Aerodynamic/control integrated coupling simulating technology in aircraft maneuvering process

Abstract

The invention discloses an aerodynamic /control integrated coupling simulating technology in the aircraft maneuvering process, and relates to the field of computational fluid mechanics and the field of control systems. The main work implementing process includes the steps of generating a control signal through the compared deviation of the attitude angle of an aircraft and a control target, outputting the control signal to a PID controller module, generating a rudder deviation angle signal after computation, outputting the rudder deviation angle signal to a dynamic mesh module, deflecting a rudder face to a corresponding angle through a dynamic mesh technology, obtaining a dynamic flow field existing after deflection of the rudder face through a Navier-Stockes equation module, generating aerodynamic force and torque signals, outputting aerodynamic force and torque to a rigid body dynamics equation and a kinematical equation, obtaining the flight attitude of the next moment, transmitting the new flight attitude to the PID controller module, and forming a closed-loop numerical simulating circuit. The high-precision simulation of a flight control system is achieved, and the technology can be used for evaluating performance of the flight control system and studying the influences of the aerodynamic force unsteady effect on the control system.

Description

Technical field [0001] Background technique [0002] [0003] Invention content [0004] [0005] [0006] [0007] [0008] Attachment description [0009] figure 1 [0010] figure 2 Detailed ways [0011] [0012] like Figure 1-2 like figure 1 [0013] figure 2 [0014] For ordinary technical personnel in their areas, other different forms of changes or changes can be made on the basis of the above description.There is no need to be poverty to all embodiments here.The obvious change or change extended in this invention is still in the scope of the present invention.

AI Technical Summary

Problems solved by technology

[0002] At present, the engineering simulation method is widely used to simulate and evaluate the control system of the aircraft, but this method does not consider the complete aerodynamic nonlinear and unsteady characteristics, and the application is limited when the aircraft flies at a large angle of attack or maneuvers rapidly, and the simulation results given likely to significantly underestimate control system hysteresis, increasing flight risk

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