Response Surface Modeling-Based Analysis on Launch Vehicle Capability

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This paper proposes a framework to analyze the capacity of a launch vehicle systematically. Important mission requirements and flight parameters that influence the payload capacity of a given launch vehicle configuration are identified. The response surface models (RSM; the “analyzer”) for the launch capacity, coasting/burning arcs, and the velocity increment elements are developed. A series of trajectory optimization results, which are obtained with the “optimizer”, are used to determine the coefficients of the models. The case study to analyze the capacity of a low Earth orbit (LEO) launch vehicle configuration is conducted to demonstrate the validity of the proposed framework.
Publisher
ELSEVIER SCI LTD
Issue Date
2018-12
Language
English
Article Type
Article
Citation

ADVANCES IN SPACE RESEARCH, v.62, no.12, pp.3281 - 3297

ISSN
0273-1177
DOI
10.1016/j.asr.2018.03.007
URI
http://hdl.handle.net/10203/248265
Appears in Collection
AE-Journal Papers(저널논문)
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