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A servo elastic test and analysis method suitable for multi-channel coupling aircraft

A technology of servo elasticity and analysis method, applied in sequence/logic controller program control, three-dimensional position/course control, attitude control, etc., can solve the problem that the aerodynamic servo elasticity problem of aircraft is no longer applicable, and achieve optimal flight control The effect of the parameter

Active Publication Date: 2017-12-22
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For aircraft with conventional layout, relatively mature analysis and test techniques are available without considering channel coupling, but the traditional method is no longer applicable to the problem of aircraft aeroservoelasticity under the condition of multi-channel coupling

Method used

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  • A servo elastic test and analysis method suitable for multi-channel coupling aircraft
  • A servo elastic test and analysis method suitable for multi-channel coupling aircraft
  • A servo elastic test and analysis method suitable for multi-channel coupling aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] A servo elasticity test and analysis method suitable for a multi-channel coupled aircraft, the steps of the method are:

[0037] (a1) The ground detection equipment supplies power to the aircraft, so that the aircraft is in an open-loop state;

[0038] (a2) Determine the test status of the aircraft as pitch channel "01";

[0039] (a3) According to the test state of the pitch channel determined in step (a2), the measurement and control computer sends the test parameter 01 (the pitch is disconnected, other channels are disconnected) to the flight control computer on the aircraft, and the surface speed is 110m / s. After the computer confirms, start the test;

[0040] (a4) The measurement and control computer sends an excitation signal to the aircraft. The excitation signal adopts a stepped sinusoidal signal: the frequency range is 1 to 25 Hz, and the frequency step size is 0.1 Hz. The sinusoidal signal at each frequency lasts for 10 signal cycles and pauses for 1 s. figur...

Embodiment 2

[0049] A servo elasticity test and analysis method suitable for a multi-channel coupled aircraft, the steps of the method are:

[0050] (b1) The ground detection equipment supplies power to the aircraft so that the aircraft is in an open-loop state;

[0051] (b2) Determine the test status of the aircraft as pitch channel "01";

[0052] (b3) According to the test state of the pitch channel determined in step (b2), the measurement and control computer sends the test parameter 01 (the pitch is disconnected, other channels are disconnected) to the flight control computer on the aircraft, and the surface speed is 30m / s. After the computer confirms, start the test;

[0053] (b4) The measurement and control computer sends an excitation signal to the aircraft. The excitation signal adopts a stepped sinusoidal signal: the frequency range is 1 to 25 Hz, and the frequency step size is 0.1 Hz. The sinusoidal signal at each frequency lasts for 10 signal cycles and pauses for 1 s. figure ...

Embodiment 3

[0063] A servo elasticity test and analysis method suitable for a multi-channel coupled aircraft, the steps of the method are:

[0064] (c1) Determine the test state of the aircraft, which includes a pitch channel with a small stability margin;

[0065] (c2) The ground detection equipment supplies power to the aircraft, so that the channel corresponding to the test state of the aircraft is in a closed-loop state;

[0066] (c3) Configure the control channel gain magnification K1 to the flight control computer on the aircraft through the measurement and control computer, K1=1 is the nominal gain, and the test surface speed state is 30m / s;

[0067] (c4) Artificial perturbation of the aircraft, simulation Figure 7 The excitation signal shown, the amplitude A should be able to overcome the nonlinear excitation of the control system and cause the response of the structure without damaging the structure and the flight control system. In this example, it is 10kg, and data is collect...

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Abstract

The invention relates to a servo elasticity test and analysis method suitable for a multichannel coupling aircraft, belonging to the aircraft aeroelasticity and large-scale ground test technical field. The servo elasticity test and analysis method solves the inertia coupling effect test verification technical problems of the structural elasticity and control surfaces of a first aerospace vehicle with multi-control surface and multi-control channel coupling, can obtain transmission function curves of each link in an aircraft system, determine a servo elasticity stability margin and check and correct theoretical models and analysis results, and meanwhile optimizes flight control parameters and ensure flight safety and reliability.

Description

technical field [0001] The invention relates to a servo elasticity test and analysis method suitable for a multi-channel coupled aircraft, belonging to the technical field of aeroelasticity and large-scale ground tests of aircraft. Background technique [0002] With the development of aerospace technology, the authority and control bandwidth of the control system in the entire aircraft are getting higher and higher. At the same time, the lightweight design requirements lead to a more obvious structural elastic effect, and the coupling between the structure, aerodynamics and the flight control system is becoming more and more important. Seriously, it will cause the problem of aero-servo-elasticity of the aircraft, ranging from reduced flight performance to structural instability and damage in severe cases, endangering flight safety. The margin is fully studied and necessary measures are taken to ensure flight safety. [0003] Modern aircraft generally use multiple control su...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/06G05D1/08G05D1/10
CPCG05B19/06
Inventor 何咏梅陈洪波楚龙飞张华山张家雄张辉杨勇
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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