Unmanned aerial vehicle UAV control law parameter adjusting method

A UAV, control law technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of not building a module library, imperfect flight control system design and simulation, etc.

Inactive Publication Date: 2019-07-19
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

But so far, Simulink is not perfect in the design and simulation of flight control systems, suc...

Method used

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  • Unmanned aerial vehicle UAV control law parameter adjusting method
  • Unmanned aerial vehicle UAV control law parameter adjusting method
  • Unmanned aerial vehicle UAV control law parameter adjusting method

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Embodiment Construction

[0016] refer to figure 1 . According to the present invention, the UAV UAV control law parameter adjustment method has the following technical characteristics: using Matlab as a tool, based on the flight control system, the general console, aerodynamic coefficient module, engine module, Landing gear, wheel, brake model, pitch angle local controller at the balance point of the UAV, steering gear model, six-degree-of-freedom aircraft model, sensor model, environmental variables and a general module library of the oscilloscope module, and all designed The parameters are loaded into the Matlab simulation environment in the form of file reading and writing, and the optimized embedded real-time simulation code is automatically generated, the model parameters are adjusted online and the simulation data is monitored, and the simulation structure diagram of the corresponding mode packaged is called out; The bus control system FCS calculates the control law, throttle position command a...

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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...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 王宏徐龙谢军贾亮李晓蕊
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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