capsule Recovery Experiment capsule has four major hardware, namely Aero Thermo-structure (ATS), Space craft platform, deceleration and floatation system and payloads. New technology developments for SRE–2 include Carbon-Carbon Nose Cap, indigenous Ultra High Frequency Beacons, etc. Aero Thermo Structure with silica tile Thermal Protection System, qualification models of payloads, solar panels, parachutes and floats were realised. Mission Management Unit hardware is ready and On-board Software In Loop tests for de-boost phase completed.
Advanced Technology Vehicles (ATVP) : The Advanced Technology Vehicle (ATV) has the unique capability to take a payload of 200-400kg up to an altitude of 800 km. Ascent of the vehicle in a direct vertical profile makes it an excellent platform for space research, best suited for the studies of upper atmospheric features and short period transient phenomena / events in the atmosphere. ATV also provides a cost effective platform for the study of microgravity conditions with up to 10 minutes of microgravity at levels better than 100 g which can be used for microgravity experiments in fluid physics, combustion research, materials sciences, biology as well as to perform precursor experiments for launch vehicles, satellites and manned missions. Post flight data analysis for ATV D-01 was completed. Vehicle systems for ATV D-02 mission are getting ready.
Twelve RH200 flights with chaff payload were successfully conducted from Thumba Equatorial Rocket Launching Station Range for wind measurement. Two proof motor tests were conducted for the propellant design and evaluation of IIST Student Rocket Flight (Vyom), which is RH200 motor with revised grain design.
New modern Launch Control Centre (LCC) at Satish Dhawan Space Centre SHAR, Sriharikota which will be used for future launches.
New IRNSS satellite control centre with four 7.2 m antennas and one 11 m antenna has been installed at Byalalu, Karnataka.
Satish Dhawan Supercomputing Facility: 220 teraflop supercomputer unveiled by VSSC.
Titanium Sponge Production Plant: A Titanium Sponge Production Plant with a capacity of 500 TPA was set up jointly by ISRO and Government of Kerala at Chavara using the indigenous technology developed by Defence Metallurgical Research Laboratory (DMRL), Hyderabad.
6 MW Plasma Wind Tunnel Facility: This facility catering to the system level evaluation of
re-entry thermal protection systems for future missions like Reusable Launch Vehicle, Space Capsule Recovery Experiment, Human Spaceflight Programme etc. was fully commissioned in 2011 at a total budget outlay of Rs.21.50 Cr. Characterisation up to a power level of 3.8 MW is completed.
Thrust Chamber Test Facility for cryogenic engines: For testing of cryogenic engine thrust chambers, Thrust Chamber Test Facility has been commissioned at LPSC, Mahendragiri.
Space Science:
Chandrayaan-2 updates:
Chandrayaan-2 mission is planned to have an Orbiter/Lander/Rover configuration. The mission is expected to be
realised by 2014. It is an Indo-Russian collaborative mission. The scientific objectives of the mission are 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 and direct analysis) using Robotics/Rover.
Orbiter Craft (OC)
Chandrayaan-2 Structure configuration has been changed from I2K
to I3K configuration due to the revision of payload lift off capacity
by GSLV. This change will enable accommodating larger propellant
tanks. The mission strategy was revised to inject the satellite in a
lower initial orbit (170 X 16980km) with a higher lift-off mass of
3200kg and the Propulsion System Configuration changed to
increase fuel carrying capability of the satellite.
The other activities completed are: finalisation of all electrical and
mechanical interfaces including the payload interfaces; Preliminary
Design Reviews (PDRs) of Bus Systems (Power, Attitude Orbit
Control Electronics, Telemetry, Tracking and Command Baseband
Systems, RF Systems, Data Handling System, Structure, Thermal Control System, Propulsion System); all
systems accommodation studies and initial thermal analysis.
Rover
The activities completed so far are: configuration of Rover and Payloads, Preliminary Design of all subsystems
and PDR of all Rover subsystems. Lunar Terrain Test Facility has been established at ISITE for simulation of
reduced ‘g’ and Lunar soil.
Russian-GK Lander Craft (LC) Interfaces:
Three interface meetings took place with Russian delegates apart
from regular mail communication and teleconferences. OC-LC and LC-Rover Interfaces and Lander-Rover
communication scheme were finalised. Landing site identification has been initiated and schedules/sequence of
activities is worked out.
Indian MARS Mission
ISRO is planning to undertake a mission to the planet Mars during 2013 timeframe. The Project Report for Indian Mars Orbiter mission has been submitted for approval of Government of India. The tentative scientific objective for the Mars mission will be to focus on life, climate, geology, origin, evolution and sustainability of life
on the planet.
Scientific payloads have been short-listed by the ADCOS review committee. Baseline, solar array and reflector configuration of the satellite have been finalised. Frequency filing for communication subsystem is under progress.
Solar mission: ADITYA-1 space based Solar Coronagraph
ADITYA-1 is the first space based Solar Coronagraph intended to study the outermost region of the sun called Corona. ADITYA-1 in the visible and near IR bands will study the Coronal Mass Ejection such as the coronal magnetic field structures, evolution of the coronal magnetic field etc., and consequently the crucial physical parameters for space weather.
The activities of ADITYA-1 are: MoU signed with the IIA for development and delivery of solar coronagraph payload; preliminary design of the optical systems of ADITYA-1 finalized and design document generated; Preliminary Design Review of the optical design completed; Trade-off studies on the selection of detector system completed and the list of subsystem packages along with power and mass budget generated. Mechanical reconfiguration of the satellite is in progress.
Astronomy mission: ASTROSAT
ASTROSAT is the first dedicated Indian Astronomy mission, which will enable multi-wavelength observations of the celestial bodies, cosmic sources in X-ray, visible 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.
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.
Planetary Science and Exploration (PLANEX)
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.
The activities in the PLANEX program during the year are Centred around investigations on meteorites to understand early solar system processes, analysis of remote sensing data from lunar missions to understand surface features and surface processes on the Moon and development of laboratory prototypes of instruments for planetary exploration.
Unlike most other basins on the Moon, Orientale is relatively less flooded
by mare basalts, exposing much of the basin structure to view. The study concentrated to identify and estimate the mineral abundance in the Orientale basin based on the absorption features and the linear spectral unmixing hyperspectral techniques.
Two payloads for the Chandrayaan-2 mission, scheduled for launch in 2013 are under development. One of the payloads, X-ray Solar Monitor is for the orbiter and the second one, Alpha Particle X-ray Spectrometer is for the rover. A new technology of Wireless Sensor Network for Lunar and Planetary Exploration is also under development.
In addition to the two annual meetings, PLANEX Workshop and the PLANEX PIs annual review meeting, two data analysis workshops (both in collaboration with SAC, Ahmedabad) and a Brainstorming session on Mars Science and Exploration have been organised.
more to come......
