Guided missile pitching channel simple sliding-mode control method based on overload and angular velocity measurement

Abstract

The invention discloses a guided missile pitching channel simple sliding-mode control method based on overload and angular velocity measurement. The method comprises the steps of processing overload signal and angular velocity signal measurement and amplitude limiting; establishing an integral sliding-mode face and selecting simplified sliding-mode control law parameters; performing continuous simulation verification on a simplified missile body model; performing robustness checkout and parameter adjustment under aerodynamic parameter perturbation. The guided missile pitching channel simple sliding-mode control method is a simple sliding-mode control method based on a gyroscope measurement attitude angle and rate gyroscope measurement guided missile attitude angular velocity technology, enables control parameter adjustment and selection to be simple and concise compared with similar control methods. The guided missile pitching channel simple sliding-mode control method is simple in control law composition and good in control low robustness, does not rely on accurate model information and has not high requirements for the overload measurement accuracy, angular velocity measurement accuracy and an on-missile computer sampling period.

Description

technical field [0001] The invention belongs to the technical field of simple sliding mode control of a missile pitch channel, and in particular relates to a simple sliding mode control method of a missile pitch channel based on overload and angular velocity measurement. Background technique [0002] The stability loop is the core inner loop in the missile control system. At present, there are mainly two types of methods in the internal loop of missiles: attitude control and overload control. Among them, the attitude control mainly measures the attitude angle and the attitude angular velocity of the missile, and then composes the control law based on the measured values ​​to carry out stable control and tracking of the attitude angle of the missile. The overload control scheme is to measure the missile's overload and attitude angular velocity or attitude angular acceleration, and then use the measured values ​​to form a control law to stably control and track the missile's ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the embodiments of the present invention is to provide a simple sliding mode control method for the missile pitch channel based on overload and angular velocity measurement, which aims to solve the current control scheme based on overload and angular acceleration measurement. Accurate measurement is more difficult, and the problem of engineering implementation without using the control scheme

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