Disturbance compensation control method for missile pilot

Abstract

The invention provides a disturbance compensation control method for a missile pilot, and relates to the field of guidance control. The method comprises the following steps: modeling by taking a missile as a controlled object, and designing a corresponding traditional attitude pilot; establishing a nonlinear kinetic equation set of the controlled object; considering the comprehensive interferencez3 to establish a state space standard form; obtaining an input and output result of the controlled object through a nonlinear kinematics equation set, and designing an extended state observer; feeding back the comprehensive interference z3 and the control gain b0 to the control output position of the traditional attitude driving instrument through the extended state observer to obtain the active-disturbance-rejection three-loop attitude driving instrument; and performing disturbance compensation control on the missile. The beneficial effects of the method are that: the structure and design parameters of the existing driving instrument are inherited, unmodeled disturbance and uncertain disturbance generated by parameter solidification and small disturbance hypothesis in the missile modeling process are estimated and compensated through the active disturbance rejection extended state observer, and comprehensive disturbance is fed back to the control output position through the extendedstate observer, so that attitude driverscope decoupling design is achieved.

Description

technical field [0001] The invention relates to the technical field of guidance control, in particular to a method for compensating for disturbance of a missile pilot. Background technique [0002] As a guided weapon, the missile's autopilot is designed to quickly follow the guidance instructions, overcome flight disturbances, and finally hit the target. The traditional autopilot design is mostly based on the assumption of local linearization, and the control in the linear region of the projectile has a better effect. However, with the continuous improvement of the performance requirements of modern weapons and the intensity of offensive and defensive confrontation, the flight characteristics of missiles are becoming more and more complex, and the contradiction between missile pilot design and tactical technical indicators is becoming more and more prominent. [0003] It is embodied in: [0004] 1) Nonlinear and strong coupling problems included in the missile model; 2) Un...

AI Technical Summary

Problems solved by technology

However, these methods mostly use the state space method, completely abandoning the traditional design structure, the parameter design is complicated, and it is not convenient for engineering implementation. Some are even in the stage of theoretical research, and the stability needs to be discussed.

Images