Future Launch Vehicle

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.

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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.

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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 :           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.