Unmanned aerial vehicle UAV control law parameter adjusting method

Abstract

The invention discloses an unmanned aerial vehicle UAV control law parameter adjusting method, and aims at providing a parameter adjusting method which is large in parameter adjusting freedom degree,capable of effectively improving system design efficiency and capable of saving cost. According to the technical scheme, the method comprises the steps that a Matlab is used as a tool, and a general control console, a pneumatic coefficient module, an engine module, an undercarriage, airplane wheels, a brake model, a pitch angle local controller at the balance point of the unmanned aerial vehicle,a six-degree-of-freedom airplane model and a general module library of a sensor model for building the control law of the unmanned aerial vehicle are generated; a field bus control system FCS selectsa set control mode to calculate a control law, an accelerator position instruction and a rudder deviation instruction according to a control instruction given by the general console, ,,sends the flight state parameters of the unmanned aerial vehicle, and directly fits the obtained controller parameters at the characteristic points to obtain a function of the controller parameters about the heightH and the Mach number M and a parameter adjustment control law of a continuous change law of the controller parameters along with the parameter variables in the whole situation.

Description

technical field [0001] The invention relates to a UAV flight control law structure and control parameter design and non-real-time digital simulation, especially a UAV UAV control law parameter adjustment method developed under the Matlab environment. Background technique [0002] Unmanned Aerial Vehicle (UAV) is a highly complex nonlinear dynamic object. For nonlinear systems, there is no mature theoretical system like linear systems. The aerodynamic derivative of the aircraft changes significantly with the change of Mach number, altitude or dynamic pressure. Therefore, the dynamic model of the aircraft will also produce large perturbations as the flight state changes. The difficulty in the design of the flight control system is how to find a control law that can adapt to the change of the dynamic model of the controlled object—the aircraft, so as to ensure that the flight performance of the aircraft can meet the requirements of the flight quality indicators within the entir...

AI Technical Summary

Problems solved by technology

But so far, Simulink is not perfect in the design and simulation of flight control systems, such as various control laws, disturbance sources, etc., and has not established a special module library

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