Method for limiting normal overload of aircraft

Abstract

The invention relates to a method for limiting normal overload of an aircraft, and belongs to the technical field of a control law for limiting normal overload of an aircraft flight control system based on a low-precision overload sensor. The realization process of the method is as follows: a longitudinal control surface command is solved by command shaping of a longitudinal rod displacement and forward gain and pitch angle rate feedback to control the aircraft control surface deflection so as to control an aircraft; when the normal overload signal fed back by the aircraft approaches the limitvalue, a normal overload limit command is solved by overload limit gain, and is superimposed on the command output after the command is formed; the command output after the command is formed is reduced, the longitudinal control surface command is reduced, the horizontal tail deviation of the aircraft is reduced, and the normal overload is reduced accordingly, so that the normal overload limit isrealized. By adopting the overload limiting method, the overload sensor with relatively low accuracy can be configured, the aircraft cost can be reduced, the pitch oscillation phenomenon caused by thelarge fluctuation of the overload sensor signal during plane flight can be avoided, the normal overload limit of the aircraft can be effectively prevented, and the flight safety can be ensured.

Description

technical field [0001] The invention relates to an aircraft normal overload limiting method, and the technical field of the normal overload limiting control law of an aircraft flight control system based on a low-precision overload sensor. Background technique [0002] The method of limiting the normal overload of the aircraft using the fly-by-wire flight control system is realized by commanding the normal overload and based on the proportional + integral control method, that is, using the PI controller, according to the given normal overload command and the real normal measured in real time The difference between the two overloads is solved to calculate the longitudinal rudder command of the aircraft, so as to realize the non-static control of the normal overload of the aircraft, thereby realizing the limit of the normal overload. However, for some UAV flight platforms, due to the limitation of flight tasks and costs, the overload sensor used in the flight control system ha...

AI Technical Summary

Problems solved by technology

However, for some UAV flight platforms, due to the limitation of flight tasks and costs, the overload sensor used in the flight control system has low accuracy and large signal noise. If such UAVs adopt the above method, it will be difficult to achieve normal overload The precise control of the aircraft may also cause pitching vibration of the aircraft due to the large noise of the normal overload signal, which seriously affects the stability control and flight safety of the aircraft.

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