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Design, Development and Flight Performances of Deceleration System


Affiliations
1 Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India
 

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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  • 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.


Abstract Views: 290

PDF Views: 143




  • Design, Development and Flight Performances of Deceleration System

Abstract Views: 290  |  PDF Views: 143

Authors

Johns Paul
Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India
Atin Aggarwal
Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India
Santhosh J. Nalluveettil
Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India
P. Purushothaman
Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India
M. Premdas
Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, India

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.

References





DOI: https://doi.org/10.18520/cs%2Fv120%2Fi1%2F122-128