Automatic flight control simulation system for general flight simulator

Abstract

The invention discloses an automatic flight control simulation system for a general flight simulator. According to the technical scheme, the system comprises a flight guide module, an automatic pilotmodule, an auto-throttle module, an automatic landing module, an automatic navigation module, an automatic trim module and a module control logic/data configuration file module. The module control logic/data configuration file module comprises a control logic module and a data configuration module. The control logic module is used for judging whether each module meets an access condition or not before the access of the module, judging whether the above module is in contradiction with a currently operated module or not during the access of the module, and judging whether other modules need to be accessed or not before the exit of the currently operated module. The data configuration module is used for describing the control rates of the flight guide module, the automatic pilot module, the auto-throttle module, the automatic landing module, the automatic navigation module and the automatic trim module. In this way, the general design of the automatic flight control simulation system canbe realized.

Description

technical field [0001] The invention belongs to the field of automatic flight control, more specifically, it relates to a general flight simulator automatic flight control simulation system. Background technique [0002] A typical flight control system consists of three feedback loops: a rudder loop, a stabilization loop, and a guidance loop. [0003] Among them, the rudder circuit is to improve the performance of the steering gear to meet the requirements of the flight control system. Usually, the output of the steering gear is fed back to the input end to form a negative feedback loop (also called a servo loop). server system). If, on the basis of the rudder circuit, the measurement components for measuring the attitude information of the aircraft are added, the two constitute the autopilot. [0004] Controlling the controlled object based on the autopilot is a stabilization loop, which can stabilize and control the flight attitude of the aircraft. [0005] A typical fl...

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Problems solved by technology

[0008] The first method is based on the realization of the airborne flight control computer. This method refers to the manual parameter adjustment of the airborne computer directly. However, the core control law algorithm of the airborne computer is strictly controlled by the manufacturer. It cannot be obtained, which makes the parameter adjustment process can only be continuously modified outside the control law of the onboard computer, that is, the control parameters are continuously transmitted to the onboard computer through the handshake protocol, and externally adjusted to meet the control requirements. quality output, which makes the whole tuning process very passive, and the onboard computer is aimed at a real aircraft of a single sortie, while the control object of the automatic flight control simulation system of the flight simulator is an aircraft based on flight dynamics The established virtual dynamic model, no matter what modeling method is used for this model, cannot completely match the real aircraft. Moreover, this virtual controlled object does not have an inertial link. Therefore, the machine used to control the real

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