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Mission Design and Performance of RLV-TD


Affiliations
1 Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
 

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.
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  • 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.

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  • Mission Design and Performance of RLV-TD

Abstract Views: 371  |  PDF Views: 131

Authors

Jyothish R. Pillai
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
M. Mutyala Rao
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
P. Bhanumathy
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
Vijith Mukundan
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
Jaison Joseph
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
A. K. Anil Kumar
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
C. Ravikumar
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
Abhay Kumar
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India

Abstract


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





DOI: https://doi.org/10.18520/cs%2Fv114%2Fi01%2F101-108