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Ravikumar, C.
- Mission Design and Performance of RLV-TD
Abstract Views :208 |
PDF Views:93
Authors
Jyothish R. Pillai
1,
M. Mutyala Rao
1,
P. Bhanumathy
1,
Vijith Mukundan
1,
Jaison Joseph
1,
A. K. Anil Kumar
1,
C. Ravikumar
1,
Abhay Kumar
1
Affiliations
1 Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, IN
1 Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 101-108Abstract
Renewed interest in re-usable launch vehicles has led to the evolution of technology demonstration concepts, where the prime objective is to demonstrate new technologies at reduced cost and shorter turnaround time. This article presents details of both ascent and descent mission design of a low-cost Reusable Launch Vehicle Technology Demonstration (RLV-TD) programme. The technology demonstrator vehicle is boosted to hypersonic Mach number using a solid booster. During ascent phase, the vehicle was flown in a gravity turn trajectory to minimize structural loads on it. In the descent phase, an optimum angle of attack profile as a function of Mach number was computed to limit dynamic pressure, load factor and achieve vehicle trim with minimum control surface deflection. The mission design parameters were evaluated using Monte Carlo analysis utilizing six degrees of freedom simulations. Comparison of actual flight performance with pre-flight prediction is also made this article. Flight performance exhibits close match with the pre-flight predictions.Keywords
Flight Performance, Reusable Launch Vehicles, Mission Design, Pre-Flight Predictions.References
- Motoda, T. and Miyazawa, Y., ALFLEX flight simulation analysis and flight testing. In AIAA, Aerospace Sciences Meeting and Exhibit, 36th Reno, NV, USA, 12–15 January 1998, p. 12.
- Bahm, C., Baumann, E., Martin, J., Bose, D., Beck, R. E. and Strovers, B., The X-43A Hyper-X Mach 7 flight 2 guidance, navigation and control overview and flight test results, American Institute of Aeronautics and Astronautics, AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, AIAA Paper 2005-3275, May 2005.
- Haya-Ramos, R. et al., Validation of the IXV mission analysis and flight mechanics design. In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, Tours, France, AIAA 2012-5966, 24–28 September 2012.
- Joseph, J. et al., Trajectory design with thrust profile optimization for ascent phase of a hypersonic sub-orbital demonstration mission. In 58th International Astronautical Federation Conference, Hyderabad, 21–24 September 2007.
- Merel, M. H. and Mullen, F. J., Analytic Monte Carlo error analysis. J. Spacecraft Rockets, 1968, 5(11), 1304–1308.
- Bowker, A. H. and Lieberman, G. I., Engineering Statistics, Prentice Hall, NJ, USA, 1972, 2 edn, p. 19.
- Mission Design, Preflight and Flight Performance and Observations for Pad Abort Test
Abstract Views :216 |
PDF Views:86
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.