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Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

Published online by Cambridge University Press:  27 March 2017

S.T.I. Rizvi ,
H. Linshu ,
X. Dajun  and
S.I.A. Shah
S.T.I. Rizvi*
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, P.R. China
H. Linshu
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, P.R. China
X. Dajun
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, P.R. China
S.I.A. Shah
Affiliation:
National University of Sciences and Technology, Islamabad, Pakistan
*
rizvi.aeng@gmail.com
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Abstract

In this work, trajectory optimisation has been performed for a wing-body rocket assisted vehicle to compute the bestset of performance parameters including burn-out angle, angle-of-attack, bank-angle and throttle command that would result in optimal down-range and cross-range performance of the re-entry vehicle. An hp-adaptive Pseudospectral method has been used for the optimisation by combining the launch and rocket rocket-assisted re-entry stages. The purpose of the research is to compute optimal burn-out condition, angle-of-attack, bank-angle and optimal thrust segments that would maximise the down-range and cross-range performance of the hypersonic boost glide vehicle, under constrained heat rate environments. The variation of down-range/cross-range performance of rocket rocket-assisted hypersonic boost glide vehicle with bounds on diminishing heat rate has also been computed.

Keywords

trajectory optimisationhypersonic boost-glidewaveriderwing-body configurationpseudospectral methodoptimal control
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1238 , April 2017 , pp. 469 - 487
Copyright
Copyright © Royal Aeronautical Society 2017 

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