Longitudinal guidance method of rocket projectile with inclined-angle restraining

Abstract

The invention discloses a longitudinal guidance method of a rocket projectile with inclined-angle restraining. The longitudinal guidance method disclosed by the invention has the advantages that the gravity item and the resistance item are compensated, and the coefficient of the compensation item changes along with the trajectory characteristic, so that the adaptability of the guidance law for different trajectories is better improved; by the addition of a variable-coefficient speed inclined-angle restraining item, the inherent laws of the own speed direction change of the trajectories in a falling process is fully utilized for carrying out proportion guidance mainly at a far distance and carrying out tail-end speed inclined-angle control at a near distance, so that the overload need of the inclined-angle restraining item is effectively reduced, and the influence of the restraining item on the maneuverability is reduced while implementing the tail-end speed inclined-angle control; the guidance law also can select a speed inclined-angle expected value and guidance parameters by self adaption according to the difference of projectile kinds so as to meet different requirements of different warheads for the inclined angle of landing speed.

Description

technical field [0001] The invention relates to a guidance method, in particular to a longitudinal guidance method of a rocket projectile with inclination angle constraints, and belongs to the field of aircraft guidance and control. Background technique [0002] Uncontrolled and simple-controlled rockets are affected by the deviation of the active stage engine and various flight disturbances, and their anti-interference and deviation capabilities are weak, so the range and strike accuracy of rockets are limited accordingly. The research and development of full-range guided rockets has become a new development direction of current rockets. In order to ensure the maneuverability of the full-range guided rocket, the main engine can be used to boost, and the fork-type air rudder installed at the tail of the warhead is used as the actuator, and the stability of the missile body and large-scale maneuvering can be realized through the designed guidance control law. From the perspe...

AI Technical Summary

Problems solved by technology

[0009] In the development process of existing models, guidance methods such as classical proportional guidance, improved proportional guidance, and proportional guidance with landing angle constraints have been applied, but both the classic form and the improved proportional guidance have initial stages. The guidance command is small, the maneuvering speed is slow, and the terminal guidance command has a large jitter, which is not conducive to the realization of the project, and cannot meet the control requirements of the landing angle

Proportional guidance method with inclination angle constraint Correcting velocity inclination at the end of flight will take up a large part of available overload, resulting in greatly reduced strike accuracy

Therefore, the existing guidance forms cannot fully meet the requirements of the landing angle constraint and strike accuracy requirements proposed by the weapon system.

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