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Ashok, V.
- Mission Design, Preflight and Flight Performance and Observations for Pad Abort Test
Abstract Views :223 |
PDF Views:90
Authors
Jayanta Dhaoya
1,
N. Remesh
1,
C. Ravikumar
1,
P. Bhanumathy
1,
A. K. Anilkumar
1,
Abhay Kumar
1,
V. Ashok
1
Affiliations
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 89-95Abstract
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
- 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.
- Davidson, J. et al., Orion crew exploration vehicle launch abort system guidance and control analysis overview. In AIAA Guidance, Navigation and Control Conference, AIAA 2008-7148, August 2008.
- 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.
- Evolution of Crew Escape System Configuration
Abstract Views :226 |
PDF Views:105
Authors
Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, IN
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 96-104Abstract
The Crew Escape System (CES) is used for safe return of crew in case of any malfunctioning of a launch vehicle during ascent, specially in the atmospheric phase of flight. In the present case, as no active control is employed, the aerodynamic stability of CES is essential for safe return of crew in case of any emergency during ascent phase. While finalizing the shape of CES, besides stability, other aerodynamic parameters like acoustic, thermal, structural load, etc. need to be analysed. Based on detailed studies using CFD, a conical-shaped CES has been finalized. This article discusses the challenges involved in aerodynamic shaping of CES and different parameters studied while finalizing the configuration.Keywords
Aerodynamic Coefficients, Crew Escape System, Launch Vehicle, Static Margin, Stability.References
- McCarthy, J. F., Ian Dodds, J. and Crowder, R. S., Development of the Apollo Launch Escape System. J. Space Craft, 1968, 5(8), 927– 932.
- Ashok, V. and Babu, T. C., Parallisation of Navier–Stoke code on a cluster of workstations. In Proceedings of the 6th International High Performance Computing Conference. Lecture Series in Computer Science, Springer Verlag, 1999.
- Balu, R., Babu, T. C., Ashok, V., Pradeep Kumar and Das, D., Development of low cost parallel computing platform for CFD applications. In Third AeSI Annual CFD Symposium, 11–12 August 2002.
- Sreenivasulu, J. et al., CFD analysis of a Launch vehicle with reverse flow nozzles – a validation study. Int. J. Aerospace Innov., 2013, 5(1).
- Sreenivasulu, J. et al., CFD analysis over a rocket configuration with and without canard. In 12th Annual CED Symposium, Bangalore, 11–12 August 2010.
- Aftosmis, M. J. and Rogers, S. E., Effects of jet-interaction on pitch control of a launch abort vehicle. AIAA Paper 2008-1281.
- Sreenivasulu, J. et al., Flow field analysis over a typical rocket with and without jet. In 10th Asian Symposium on Visualization, SRM University, Chennai, India, 1–5 March 2010.
- Sreenivasulu, J. et al., Aerodynamic analysis of a rocket configuration with grid fin. In Proceedings of the 37th National and 4th International Conference on Fluid Mechanics and Fluid Power, IIT Madras, Chennai, India, 16–18 December 2010.