Automatic amplitude modulation frequency scanning method for airplane servo elasticity frequency response test

A technology of servo elasticity and aircraft, applied in the direction of adaptive control, electrical test/monitoring, control/adjustment system, etc., can solve the problems of large error of test data, inability to guarantee the safety of rudder surface structure and signal-to-noise ratio of loop response signal at the same time

Active Publication Date: 2014-02-05
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0005] The purpose of the present invention is to solve the technical problem that the safety of the rudder surface structure and the signal-to-noise ratio of the loop response signal cannot be...

Method used

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  • Automatic amplitude modulation frequency scanning method for airplane servo elasticity frequency response test
  • Automatic amplitude modulation frequency scanning method for airplane servo elasticity frequency response test
  • Automatic amplitude modulation frequency scanning method for airplane servo elasticity frequency response test

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Experimental program
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Embodiment

[0060] 1. Acceleration sensors are arranged on the trailing edge of the aircraft control surface;

[0061] 2. Reference Figure 4 Disconnect the feedback loop of the flight control system of the aircraft between the output end of the rudder deviation command of the flight control computer and the synthesis end of the forward command of the actuator, and connect it to the real-time simulation system;

[0062] 3. Build an automatic AM sweep simulation model in the real-time simulation system. The automatic AM sweep simulation model includes a constant-amplitude step sine excitation signal generation function module, an automatic AM signal generation function module, and a loop dynamic characteristic calculation function module;

[0063] 4. Refer to Figure 4 , according to the text description in the figure, complete the signal transmission connection between the equal-amplitude step sine excitation signal generation module, the automatic amplitude modulation signal generation ...

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Abstract

The invention belongs to the field of airplane aeroelasticity tests, and relates to an airplane ground test scope, in particular to an automatic amplitude modulation frequency scanning method for an airplane servo elasticity frequency response test. Control plane overloads are fed back to automatically adjust a frequency scanning amplitude value, on the premise that safety of a control pane structure is guaranteed, control plane deflection exciting force of all frequency scanning points is kept maximum so that sufficiently large airplane structure response can be excited, the signal to noise ratio of a response signal of an airplane-flight control combined circuit is improved, test errors are reduced, and reliability of a test result is improved. Meanwhile, the adjusting process of an excitation signal amplitude value is controlled through construction of a hyperbolic tangent-exponent function, violent response of a control plane caused by sudden changes of the excitation signal amplitude value is prevented from happening in the process of frequency scanning, and safety of the control plane structure is ensured. In addition, the advantages of a real-time simulation system of a computer are brought into full play, in the process of the test, people only need to slightly click a mouse, so that parameters such as control limit overloads and excitation signal cycles can be adjusted, and the automatic amplitude modulation frequency scanning method is high in practicability.

Description

Technical field: [0001] The invention belongs to the field of aircraft aeroelasticity test, relates to the field of aircraft ground test, in particular to an automatic amplitude modulation sweeping method for aircraft servo elastic frequency response test. Background technique [0002] When carrying out aircraft ground servo elastic frequency response tests, the equal-amplitude variable-frequency sinusoidal excitation signal is usually injected in front of the actuator to drive the deflection of the rudder surface, and the aircraft is excited by the inertial force caused by the deflection of the rudder surface. The airborne flight control sensor (accelerometer , angular rate gyro, etc.) After sensing the vibration information of the airframe, the control law is used to solve the output rudder deviation command, and the open-loop frequency response characteristics of the aircraft-flight control combined circuit can be obtained by measuring the rudder deviation command output b...

Claims

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Application Information

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IPC IPC(8): G05B23/02G05B13/04
Inventor 蒲利东洪兆贵高怡宁
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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