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An Overview of Reusable Launch Vehicle Technology Demonstrator


Affiliations
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
2 ISRO Propulsion Research Complex, Mahendragiri 677 133, India
 

After the successful operationalization of Polar Satellite Launch Vehicle and Geo Synchronous Launch Vehicle, the Indian Space Research Organisation is in the process of developing Reusable Launch Vehicle technologies to achieve low-cost access to space. Towards this programme, a winged body configuration was conceived, which can fly at subsonic, supersonic and hypersonic Mach number regime, re-enter into the earth’s atmosphere and simulate the landing manoeuvre. The aerodynamic design, analysis and wind-tunnel testing, aerothermal and structural design, analysis and testing were carried out. Suitable solid motor with slow burn rate propellant was developed. Mission design, guidance and control schemes were implemented. In order to meet the above objectives, certain technologies and infrastructure were developed. The entire subsystems were integrated and a large number of flight measurements were made in the maiden successful flight of Reusable Launch Vehicle Technology Demonstrator in May 2016. The flight measurements and flight performance indicated that the design philosophy, testing schemes and approaches followed are in order, thus providing confidence to proceed to the next logical step in the development of Reusable Launch Vehicle Technologies.

Keywords

Flush Air Data System, Hypersonic Flight Test, Reusable Launch Vehicle Technology, Winged-Body Configuration.
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  • Motoda, T. and Miyazawa, Y., ALFLEX flight simulation analysis and flight testing. In 36th AIAA Aerospace Sciences Meeting and Exhibit, 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 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.

  • Ragab, M. M. et al., Launch vehicle recovery and reuse. AIAA, SPACE 2015 Conference and Exposition, 2015.

  • Tsuchiya, T. and Mori, T., Optimal design of two-stage-to-orbit space planes with air breathing engines. J. Spacecraft Rocket, 2005, 42(1), 90–97.

  • St. Germain et al., A small payload class TSTO vehicle concept utilizing rocket based combined cycle propulsion. 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2001-3516, July 2001.

  • Iranzo-Greus, D. et al., Evolved European space reusable space transportation (Everest) – system design process and current status. In 55th International Astronautical Congress, Vancouver, Canada, 2004.


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  • An Overview of Reusable Launch Vehicle Technology Demonstrator

Abstract Views: 348  |  PDF Views: 137

Authors

K. Sivan
Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, India
S. Pandian
ISRO Propulsion Research Complex, Mahendragiri 677 133, India

Abstract


After the successful operationalization of Polar Satellite Launch Vehicle and Geo Synchronous Launch Vehicle, the Indian Space Research Organisation is in the process of developing Reusable Launch Vehicle technologies to achieve low-cost access to space. Towards this programme, a winged body configuration was conceived, which can fly at subsonic, supersonic and hypersonic Mach number regime, re-enter into the earth’s atmosphere and simulate the landing manoeuvre. The aerodynamic design, analysis and wind-tunnel testing, aerothermal and structural design, analysis and testing were carried out. Suitable solid motor with slow burn rate propellant was developed. Mission design, guidance and control schemes were implemented. In order to meet the above objectives, certain technologies and infrastructure were developed. The entire subsystems were integrated and a large number of flight measurements were made in the maiden successful flight of Reusable Launch Vehicle Technology Demonstrator in May 2016. The flight measurements and flight performance indicated that the design philosophy, testing schemes and approaches followed are in order, thus providing confidence to proceed to the next logical step in the development of Reusable Launch Vehicle Technologies.

Keywords


Flush Air Data System, Hypersonic Flight Test, Reusable Launch Vehicle Technology, Winged-Body Configuration.

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DOI: https://doi.org/10.18520/cs%2Fv114%2Fi01%2F38-47