Return and abort trajectory optimisation for reusable launch vehicles

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Abstract

Among the future space access vehicles, the lifting body spaceplane is the most promising approach to prevent damage to both the launcher and the payload in case of loss of thrust. The glide performances of the vehicle allow the recovery in both nominal and abort cases. The approach presented is used in the investigation of the unpowered descent paths of a sample vehicle through trajectory optimisation. The vehicle's downrange and crossrange limits are obtained for aborts in multiple flight conditions.
Original languageEnglish
Title of host publicationProceedings of the 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Place of PublicationReston, VA
Number of pages11
ISBN (Electronic)9781624104633
DOIs
Publication statusPublished - 2 Mar 2017
EventAIAA International Space Planes and Hypersonic Systems and Technology Conference - Xiamen, China
Duration: 6 Mar 20179 Mar 2017
Conference number: 21
https://www.aiaa.org/EventDetail.aspx?id=33740

Publication series

NameInternational Space Planes and Hypersonic Systems and Technologies Conferences
PublisherAmerican Institute of Aeronautics and Astronautics

Conference

ConferenceAIAA International Space Planes and Hypersonic Systems and Technology Conference
Abbreviated titleHypersonics 2017
CountryChina
CityXiamen
Period6/03/179/03/17
Internet address

Keywords

  • launch vehicles
  • trajectory optimisation
  • downrange
  • crossrange
  • payloads
  • recovery

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  • Cite this

    Toso, F., & Maddock, C. (2017). Return and abort trajectory optimisation for reusable launch vehicles. In Proceedings of the 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference [AIAA 2017-2250] (International Space Planes and Hypersonic Systems and Technologies Conferences). Reston, VA. https://doi.org/10.2514/6.2017-2250