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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

Inactive Publication Date: 2016-01-06
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the large number of state points in the flight envelope, parameter adjustment is a very cumbersome and complicated task
At present, there is no systematic and complete method to adjust and integrate the automatic flight control law parameters within the entire flight envelope

Method used

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  • Automatic flight control system parameter adjusting and integration method
  • Automatic flight control system parameter adjusting and integration method
  • Automatic flight control system parameter adjusting and integration method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[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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Abstract

The invention discloses an automatic flight control system parameter adjusting and integration method. The method comprises the following steps of determining a national military standard requirement corresponding to a modality and taking performance indexes which need to be reached as target functions when a control law parameter is optimized; establishing a relation of the control law parameter and the target functions so as to find a parameter value with optimal control performance; endowing a weighting coefficient to each target function and carrying out comprehensive summation so as to acquire a total-utility target function; setting the acquired total-utility target function as a fitness function in a genetic algorithm, setting the control law parameter which is searched as an optimization individual of the algorithm and using the genetic algorithm to calculate a control law parameter value when the total-utility target function is optimal under each modality; establishing a function of a parameter value and dynamic pressure so as to obtain a control law parameter value in a whole envelope scope. By using the method, the control law parameter can be rapidly and automatically searched; a requirement of the national military standard to specific control performance of each modality is satisfied and the control law parameters of all the state points in the envelope can be rapidly determined.

Description

technical field [0001] The invention relates to parameter adjustment and integration technology in the aviation field, in particular to an automatic flight control system parameter adjustment and integration method. Background technique [0002] The flight state of the aircraft is nonlinear and changes in real time. Under each specific flight state within the flight envelope, the aircraft can be approximated as a linear model. Finding the optimal control law parameters under each specific flight state can make the aircraft in the best control status. However, due to the large number of status points in the flight envelope, parameter adjustment is a very cumbersome and complicated task. At present, there is no systematic and complete method to adjust and integrate the automatic flight control law parameters within the entire flight envelope. Contents of the invention [0003] In order to solve the above problems, the present invention provides a method for automatic fligh...

Claims

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Application Information

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IPC IPC(8): G05B17/02
Inventor 董新民刘棕成李洪波薛建平李瑾
Owner AIR FORCE UNIV PLA
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