Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Abstract

Purpose

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.

Citation

Li, Y., Cui, N. and Rong, S. (2009), "Trajectory optimization for hypersonic boost‐glide missile considering aeroheating", Aircraft Engineering and Aerospace Technology, Vol. 81 No. 1, pp. 3-13. https://doi.org/10.1108/00022660910926854