Stability calculation method of incidence angle controller

Abstract

The invention discloses a stability calculation method of an incidence angle controller. The stability calculation method comprises the following steps of S1, calculating the longitudinal equation of an offset incidence angle state under a certain flight state of a plane; S2, selecting the flight state of the plane in the step S1 and calculating the longitudinal equation of a maximum incidence angle state; S3, calculating the stability reserve of a control augmentation stability system when the incidence angle in the step S1 is alpha L; S4, calculating the stability reserve of the incidence angle controller when the incidence angle in the step S1 is alpha L; S5, calculating the stability reserve of the control augmentation stability system when the incidence angle in the step S2 is alpha max; S6, calculating the stability reserve of the incidence angle controller when the incidence angle in the step S2 is alpha max; S7, taking the minimum value of a magnitude margin as the magnitude margin of the incidence angle controller, and taking the minimum value of a phase margin as the phase margin of the incidence angle controller; and S8, determining the stability reserve of the incidence angle controller within an entire flight envelope. According to the method, a traditional qualitative evaluation method for the stability of the incidence angle controller is converted into the qualitative evaluation method, and the specific numeric values of the magnitude margin and the phase margin of a flight control system are obtained.

Description

technical field [0001] The invention relates to the technical field of flight control, in particular to a stability calculation method for an angle of attack controller. Background technique [0002] The angle of attack controller is the most important protection function among many boundary protection functions of the flight control system. Modern high-performance aircraft often fly at high angles of attack in order to better maneuverability, and even quickly reach the maximum angle of attack flight state from a level flight state with a full pull lever (or full pull control wheel) in order to obtain the best maneuverability , but the aircraft cannot exceed the maximum angle of attack. Once the maximum angle of attack is exceeded, the aircraft is likely to stall or exceed the maximum carrying capacity of the airframe and disintegrate, seriously threatening flight safety. Therefore, modern fly-by-wire flight control systems all have angle-of-attack controllers to realize th...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a method for calculating the stability of an angle of attack controller, to solve or at least alleviate at least one problem in the background art

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