Aircraft boundary limit control law and design method thereof

Abstract

The invention provides an aircraft boundary limit control law design method, which belongs to the technical field of flight control, and comprises the following steps: calculating boundary limit values according to flight speed, the boundary limit values comprising an attack angle limit value and a normal overload limit value, and determining a critical speed value; limiting an attack angle when the speed value is lower than the critical speed value, and limiting normal overload when the speed value is higher than the critical speed value; performing dynamic maximum value obtaining and logic comparison on attack angle and normal overload feedback signals; and calculating the difference between a signal output by a boundary limit control law of the steering column and a boundary limit value, and through static-error-free integral control law design, controlling the aircraft control surface to deflect so that the aircraft attack angle and overload do not exceed boundary limits. Accordingto the invention, worry-free control in the full flight envelope of the aircraft can be realized, and flight safety and maximum maneuverability of the aircraft are ensured.

Description

technical field [0001] The application belongs to the technical field of aircraft design, and in particular relates to a method for designing an aircraft boundary-limited control law. Background technique [0002] Boundary restrictions are essential during aircraft maneuvering, especially in maneuvering flights. Good boundary restrictions can ensure the safety of the aircraft, reduce the workload of the pilots, and realize "worry-free" control of the aircraft. [0003] In the prior art, methods such as hardware limitation and second-level angle-of-attack software limitation are often used for boundary limitation. Hardware limitation is realized by adding some physical components (such as limiting devices), thus increasing the weight of the aircraft and occupying the flight area. At the same time, due to the tolerance of machining, it is difficult to achieve precise limitation. When the deceleration maneuver is implemented, the limiter will delay the action of the control sti...

AI Technical Summary

Problems solved by technology

[0004] The purpose of this application is to provide a method for designing an aircraft boundary-limited control law to solve or alleviate at least one of the problems in the background art

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