Vehicle and Mission Design of a Future Small Payload Launcher

Maddock, C. A. et al. (2017) Vehicle and Mission Design of a Future Small Payload Launcher. In: 21st AIAA International Space Planes and Hypersonics Technologies Conference, Xiamen, China, 06-09 Mar 2017, ISBN 9781624104633 (doi:10.2514/6.2017-2224)

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This paper presents the conceptual design and performance analysis of a partially reusuable space launch vehicle for small payloads. The system uses a multi-stage vehicle with rocket engines, with a reusuable first stage capable of glided or powered flight, and expendable upper stage(s) to inject a 500 kg payload in different low Earth orbits. The space access vehicle is designed to be air-launched from a modified aircraft carrier. The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs. A final design solution is presented showing the range of achievable orbits looking at maximising the altitude for injection into circular orbits at different inclinations.

Item Type:Conference Proceedings
Additional Information:This work was funded by the UK Space Agency through the National Space Technology Programme (NSTP-2) Sub-Orbital and Small Launcher Research Projects Call.
Glasgow Author(s) Enlighten ID:Rengarajan, Dr Sriram and Lo, Dr Kin Hing and Kontis, Professor Konstantinos
Authors: Maddock, C. A., Toso, F., Ricciardi, L., Mogavero, A., Lo, K. H., Rengarajan, S., Kontis, K., Milne, A., Merrifield, J., Evans, D., West, M., and McIntyre, S.
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences

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