Servo elasticity test and analysis method suitable for multichannel 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control, attitude control, etc., can solve the problem that the aerodynamic servo elasticity problem of aircraft is no longer applicable, and achieve optimal flight control The effect of the parameter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: 2015-08-19
CHINA ACAD OF LAUNCH VEHICLE TECH
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AI Technical Summary

Benefits of technology

This patented technology allows for accurate determination of the optimal flight controls by analyzing data from different sources such as sensors or controllers connected through communication networks. It also helps improve safety during takeoffs and landings on airplanes.

Problems solved by technology

This patents describes how airplanes can experience issues caused by high stress on their wings due to factors like weight distribution or environmental conditions such as temperature changes during flights. These challenging situations result in increased vibrations leading to poor flying behavior and potential crashes. To address these concerns, advanced avionics technologies (A/C) for controllers called Flight Management Systems (FMS), which help prevent excessive strain on structures while ensuring stable operation over long periods of time under varying atmospheric pressure environments, require accurate testing methods to verify its ability to maintain safe flight operations even after being exposed to extreme temperatures.

Method used

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  • Servo elasticity test and analysis method suitable for multichannel coupling aircraft
  • Servo elasticity test and analysis method suitable for multichannel coupling aircraft
  • Servo elasticity test and analysis method suitable for multichannel coupling aircraft

Examples

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Effect test

Embodiment 1

[0036] A servo elastic test and analysis method applicable to multi-channel coupling 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 state of the aircraft as the 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 (pitch off, other channels off) to the flight control computer on the aircraft, and the table 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 stepping sinusoidal signal: the frequency range is 1 to 25 Hz, and the frequency step is 0.1 Hz. The sinusoidal signal at each frequency lasts for 10 signal periods and pauses for 1 second. figure 2 As shown, the flight con...

Embodiment 2

[0049] A servo elastic test and analysis method applicable to multi-channel coupling 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 state of the aircraft as the 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 (pitch off, other channels off) to the flight control computer on the aircraft, and the table 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 stepping sinusoidal signal: the frequency range is 1 to 25 Hz, and the frequency step is 0.1 Hz. The sinusoidal signal at each frequency lasts for 10 signal periods and pauses for 1 second. figure 1 As shown, the flight contr...

Embodiment 3

[0063] A servo elastic test and analysis method applicable to multi-channel coupling aircraft, the steps of the method are:

[0064] (c1) Determine the test state of the aircraft, including the 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 amplification factor K1 to the flight control computer on the aircraft through the measurement and control computer, K1=1 is the nominal gain, and when the test speed state is 30m / s;

[0067] (c4) Artificially disturbed aircraft, simulated Figure 7 For the excitation signal shown, the amplitude A should be able to overcome the nonlinear excitation of the control system to respond to the structure without damaging the structure and the flight control system. In this example, it is 10kg, and the data is collected at the same ...

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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

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Claims

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Application Information

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Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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