Helicopter flight control system transfer characteristic test method

A technology of flight control system and transfer characteristics, applied in the direction of aircraft component testing, etc., can solve the problems of resonance danger and reduce resonance damping margin, etc.

Active Publication Date: 2021-03-16
CHINA HELICOPTER RES & DEV INST
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AI Technical Summary

Problems solved by technology

The change of the helicopter's flight attitude is a low-frequency change. The flight control system controls the rotor pitch in real time according to the flight attitude signal. The pitch also changes at a low frequency according to the feedback flight attitude, so that the blades move with the low-frequency movement of the helicopter to produce waving and shimmy motions

Method used

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  • Helicopter flight control system transfer characteristic test method
  • Helicopter flight control system transfer characteristic test method
  • Helicopter flight control system transfer characteristic test method

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Embodiment Construction

[0019] The flight control system transfer characteristic test method involved in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0020] The first step: test preparation, the flight control system transfer characteristic test can be carried out on the model rotor test bench, the test system includes the test bench and the model rotor installed on the test bench. The test bench is a helicopter simulated fuselage test bench, which should include control system, test system, video system, mechanical system and auxiliary system. The composition of the test system is as follows: figure 1 shown.

[0021] (1) Test piece inspection. Before the test, check and record by visual observation and knocking to determine whether there is interference or cracks in the rotor system. Equipment such as test instruments, meters and sensors should be within the validity period, and the measuring equipment should meet the requirements...

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Abstract

The invention belongs to the technical field of helicopter dynamic tests, and discloses a helicopter flight control system transmission characteristic test method. The method comprises the steps of respectively performing sweep frequency excitation on a rotor time domain total distance and a periodic variable pitch through a control system, operating an excitation signal through a hydraulic actuator cylinder, and measuring the rotor time domain total distance and the periodic variable pitch under excitation; and performing FFT on the time domain total distance and the periodic variable pitch of the hydraulic actuator cylinder and a paddle to obtain a control system total distance and periodic variable pitch frequency domain transfer function. The method can be used for providing data for establishing a helicopter flight control system mathematical model based on tests, and providing basic technical support for establishing a helicopter rotor and body coupling stability model considering a flight control system and stability comprehensive analysis. The method has a certain engineering reference value for design and analysis of ground resonance and air resonance of advanced helicopters in China, and has far-reaching significance for guaranteeing safe flight and stability improvement of modern advanced helicopters.

Description

technical field [0001] The invention belongs to the helicopter dynamics test technology, and relates to a test method for the transmission characteristics of a helicopter flight control system, which grasps the transmission relationship between the input of a hydraulic cylinder and the total pitch of the rotor, and the horizontal and vertical periodic pitch values, and considers the flight control system for the establishment of the test method. The helicopter rotor and body coupled stability model and comprehensive stability analysis provide basic technical support. Background technique [0002] While modern advanced helicopters usually use automatic flight control or stability augmentation systems to increase the stability of helicopter manipulation, advanced helicopters with automatic flight control systems or stabilization systems often encounter automatic Phenomenon in which the flight control system or stability augmentation system adversely affects the helicopter grou...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 朱艳陈焕陈垚锋陈卫星冯志壮孙凤楠钱峰代志雄刘晨
Owner CHINA HELICOPTER RES & DEV INST
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