Guiding method and device for guided missile boosting section correction and hypersonic aircraft

Abstract

The invention relates to a guided missile boosting section correction guiding method and device and a hypersonic aircraft, and the method comprises the steps that the re-planning of a trajectory is carried out through a guided missile trajectory planning method based on model prediction static planning according to the terminal constraint of a changed guided missile boosting section; a double-trapezoid sideslip angle design is introduced in ballistic trajectory re-planning, and the missile boosting section is controlled to carry out residual energy dissipation; and according to the prediction correction guidance scheme based on model prediction static planning, controlled quantity correction is performed on the missile boosting section, and a missile is controlled to complete an expected flight task. According to the scheme, the energy management method for adjusting the terminal height and the trajectory inclination angle through pitching motion and adjusting the terminal speed through yawing motion is designed on the basis of the MPSP theory, so that the state of the missile boosting section terminal is completely controllable, and the purpose that the energy width range of the solid missile boosting section terminal is adjustable is effectively achieved; meanwhile, the method has high robustness, and the flight mission requirement of the boosting section is met.

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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