FUTURE PROGRAMS OF ISRO

Transcription

1 FUTURE PROGRAMS OF ISRO FORTHCOMING SATELLITES Page 1 INSAT - 3D SARAL INSAT-3D, an exclusive meteorological satellite, is configured with advanced meteorological payloads - a 6 Channel Imager, 19 Channel Sounder along with Data Relay Transponder and Satellite Aided Search & Rescue payloads. The spacecraft platform is adopted from the standard I-2K bus with a power handling capability of around 1100 W with a lift off mass of 2090 kg. The Satellite for ARGOS and ALTIKA (SARAL) is a joint ISRO - CNES mission, and will be launched during , by PSLV-C20 into a sun-synchronous orbit with a local time of 6 pm descending node at an altitude of around 800 km. The Ka band altimeter, ALTIKA, provided by CNES consists of a Ka-band radar altimeter, operating at 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 Radio-positioning Integrated by Satellite (DORIS) on board enables 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. ASTROSAT ASTROSAT is a national multiwavelength space borne astronomy observatory, which would enable simultaneous observations of the celestial bodies, cosmic sources in X-ray and UV spectral bands. The uniqueness of ASTROSAT lies in its wide spectral coverage extending over visible ( Å), UV ( Å), soft X and hard X ray regions (0.5-8 kev; 3-80 kev). The satellite would be launched by PSLV to an altitude of 650 km with 8 o orbital inclination from Satish Dhawan Space Centre, Sriharikota. GSAT-6 GSAT-6 spacecraft is configured with five S-band beams to cover the Indian main land, each beam supporting one CxS-band forward link transponder and one SxC-Band return link transponder. Thus, the 5 beams will have paired five

2 GSAT-7 GSAT-9 GSAT-10 GSAT-11 GSAT-14 transponders. The communication link operates through a Hub. The spacecraft employs the standard I-2k has with a power generation capability of around 3.1 KW. The spacecraft weighs 2200 kg at lift-off. The payload uses a high power S-Band TWTA and a new technology 6m unfurlable antenna. 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. The satellite weighs 2330 kg with a payload power of 2000W. The configuration of the satellite has been finalised and the design of new payload elements is completed. GSAT-9 will carry 12 Ku band transponders with India coverage beam and a GAGAN payload. The satellite is planned to be launched during by GSLV. The platform system is based on I-2K satellite with a liftoff mass of 2330 kg and payload power of 2300W. GSAT-10 spacecraft, envisaged to augment the growing need of Ku and C-band transponders carries 12 Ku Band, 12 C Band and 12 Extended C Band transponders and GAGAN (GPS and GEO augmented navigation) payload. The spacecraft employs the standard I-3K structure with power handling capability of around 6 KW with a lift off mass of 3400 kg. Subsystem fabrication and testing is in progress to realise the spacecraft for launch during GSAT-11 is based on I-4K bus which is under advanced stage of development. The spacecraft can generate KW of power and can support payload power of 8KW. The payload configuration is on-going. It consists of 16 spot beams covering entire country including Andaman & Nicobar islands. The communication link to the user-end terminals operate in Ku-band while the communication link to the hubs operate in Ka-band. The payload is configured to be operated as a high data throughput satellite, to be realised in orbit in 2013 time frame. GSAT-14 is intended to serve as a replacement for EDUSAT as the spacecraft is configured with 6 Ku and 6 Ext C band transponders providing India coverage beams. In addition, the spacecraft also carries Ka band beacons, which are planned to be used to carry out studies related to rain and atmospheric effects on Ka band satellite communication links in Indian region. The spacecraft weighs around 2050 kg and is planned to be launched by GSLV with indigenous cryogenic upper stage. Page 2

3 IRNSS-1 Indian Regional Navigational Satellite System (IRNSS)-1, the first of the seven satellites of the IRNSS constellation, carries a Navigation payload and a C-band ranging transponder. The spacecraft employs an optimised I-1K structure with a power handling capability of around 1600W and a lift off mass of 1380 kg, and is designed for a nominal mission life of 7 years. The first satellite of IRNSS constellation is planned to be launched onboard PSLV during while the full constellation is planned to be realised during 2014 time frame. Page 3 LAUNCH VEHICLE / FORTHCOMING LAUNCHES PSLV-C20/SARAL Mission The Satellite for ARGOS and ALTIKA (SARAL) is a joint ISRO - CNES mission, will be launched by PSLV-C20 into a sun-synchronous orbit with a local time of 6 pm descending node at an altitude of around 800 km. The satellite is scheduled for launch during last quarter of PSLV-C21/SPOT-6 Mission SPOT-6, an advanced French Remote Sensing Satellite built by ASTRIUM SAS, will be launched onboard ISRO's Polar Satellite Launch Vehicle (PSLV-C21), during the second half of Along with SPOT - 6 Satellite (weighing nearly 800 kg), the PSLV, in its core alone configuration, will also carry other co-passenger payloads. PSLV-C22/IRNSS-1 Mission The first Satellite of Indian Regional Navigation Satellite System (IRNSS) constellation, IRNSS-1 will be launched by PSLV-C22 during 2nd half of GSLV-Mk III FUTURE LAUNCH VEHICLE The GSLV Mk III is conceived and designed to make ISRO fully self reliant in launching heavier communication satellites of INSAT-4 class, which weigh 4500 to 5000 kg. The vehicle envisages multi-mission launch capability for GTO, LEO, Polar and intermediate circular orbits. GSLV Mk III is designed to be a three stage vehicle which is 42.4 m tall with a lift off mass of 630

4 tonnes. The booster stage comprises two identical S-200 large solid boosters with 200 tonne of solid propellants that are strapped on to the L-110 core liquid stage. The upper stage is the C25 cryogenic stage. The payload fairing measures 5 m in diameter with a payload volume of 100 cu m. The development work on GSLV MkIII is progressing for the first experimental launch during Page 4 REUSABLE LAUNCH VEHICLE-TECHNOLOGY DEMONSTRATOR (RLV-TD) As a first step towards realizing 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). HUMAN SPACE FLIGHT MISSION PROGRAMME A study for undertaking human space flight to carry human beings to low earth orbit and ensure their safe return has been made by the department. The department has initiated pre-project activities to study technical and managerial issues related to undertaking manned mission with an aim to build and demonstrate the country s capability. The programme envisages the development of a fully autonomous orbital vehicle carrying 2 or 3 crew members to about 300 km low earth orbit and their safe return. Space Capsule Recovery Experiment (SRE-II) SPACE SCIENCE MISSIONS The main objective of SRE II is to realize a fully recoverable capsule and provide a platform to conduct microgravity experiments on Micro-biology, Agriculture, Powder Metallurgy, etc. SRE-2 is proposed to be launched onboard PSLV during Chandrayaan-2 Chandrayaan-2, India s second mission to the Moon, will have an Orbiter and Lander-Rover

5 module. ISRO will have the prime responsibility for the Orbiter and Rover; Roskosmos, Russia will be responsible for Lander. Chandrayaan-2 will be launched on India s Geosynchronous Satellite Launch Vehicle (GSLV-MkII) around timeframe. The science goals of the mission are to further improve the understanding of the origin and evolution of the Moon using instruments onboard Orbiter and in-situ analysis of lunar samples using Lander and Rover. Page 5 The following five payloads are selected for Orbiter. 1. Large Area Soft X-ray Spectrometer (CLASS) and Solar X-ray Monitor (XSM) for mapping the major elements present on the lunar surface. 2. L and S band Synthetic Aperture Radar (SAR) for probing the first few tens of meters of lunar surface for the presence of different constituents including water ice. SAR is expected to provide further evidence confirming the presence of water ice below the shadowed regions of the moon. 3. Imaging IR Spectrometer (IIRS) for mapping of lunar surface over a wide wavelength range for the study of minerals, water molecules and hydroxyl present. 4. Neutral Mass Spectrometer (ChACE-2) to carry out a detailed study of the lunar exosphere. 5. Terrain Mapping Camera-2 (TMC-2) for preparing a three-dimensional map essential for studying the lunar mineralogy and geology. Following two scientific payloads selected for Indian Rover would carry out elemental analysisof the lunar surface near the landing site 1. Laser Induced Breakdown Spectroscope (LIBS). 2. Alpha Particle Induced X-ray Spectroscope (APIXS). Aditya-1 The First Indian space based Solar Coronagraph to study solar Corona in visible and near IR bands. Launch of the Aditya mission is planned during the next high solar activity period ( ) The main objectives is to study the Coronal Mass Ejection (CME) and consequently the crucial physical parameters for space weather such as the coronal magnetic field structures, evolution of the

6 coronal magnetic field etc. This will provide completely new information on the velocity fields and their variability in the inner corona having an important bearing on the unsolved problem of heating of the corona would be obtained. Page 6 SATELLITE NAVIGATION GAGAN The Ministry of Civil Aviation has decided to implement an indigenous Satellite-Based Regional GPS Augmentation System also known as Space-Based Augmentation System (SBAS) as part of the Satellite-Based Communications, Navigation and Surveillance (CNS)/Air Traffic Management (ATM) plan for civil aviation. The Indian SBAS system has been given an acronym GAGAN - GPS Aided GEO Augmented Navigation. A national plan for satellite navigation including implementation of Technology Demonstration System (TDS) over the Indian air space as a proof of concept has been prepared jointly by Airports Authority of India (AAI) and ISRO. TDS was successfully completed during 2007 by installing eight Indian Reference Stations (INRESs) at eight Indian airports and linked to the Master Control Center (MCC) located near Bangalore. The next major milestone in GAGAN is the conduct of PSAT (Preliminary System Acceptance Testing) which has been successfully completed in Dec The first GAGAN navigation payload is slated on GSAT-8 which was launched on May 21, The second GAGAN payload is scheduled to be launched on GSAT-10 in the first quarter of The third GAGAN payload is planned on another GEO satellite.