Trajectory optimization for hypersonic boost-glide missile considering aeroheating

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Trajectory optimization for hypersonic boost-glide missile considering aeroheating

Li, Yu / Cui, Naigang / Rong, Siyuan

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The purpose of this paper is to optimize the downrange for hypersonic boost-glide (HBG) missile under near-real condition, and to validate the suitability of proposed wall cooling materials.

Design/methodology/approach –

The trajectory optimization problem is characterized by a boost phase followed by a glide phase. A multi-phase trajectory optimization tool is adopted to optimize the downrange. The associated optimal control problem has been solved by selecting a direct shooting method. The dynamics has been transcribed to a set of nonlinear constraints and the arising nonlinear programming problem has been solved through a sequential quadratic programming solver. An aerothermodynamics analysis method is introduced to calculate the aerodynamic heating at nose, leading edge, and ventral centerline regions.

Findings –

HBG missile is suitable for long-range attack, and the optimal trajectory solved is a novel boost-glide-skip trajectory, i.e. boost firstly, glide secondly, and skip at last. The proposed wall materials are valid.

Originality/value –

This paper provides further study on the methods of trajectory design and aerothermodynamics analysis for HBG missile.