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Authors
Affiliations
1 Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 122-128
Abstract
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.
Full Text
References
- Aggarwal, A., Paul, J., Nalluveettil, S. J., Purushothaman, P. and Premdas, M., Crew Module deceleration system integration for CARE mission – development challenges. In National Conference on Recent Trends in Aerospace Systems Integration and Testing, IPRC/ISRO, Mahendragiri, 2015.
- Knacke, T. W., Parachute Recovery Systems Design Manual, Report Number NWC TP 6575, Naval Weapons Center, China Lake, CA, 1991.
