Balanced control distribution method of airplane with multiple control surfaces

Abstract

The invention provides a balanced control distribution method of an airplane with multiple control surfaces, which mainly comprises the following steps of: transferring a control distribution problem of the multiple control surfaces into an equivalent control problem of a virtual control surface and a real control surface, determining a basic method for carrying out normalization on the real control surface and carrying out balanced distribution on the control efficiency, classifying the real control surface, carrying out the normalization and sequencing according to absolute values of the normalized control efficiency, determining the leading control efficiency of the virtual control surface, grading the normalized control surfaces, calculating a distribution coefficient and the like. Inthe invention, by utilizing the balanced control distribution method, the control of the multiple control surfaces is equalized to the control of the special control efficiency and the virtual control surface which is limited by a deflection range, so that the design of the control efficiency is simplified, the problem that the angular rate of the control surface is transfinite, and the matrix calculation of the weighted balanced distribution is simple; the deflection range, the control efficiency, the control grade and the authority coefficient of the control surface are comprehensively considered, and the effective control surface is completely utilized, so that the saturation, which is caused by that some control surfaces bear overmuch control efficiency, is effectively avoided.

Description

technical field [0001] The invention belongs to the field of flight control, and in particular relates to a balanced control distribution method for aircraft with multiple control surfaces. Background technique [0002] Traditional aircraft often use ailerons to generate roll motion, rudders to generate yaw motion, and elevators to generate pitch motion. In order to improve maneuverability and reliability, today's aircraft often adopt a multi-control surface layout. For example, the American advanced fighter YF-22 has 12 independent control surfaces (horizontal tail, aileron, rudder, flaperon, leading edge flap, and two control surfaces each for pitch thrust vector). Since the control surfaces that produce roll, yaw and pitch moments are not unique, the multi-control surface layout improves the flexibility of aircraft manipulation and the control margin of the aircraft, thereby enhancing the control performance and safety performance of the flight. [0003] The redundancy ...

AI Technical Summary

Problems solved by technology

These methods are strong in mathematics, difficult to guarantee real-time performance, and the physical concepts are not clear enough, so there are certain limitations in practical engineering applications.

[0004] It can be seen that many current control allocation methods are to solve the deflection angles of all control surfaces from the expected torque according to the control efficiency matrix. The control command of the instrument needs to be converted into the desired torque command, which increases the complexity of the control law design and limits the engineering application

Images