Method for simulating strength of reversible control loading system of flight simulator

Abstract

The invention discloses a method for simulating strength of a reversible control loading system of a flight simulator. A stick force simulation model identical with a reversible control system of a real plane is built, and is provided with a servo trim tab. Due to the fact that the level force simulation model and the real plane are the same in actual composition, force generated by the servo trim tab can be independently debugged, debugging is simplified compared with a hinge moment coefficient adjusting method in the prior art, the time for debugging and the production cycle of a product are shortened, and the time for debugging is shortened by 42.5% compared with the hinge moment coefficient adjusting method. Therefore, product competitiveness is improved; the level force simulation model is suitable for simulating force of a joystick, with a servo trim tab, of the reversible control system of the plane, and also suitable for stimulating force of a joystick, without the servo trim tab, of the reversible control system of the plane; coefficients of the level force simulation model can be modified along with the actual control of the simulated plane, and the level force simulation model has universality. According to the method for simulating strength of the reversible control loading system of the flight simulator, influence caused by aerodynamic force on hinge moment of a control surface is effectively eliminated, and fidelity of simulation of force of the joystick of the reversible control system is improved.

Description

technical field [0001] The invention relates to the field of mathematical modeling and computer digital simulation of the real control mechanism of the aircraft, which is used for the flight simulator to reproduce the stick force and the aerodynamic force caused by the aerodynamic force and the The dynamic and static characteristics of the control system under different control modes (such as: automatic, manual, emergency control, etc.). Background technique [0002] On aircraft with a reversible control system, the pilot applies a force to the steering wheel to deflect the rudder surface, and there is a rigid tie rod system between the steering wheel and the rudder surface. The aircraft control system includes rudder, elevator, aileron, rudder trim, elevator trim, aileron trim, elevator follow-up compensation, rudder follow-up compensation, aileron follow-up compensation, flap control system, etc. [0003] The aircraft control system is one of the important and main on-boa...

AI Technical Summary

Problems solved by technology

However, there is no modeling of the follower compensator, and its function is realized by adjusting the hinge moment coefficient method

However, this debugging method is difficult and easily causes high-frequency oscillation of the control system, and even instability

In fact, when the geometry and aerodynamic forces of the aircraft are kept similar, that is, the angle of attack, the deflection angle of the rudder and the size of the rudder are kept constant, as the airspeed increases, the hinge moment will increase sharply, and the consequent steering wheel force will Increased violently, the maneuvering of the aircraft becomes difficult

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