A Multi-constrained Adaptive Predictor–Corrector Guidance Method for Ascent Phase of Hypersonic Vehicle

Abstract

In this paper, considering the various terminal states constraints, and coupling of different states in the ascent phase of the hypersonic aircraft, a multi-constrained guidance method based on predictor–corrector policy is proposed. Firstly, the dynamic equations of ascent phase are given. And then, the dynamic amplification factors for the various flight states are calculated. Analyzing the dynamic equations of ascent phase, it can be found that only the attack angle is used to control various states and the guidance of ascent phase is an under-driven problem. The path angles are small values at the terminal flight phase, and it has little couple influence on the altitude. In order to solve the under-driven problem, the whole ascent phase has two parts. At the initial phase, eliminating the terminal height error is chosen as the guidance object. At the terminal phase, eliminating the path angle error at the end point is chosen as the guidance object. What’s more, the influence of choosing different segmentation altitude on the terminal states errors is analyzed. Moreover, the Monte Carlo simulation demonstrates the effectiveness of the proposed multi-constrained adaptive predictor–corrector guidance method.