NSAT-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. ASTROSAT The ASTROSAT project is aimed at design, development, fabrication and launch of an astronomical observatory for studies of cosmic sources. ASTROSAT is envisaged to be a National Observatory which will be available for astronomical observations to any researcher in India. Although most of the observation time will be for the use of Indian researchers, a part of the ASTROSAT observation time will also be made available to International astronomical community on a competitive basis. ASTROSAT is planned to be launched by Polar Satellite Launch Vehicle (PSLV). The life of the satellite has been configured for a minimum period of 5 years. GSAT-6 & 6A GSAT-6 is a high power S-band communication satellite that will be co-located with GSAT-12, INSAT-4A and GSAT-10 at 83ºE.The satellite is configured around I-2K bus with a lift-off mass of 2200 kg. It is configured with CxS and SxC transponders. The S-band up and down links have high G/T and EIRP to be able to communicate with smaller ground terminals. This satellite will also provide a platform for developing technologies such as demonstration of large unfurlable antenna in satellites, handheld ground terminals and network management techniques that could be useful in future satellite based mobile communication applications. GSAT-6A will be a follow-on satellite planned to be launched by the end of 12th Five year plan. GSAT-7 GSAT-7 is a multi-band satellite carrying payloads in UHF, S-band, C-band and Ku-band. The satellite employs the standard 2000 Kg class bus (I-2K) platform with a power handling capability of around 3000 W and lift-off mass of 2550 Kg. It is planned to be launched during the second half of 2013 and to be positioned at 74oE. GSAT-9 GSAT-9 satellite is configured with 12 Ku-band transponders and to be positioned at 48ºE. The satellite is configured with 2000 Kg class (I-2K) bus with a power handling capability of around 2.8 KW and a lift-off mass of 2350 kg. Configuration of the satellite system has been finalised and realization is in progress. GSAT-11 GSAT-11 is an advanced communication satellite employing a 4000 Kg–6000 Kg class bus and is proposed to carry 32 Ku band user beams with corresponding gateway links operating in Ka band. The satellite will have power handling capability of around 10 KW. Spacecraft level Preliminary Design Review (PDR) has been completed and System level interfaces are _inalized. Activities for the development of structural and subsystem-qualification models are in progress. GSAT-14 GSAT–14 satellite with 6 Extended C band and 6 Ku band transponders is envisaged to enhance communication transponder capacity. The satellite employs the standard 2000 Kg class bus (I–2K) with a power handling capability of around 2.5 KW and a lift-off mass of 1980 kg. The spacecraft will be launched onboard GSLV–D5 Mission during second half of 2013. GSAT-15 GSAT-15 is a communication satellite planned to be positioned at 93.5ºE with a lift-off mass of about 3100kg and 6.8 KW power generation capacity. It is expected to function with a mission life of more than 12 years. The satellite will carry 18 Ku Band operational transponders and two channel GAGAN payload. GSAT-15 is planned to be launched onboard a procured launcher. GSAT-16 GSAT-16 is a communication satellite planned to be positioned at 55ºE with a lift-off mass of about 3100 kg and 6.8 KW power generation capacity. It is expected to function with a mission life of more than 12 years. The satellite will carry 12 Ku, 24 C and 12 Extended C-band transponders. GSAT-16 is planned to be launched onboard a procured launcher. IRNSS-1A Indian Regional Navigational Satellite System - IRNSS-1A, 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. IRNSS-1A is planned to be launched onboard PSLV-C22 in June 2013 while the full constellation is planned to be realised during 2014 time frame. Top Launch Vehicle / Forthcoming Launches PSLV-C22/IRNSS-1A Mission The first Satellite of Indian Regional Navigation Satellite System (IRNSS) constellation, IRNSS-1A will be launched by PSLV-C22 in June 2013. INSAT-3D Mission INSAT-3D is scheduled to be launched during mid July, 2013 by Ariane from Kourou French Guiana. GSAT-7 Mission GSAT-7 is scheduled to be launched during mid Aug, 2013 by Ariane from Kourou French Guiana. GSLV-D5/GSAT-14 Mission GSAT-14 is planned to be launched by GSLV-D5 during 2nd half of 2013 from Sriharikota. Mars Orbiter Mission Mars Orbiter Mission is planned to be launched by PSLV-C25 during October 2013 from Sriharikota. Top Future Launch Vehicle GSLV-Mk III 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-MkIII is a three stage heavy lift launch vehicle, designed for launching four tonne class of communication satellites to Geosynchronous Transfer Orbit (GTO). It has three propulsion stages and is 42.4 m tall with a lift-off weight of 630 tonnes. Two identical large solid strap-on boosters (S200) with 200 tonnes of solid propellant are strapped on either side of the core stage (L110) with 110 tonnes of liquid propellant loading. The upper stage is the cryogenic stage (C25) with 27 tonnes propellant loading. Carbon Fibre Reinforced Polymer (CFRP) payload fairing measures 5 m in diameter which can accommodate a payload volume of 100 cu m. Top 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). The Integrated Technical Review (ITR) of RLV-TD by the National Review Committee in October 2012 has concluded that launch of RLV-TD HEX-01 mission in September 2013 is feasible. Pre Project activities of Human Space Flight Mission Programme The objective of Human Spaceflight Programme is to undertake a human spaceflight mission to carry a crew of two to Low Earth Orbit (LEO) and return them safely to a predefined destination on earth. The programme is proposed to be implemented in defined phases. Currently, the pre project activities are progressing with a focus on the development of critical technologies for subsystems such as Crew Module (CM), Environmental control and Life Support System (ECLSS), Crew Escape System, etc. 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. Top Space Science Missions Mars Orbiter Mission Mars Orbiter Mission is ISRO’s first interplanetary mission to planet Mars with a spacecraft designed to orbit Mars in an elliptical orbit of 372 km by 80,000 km. Mars Orbiter mission is India’s next challenging technological mission out of the Earth’s gravitational field. The major demands will be critical mission operations and stringent requirements on propulsion, communications and other bus systems of the spacecraft. The primary driving technological objective of the mission is to design and realize a spacecraft with a capability to reach Mars (Martian transfer Trajectory), then to orbit around Mars (Mars Orbit Insertion) which will take about nine months time. Yet another technological challenge is to realize related deep space mission planning and communication management at a distance of nearly 400 million km. The polar Satellite Launch Vehicle PSLV will be used to inject the spacecraft from SDSC, SHAR in the 250 X 23000 km orbit with an inclination of 17.864 degree. As the minimum energy transfer opportunity from Earth to Mars occurs once in 26 months, the opportunity in 2013 demands a cumulative incremental velocity of 2.592 km/sec. This satellite will also carry compact science experiments, totaling a mass of 15 kg, as listed in the table below : Payload Primary Objective Lyman Alpha Photometer (LAP) Escape processes of Mars upper atmosphere through Deuterium/Hydrogen Methane Sensor for MARS (MSM) Detect presence of Methane Martian Exospheric Composition Explorer (MENCA) Study the neutral composition of the Martian upper atmosphere MARS Colour Camera (MCC) Optical imaging TIR imaging spectrometer (TIS) Map surface composition and mineralogy Space Capsule Recovery Experiment (SRE-II) SRE-2 Project was formed with the main objective of realising a fully recoverable capsule and to provide a platform to conduct micro-gravity experiments. SRE capsule has four major hardware, namely, Aero Thermo-structure (ATS), Spacecraft platform, deceleration and floatation system and payloads. 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. Chandrayaan-2 Chandrayaan-2 will be an Indo-Russian Mission. It is an advanced version of the previous Chandrayaan-1 mission to Moon. ISRO’s capability to soft-land on the lunar surface will be demonstrated with this mission. Chandrayaan-2 is configured as a two module system comprising of an Orbiter Craft module (OC) and a Lander Craft module (LC) carrying the Rover developed by ISRO. Both the modules are interfaced mechanically by an inter module adapter. The Orbiter Craft with payloads onboard will orbit around the moon and perform the objectives of remote sensing the moon. The payloads on the orbiter will conduct mineralogical and elemental studies of the Moon’s surface. The Lander Craft with scientific payloads will soft land on the lunar surface at a predetermined location on the lunar surface. Payloads for Lander are under finalization. The Rover is released by the Lander Craft and has the mission objective of performing mobility activities on low gravity and vacuum of Moon surface with Semi-Autonomous navigation and hazard avoidance capability. The Laser Induced Breakdown Spectroscope (LIBS) and Alpha Particle X-Ray Spectrometer (APXS) payloads onboard Rover would perform elemental analysis of the lunar surface near the landing site. Aditya-1 Aditya-1 is a scientific mission designed to study solar corona. The major scientific objectives of the proposed space solar coronagraph are to achieve a fundamental understanding of the physical processes that (a) Heat the solar corona (b) Accelerate the Solar Wind, and (c) Produce Coronal Mass Ejections (CMEs). The proposed design of the coronagraph instrument is aimed to understand High Frequency Intensity Oscillations(~1Hz), Dynamics of Coronal Loops with High Cadence, Magnetic Field Topology and CMEs close to the Solar Disk. Aditya-1 is planned to be launched by PSLV into 800 km polar orbit. It will carry an internally occulted solar coronagraph of mass 130 kg. The 20 cm coronagraph, having a Field of View of corona from 1.05 R to 3.0 R, uses an off axis parabolic mirror. The payload will have three CCD detectors system with a capability of simultaneous imaging in 6374 Å, 5303 Å and in 5800 Å for continuum/broadband. Top Satellite Navigation GAGAN The Indian Space Research Organisation and the Airports Authority of India (AAI) are implementing the GAGAN project as a Satellite Based Augmentation System for the Indian Airspace. The primary objective of GAGAN is to establish a certified satellite based augmentation system for safety-of-life applications The functional performance and operational requirements of GAGAN will be governed by the specifications as mentioned in the international standards. In the GAGAN-FOP, all the ground elements, namely, 15 Indian Reference Earth Station (INRES), 2 Indian Master Control Centre (INMCC) and 2 Indian Land Uplink Station (INLUS) were established and integrated. In addition to the existing Optical Fibre Cable (OFC) Data Communication Network, VSAT link is also established between almost all INRES sites and INMCC. The establishment of third INLUS at New Delhi and an additional data communication network are in progress. The GAGAN Indian Land Uplink Station INLUS-B was integrated with GSAT-8 satellite. Stability test was run with updated sets of Operation Specific and Station Specific Parameters. 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Posted on: Wed, 05 Jun 2013 19:46:05 +0000
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