Automatic flight control system parameter adjusting and integration method
A technology of automatic flight control and system parameters, applied in the aviation field, can solve the problems of cumbersome and complex parameter adjustment, and achieve the effect of fast automatic search
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[0030] Taking the control law parameter adjustment and integration of the pitch control mode as an example to illustrate the specific implementation.
[0031] Run by Matlab program language command "sim" image 3 As shown in the simulation model, when the control law parameter K P 、K I 、K q When the constant value is taken, the pitch angle response curve under the control law parameters can be obtained. The corresponding performance index can be calculated according to the response curve, and the corresponding relationship between the control law parameters and the performance index is found. Set the performance index as the objective optimization function, and establish the following total utility objective optimization function:
[0032] f ( K P , K I , K D ) = ...
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