Aircraft overload tracking method taking overload and angular velocity as outer loop

Abstract

The invention relates to an aircraft overload tracking method taking overload and angular velocity as an outer loop, and belongs to the technical field of aircraft control. The method is characterizedin that an accelerometer is adopted to measure the actual overload of an aircraft; the actual overload is compared with an overload instruction to obtain an overload error; a gyroscope is adopted tomeasure a yaw rate, and nonlinear transformation is carried out to obtain two damping signals of an overload outer loop; and then two paths of integral signals are provided by the integral and nonlinear integral signals of the overload error; and finally, a proportional signal, the two paths of integral signals and the two paths of differential signals are integrated to form an overload error outer loop signal. And then integration and nonlinear integration are carried out on the outer ring signal, and the yaw rate signal is superposed to form an attitude stabilization loop of the overload inner ring instruction driven aircraft, so that a control target of lateral overload instruction tracking is realized. According to the method, overload control can be realized based on reserving of a traditional attitude loop.

Description

technical field [0001] The invention belongs to the field of aircraft control, and in particular relates to a control system design method for aircraft attitude stability and overload stability. Background technique [0002] At present, the design methods of the aircraft control system mainly include two types of methods: overload stable tracking and attitude stable tracking. Stability margin and reliability, so it is widely used in most unmanned and manned aircraft. The traditional overload control generally does not measure the attitude angle of the aircraft, but only measures the overload and angular velocity. However, the present invention proposes a composite control method that combines overload and attitude control. The angular velocity is used to provide a damping signal in the outer loop, and the overload error and error are matched. The multiple integrated signals of the integrated signal are finally obtained to drive the attitude stabilization tracking loop of th...

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Problems solved by technology

[0004] The purpose of the present invention is to provide an aircraft overload tracking method with overload and angular velocity as the outer loop, and then at least to a certain extent overcome the limitations and defects of related technologies that cannot be achieved on the basis of retaining the traditional attitude system. Overload control The problem

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