Return and abort trajectory optimisation for reusable launch vehicles

Toso, Federico and Maddock, Christie; (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. International Space Planes and Hypersonic Systems and Technologies Conferences . American Institute of Aeronautics and Astronautics Inc, AIAA, CHN. ISBN 9781624104633 (https://doi.org/10.2514/6.2017-2250)

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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.

  • Item type:Book Section
    ID code:60557
    Dates:
    Date
    Event
    2 March 2017
    Published
    14 November 2016
    Accepted
    Notes:©2017 AIAA 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: American Institute of Aeronautics and Astronautics Inc, AIAA. DOI: 10.2514/6.2017-2250
    Subjects:Technology > Motor vehicles. Aeronautics. Astronautics
    Department:Faculty of Engineering > Mechanical and Aerospace Engineering
    Depositing user: Pure Administrator
    Date deposited:28 Apr 2017 11:53
    Last modified:24 Apr 2024 00:06
    URI:https://strathprints.strath.ac.uk/id/eprint/60557
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