Method for preventing control plane integral saturation in aircraft ground servo elasticity test

A servo elastic and anti-integration technology, applied in electrical testing/monitoring, etc., can solve problems such as failure to test normally, achieve the effects of prolonging integration saturation time, strong adaptability, and improving reliability

Active Publication Date: 2014-01-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the invention is: under the premise of ensuring the minimum impact on the dynamic characteristics of the flight control law in the elastic vibration frequency range of the aircraft, solve the problem of rapid integral saturation of the rudder surface due to the presence of an integral link in the feedback loop in the aircraft ground servo elasticity test, which cannot Technical issues with normal testing

Method used

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  • Method for preventing control plane integral saturation in aircraft ground servo elasticity test
  • Method for preventing control plane integral saturation in aircraft ground servo elasticity test
  • Method for preventing control plane integral saturation in aircraft ground servo elasticity test

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Experimental program
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Embodiment

[0032] 1. A real-time simulation system is connected between the flight control sensor and the flight control computer. The real-time simulation system includes the main control computer and the simulation computer

[0033] 2. Complete the high-pass filter parameter setting in the main control computer, as follows

[0034] 1) Construct the high-pass filter transfer function as follows:

[0035] H F ( s ) = s 2 s 2 + 2 ξ ω n · s + ω n 2

[0036] 2) Select ξ=0.707 to solve the following constrained optimization problem

[0037]

[0038] Where ...

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Abstract

The invention belongs to the field of aircraft strength tests, and relates to the category of aircraft aeroelasticity tests, in particular to a method for preventing control plane integral saturation in an aircraft ground servo elasticity test. A real-time emulation system is connected between a flight control sensor and a flight control computer in series. The real-time emulation system comprises a main control computer and an emulation computer. After parameters of a high-pass filter are set and coded in the main control computer, the coded parameters are transmitted to the emulation computer. The parameters of the high-pass filter are designed with the dynamic characters of the control law within the range of the aircraft elastic vibration frequency as the restraint, the time of control plane integral saturation is prolonged, fast control plane integral saturation is effectively restrained, and meanwhile the effect on the test result is reduced to the maximum extent. The filter is placed in an external emulation machine, hardware and software of an onboard control system do not need to be adjusted, the parameters of the filter can be adjusted according to the actual situation in the test, and the method is high in adaptability and practicability.

Description

technical field [0001] The invention belongs to the field of aircraft strength tests, relates to the category of aircraft aeroelasticity tests, and in particular to an anti-integral saturation method for rudder surfaces of aircraft ground servo elasticity tests. Background technique [0002] Most modern digital fly-by-wire flight control systems have the functions of attitude maintenance and automatic trimming, and the realization of these control functions usually requires an integral link in the feedback loop. Due to the integral link in the feedback loop, in the ground servo elasticity test, as long as there is zero drift or static error in the feedback signal, the rudder deviation command will be saturated as time goes by, especially when the integral constant in the feedback loop is large, the rudder surface Will quickly saturate in a short period of time, making the test impossible. [0003] At present, for the rudder surface integral saturation problem in the ground ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
Inventor 蒲利东党云卿张红波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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