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Mission Design, Preflight and Flight Performance and Observations for Pad Abort Test


Affiliations
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
 

Abort system is initiated to take the Crew Module (CM) away from the launch vehicle in case of an emergency at lift-off or at any point of time after launch for a mission with crew onboard. Crew Escape System (CES)-based abort is carried out from launch pad and during the atmospheric phase of ascent flight. The design and operation of CES play a crucial role in providing abort capability for escape from launch vehicle and return of the crew back to Earth during critical phase of ascent flight. CES motors are used to pull CM away from the launch vehicle during this mode of abort. Mission simulation and analysis is necessary for the design of CES-based abort mission and for its configuration. This article discusses the mission design, challenges faced during the design and strategies formulated towards the successful execution of Pad Abort Test.

Keywords

Abort System, Flight Performance, Launch Vehicle, Mission Design.
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  • Hyle, C. T. et al., Abort Planning for Apollo mission. In AIAA 8th Aerospace Sciences Meeting, AIAA-70-0094, 1970.

  • Davidson, J. et al., Crew exploration vehicle ascent abort overview, AIAA-2007-6590. In AIAA Guidance, Navigation and Control Conference, August 2007.

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  • Dhaoya, N. et al., Mission design and trajectory simulation for CES. In Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015), 3–5 December 2015, Trivandrum, India, Paper id CP 89.


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  • Mission Design, Preflight and Flight Performance and Observations for Pad Abort Test

Abstract Views: 215  |  PDF Views: 86

Authors

Jayanta Dhaoya
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
N. Remesh
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
C. Ravikumar
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
P. Bhanumathy
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
A. K. Anilkumar
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
Abhay Kumar
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
V. Ashok
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India

Abstract


Abort system is initiated to take the Crew Module (CM) away from the launch vehicle in case of an emergency at lift-off or at any point of time after launch for a mission with crew onboard. Crew Escape System (CES)-based abort is carried out from launch pad and during the atmospheric phase of ascent flight. The design and operation of CES play a crucial role in providing abort capability for escape from launch vehicle and return of the crew back to Earth during critical phase of ascent flight. CES motors are used to pull CM away from the launch vehicle during this mode of abort. Mission simulation and analysis is necessary for the design of CES-based abort mission and for its configuration. This article discusses the mission design, challenges faced during the design and strategies formulated towards the successful execution of Pad Abort Test.

Keywords


Abort System, Flight Performance, Launch Vehicle, Mission Design.

References





DOI: https://doi.org/10.18520/cs%2Fv120%2Fi1%2F89-95