Explicit guidance law for rocket with terminal speed, trajectory inclination angle and overload constraint

Abstract

The present invention provides an explicit guidance law for a rocket with a terminal speed, a trajectory inclination angle and overload constraint. The explicit guidance law for a rocket is formed by integration of an optimal trajectory-shaping guidance law and a terminal speed control scheme. The optimal trajectory-shaping guidance law can control an aircraft to hit a target from a predetermined direction, the terminal speed control scheme controls the transverse maneuverable accelerated speed of the aircraft bending so as to control the prolonging of flight distance to regulate the size of the terminal speed, and the size of the transverse maneuverable accelerated speed is determined through an iteration correction algorithm. The analysis guidance law can satisfy the terminal trajectory inclination angle and the terminal speed constraint, and allow an aircraft to approach to the maneuverable accelerated speed of the target to gradually decrease to 0; further, the present invention provides a method for determination of coefficients of guidance law for a rocket, namely the coefficients of guidance law for a rocket are determined through proper selection of features of a linear approximation system; and moreover, a coefficient stability domain of the guidance law for the rocket is obtained so as to strictly prove that only if the coefficients of guidance law for a rocket are in the stability domain the guiding system is stable and the aircraft hits a target at a small angle of attack.

Description

technical field [0001] The invention relates to an explicit guidance law with terminal velocity, ballistic inclination and overload constraints, and belongs to the fields of aerospace technology, weapon technology and guidance control. Background technique [0002] For the terminal flight of a hypersonic gliding vehicle, it is generally hoped to guide the vehicle to hit the ground target from an approximately vertical direction, so that the seeker has a better field of view; at the same time, it is necessary to control the terminal speed of the vehicle, because in general Excessive terminal velocity is not conducive to ensuring heat flux density and incoming flow pressure constraints, and too small terminal velocity is not conducive to the need for penetration. If the aircraft is loaded with a ground-penetrating warhead, it is required to hit the target with a smaller angle of attack; otherwise, when it hits the target with a larger angle of attack, the projectile body will ...

AI Technical Summary

Problems solved by technology

At the same time, the traditional explicit guidance law cannot satisfy the constraints on terminal velocity, ballistic inclination and overload at the same time, and a large overload will greatly increase the amount of misses when the projectile meets the target.

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