TY  - JOUR
AB  - 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.
VL  - 87
IS  - 1
SN  - 0002-2667
DO  - 10.1108/AEAT-04-2013-0079
UR  - https://doi.org/10.1108/AEAT-04-2013-0079
AU  - ul Islam Rizvi S. Tauqeer
AU  - Linshu He
AU  - Dajun Xu
PY  - 2015
Y1  - 2015/01/01
TI  - Optimal trajectory analysis of hypersonic boost-glide waverider with heat load constraint
T2  - Aircraft Engineering and Aerospace Technology: An International Journal
PB  - Emerald Group Publishing Limited
SP  - 67
EP  - 78
Y2  - 2024/09/19
ER  -