Correction guidance method and device for missile boosting phase and hypersonic vehicle

Abstract

The present application relates to a guidance method and device for correcting guidance of a missile boosting phase, and a hypersonic vehicle. The method includes the steps of: performing ballistic trajectory reconfiguration through a missile trajectory planning method based on model predictive static programming according to the terminal constraints of the changed missile boosting phase. Planning; Introduce double trapezoidal sideslip angle design in ballistic trajectory re-planning to control the residual energy dissipation in the boosting phase of the missile; according to the predictive correction guidance scheme based on model predictive static planning, correct the control amount in the boosting phase of the missile, and control The missile completed the expected flight mission. By adopting the above scheme and based on the MPSP theory, an energy management method is designed that uses pitch motion to adjust the terminal height and ballistic inclination, and uses yaw motion to adjust the terminal speed. The goal of wide-area adjustable terminal energy in the boost phase of the missile is also strong robustness to meet the mission requirements of the boost phase.

Description

technical field [0001] The present application relates to the field of guidance technology, in particular to a method and device for correcting guidance of a missile booster phase and a hypersonic vehicle. Background technique [0002] With the development of diverse space missions such as deep space exploration and manned spaceflight, and the development of combat technologies such as long-range precision and rapid strikes, boosters that can complete launch tasks completely autonomously and quickly have become the focus of development in this field. When used as a weapon system, the booster should have the following characteristics: (1) Short launch time: The new missile requires guidance strategies and methods to save the ballistic calculation and element binding before launch, thereby greatly reducing the launch preparation time; (2) Autonomous Strong adaptability: The diversified combat missions of new missiles require the boost guidance algorithm to meet different termi...

AI Technical Summary

Problems solved by technology

New types of combat missions and military requirements put forward higher requirements for booster guidance. However, traditional missile guidance methods cannot meet the above-mentioned guidance requirements, and there is a problem that the terminal energy cannot be controlled in a large range.

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