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Optimal trajectory analysis of hypersonic boost-glide waverider with heat load constraint

S. Tauqeer ul Islam Rizvi (School of Astronautics, Beihang University, Beijing, China)
He Linshu (School of Astronautics, Beihang University, Beijing, China)
Xu Dajun (School of Astronautics, Beihang University, Beijing, China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 5 January 2015

Abstract

Purpose

The purpose of the paper is to study the variation of optimal burnout angle at the end of the ascent phase and the optimal control deflection during the glide phase, that would maximize the downrange performance of a hypersonic boost-glide waverider, with variation in heat rate and integrated heat load limit.

Design/methodology/approach

The approach used is to model the boost phase so as to optimize the burnout conditions. The nonlinear, multiphase, constraint optimal control problem is solved using an hp-adaptive pseudospectral method.

Findings

The constraint heat load results for the waverider configuration reveal that the integrated heat load can be reduced by more than half with only 10 per cent penalty in the overall downrange of the hypersonic boost-glide vehicle, within a burnout speed range of 3.7 to 4.3 km/s. The angle-of-attack trim control requirements increase with stringent heat rate and integrated heat load bounds. The normal acceleration remains within limits.

Practical implications

The trajectory results imply lower thermal protection system weight because of reduced heat load trajectory profile and therefore lower thermal protection system cost.

Originality/value

The research provides further study on the trajectory design to the hypersonic boost-glide vehicles for medium range application.

Keywords

Acknowledgements

The authors would like to thank the Chinese Scholarship Council for funding the research.

Citation

ul Islam Rizvi, S.T., Linshu, H. and Dajun, X. (2015), "Optimal trajectory analysis of hypersonic boost-glide waverider with heat load constraint", Aircraft Engineering and Aerospace Technology, Vol. 87 No. 1, pp. 67-78. https://doi.org/10.1108/AEAT-04-2013-0079

Publisher

:

Emerald Group Publishing Limited

Copyright © 2015, Emerald Group Publishing Limited