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Human Spaceflight Programme (HSP) of Indian Space Research Organisation is proposed with the objective of carrying two crew members to low Earth orbit and bring them back safely to a predetermined location on Earth. The deceleration system for the programme has been designed for a 4-tonne class payload and shall cater to the requirements of nominal as well as abort missions. In order to finalize the parachute configurations and deployment sequence, detailed studies and development tests, starting from wind tunnel tests to full-scale air-drop tests were carried out. After successful structural and functional qualification of the parachutes and the various subsystems, the system was used to safely recover the module in the Crew Module Atmospheric Re-entry Experiment, the first unmanned spaceflight of HSP. This article provides details on the system configurations, deployment sequence and numerous tests that have been carried out till now in order to make the system worthy of manned flights in future.

Keywords

Abort Missions, Deceleration System, Deployment Sequence Parachutes, Manned Flights.
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