Ballistic trajectory tracking method of flight body state sensing self-adaptive scheme

Abstract

The invention discloses a flight body state perception adaptive scheme trajectory tracking method. The guidance law adopts guidance law parameter adaptive change fusing a classical linear trajectory tracking method and based on flight body motion state perception and decision making: generating a longitudinal guidance instruction according to the deviation of the trajectory height and the longitudinal speed of an actual trajectory and a scheme trajectory under the same transverse coordinate; generating a transverse guidance instruction according to trajectory lateral deviation and lateral speed of the actual trajectory and the scheme trajectory under the same transverse coordinate; the longitudinal and transverse guidance instructions are functions of trajectory deviation and guidance law parameters, and the guidance law parameters are adjusted in real time along with the deviation change of the real-time position of the flight body and the position parameters corresponding to the scheme trajectory, and the deviation change of the real-time flight speed and the speed parameters corresponding to the scheme trajectory; therefore, stable and high-precision convergence is realized.

Description

technical field [0001] The invention belongs to the field of aircraft guidance and control, in particular to a ballistic tracking method for a flying body state perception adaptive scheme for a flying body without a control loop. Background technique [0002] With the continuous improvement of the range and accuracy requirements of projectiles and arrows, the significance and role of the guidance and control system on such flying bodies are becoming larger and larger, which can stabilize the flying body and guide the flying body to fly according to the set trajectory. hit the target. In general, the guidance control system of the flying body consists of a guidance loop and a control loop. The control loop is divided into overload tracking control and attitude tracking control according to the difference of the tracking command signal. The controller measures the missile body according to the guidance command and the inertial navigation device. Attitude angle, attitude angul...

AI Technical Summary

Problems solved by technology

In general, the guidance loop adopts the classical PID control, robust control, sliding mode control and other theoretical design schemes for ballistic tracking guidance laws. Since there is no control loop to provide stable attitude of the missile body, it is easy for the flying body to produce Swing, even under the action of disturbance, the swing is intensified, which increases the flight resistance, affects the range, reduces the tracking accuracy of the projected trajectory, and cannot meet the relevant flight index requirements

For the long-range flying body, the guidance circuit alone guides the flying body to fly along the planned ballistic trajectory. In the relevant literature at home and abroad, there is no relevant design of the guidance law that considers the flight stability and tracking effect of the flying body for adaptive adjustment. Improve the ballistic tracking effect of the program. With the increasing demand for the development of this type of flying object, this research becomes more urgent

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