Method for automatically generating overload instruction of supersonic-velocity guided missile climbing trajectory

Abstract

The invention discloses a method for automatically generating an overload instruction of a supersonic-velocity guided missile climbing trajectory. A missile computer is adopted to set a high-altitude ideal moving object, then the ideal missile acceleration is calculated according to a proportional navigation law and converted into the overload instruction, a missile overload controller tracks the overload instruction, and finally the automatic instruction generation design of the climbing trajectory is finished. The method has a wide initial launching height and posture requirement range, can accurately control the height of a missile tail section and has good intelligence, and the initial missile launching height and the height of the missile climbing tail section can be set optionally. The overload in the whole process can be subjected to saturation constraint correction. The process from tail section climbing to flat flying is smooth, and the overload is close to 0. All of parameters in the instruction design are not required to be adjusted and corrected in advance, and the method is especially suitable for application in multiple-time climbing or any trajectory planning of a smart missile.

Description

technical field [0001] The invention belongs to the technical field of missile climbing trajectory design, in particular to a method for automatically generating supersonic missile climbing trajectory overload instructions. Background technique [0002] Most of the traditional missile climbing trajectory design adopts the scheme of attitude command plus altitude command to cooperate with control. This scheme requires that the initial height and terminal height of the missile be accurately known or changed within a small range of assumed values. When the airborne missile needs to be launched at any height , this scheme is difficult to meet the requirements. When the airborne missile requires the missile to climb twice or multiple times for tactical penetration, the traditional scheme is also difficult to meet the requirements. The main reason is that the traditional attitude command plus the altitude command match. The design method is designed for an assumed ideal ballistic ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the embodiments of the present invention is to provide a method for automatically generating a supersonic missile climb trajectory overload command, aiming at solving the problem of relying on the settings in the previous airborne supersonic mi

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