Method for estimating sweep frequency voltage of airplane structure modal coupling test

A modal coupling, aircraft structure technology, applied in the testing of machine/structural components, aircraft component testing, vibration testing, etc., can solve the problems of affecting the test results, structural damage, overload of the control surface, etc., to achieve simple input data, The method is convenient and easy to implement

Inactive Publication Date: 2021-06-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0002] The aeroservoelastic stability problem is a stability problem caused by the coupling of aircraft aeroelasticity and flight control, which is directly related to the flight safety of the aircraft; and the structural mode coupling test is a necessary ground for testing the aeroservoelastic stability of the aircraft. The test, through the structural modal coupling test, can grasp the aerodynamic servo elastic performance of the aircraft, and provide reference for the design of the structural notch filter; during the structural modal coupling test, the control surface is vibrated by giving the control surface a sinusoidal excitation , and drives the aircraft body to vibrate; the amplitude of this sinusoidal excitation is controlled by the frequency sweep voltage, and the trial and error method is usually used to obtain the frequency sweep voltage in the past; if the frequency sweep voltage is too large, the control surface will be overloaded and the structure will be damaged. damage; if the frequency sweep voltage is too small, the noise will have a greater impact on the frequency sweep signal, thereby affecting the test results

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  • Method for estimating sweep frequency voltage of airplane structure modal coupling test
  • Method for estimating sweep frequency voltage of airplane structure modal coupling test
  • Method for estimating sweep frequency voltage of airplane structure modal coupling test

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Embodiment Construction

[0020] The present invention will be described in further detail below. see figure 1 and figure 2 , a method for estimating the frequency sweep voltage of an aircraft structural modal coupling test, the aircraft control surface parameters are known, and the parameters include the natural frequency f of the control surface rotational mode n and modal damping ξ n , the control surface servo cut-off frequency f c , the control surface characteristic length c, the maximum overload n that the control surface structure can withstand max , the control surface safety factor s, the relationship K between the known frequency sweep voltage U and the control surface rotation angle θ, and the known test frequency sweep range [f 0 , f max ], estimate the frequency sweep voltage U; the present invention provides a theoretical basis for the frequency sweep voltage estimation of the structural modal coupling test, and provides support for the development of the test; where f n , f c , ...

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Abstract

The invention belongs to the field of aeroelastic mechanics and relates to a sweep frequency voltage estimation method for an aircraft structure modal coupling test. A sweep frequency voltage of the airplane structure modal coupling test is estimated, and reference input data is provided for carrying out the test; the method comprises the following steps of predicting a relation K among a control plane rotation modal inherent frequency fn, modal damping xin, a control plane steering engine cut-off frequency fc, a control plane characteristic length c, a maximum overload nmax which can be borne by a structure, a safety coefficient s, a sweep frequency range [f0, fmax], a sweep frequency voltage U and a control plane rotation angle theta; and estimating the sweep frequency voltage U. According to the method, a theoretical basis is provided for frequency sweep voltage estimation of an airplane structure modal coupling test, and support is provided for development of the test.

Description

technical field [0001] The invention belongs to the field of aeroelasticity, and relates to a method for estimating frequency sweep voltage of an aircraft structure modal coupling test considering the inherent characteristics of a control surface. Background technique [0002] The aeroservoelastic stability problem is a stability problem caused by the coupling of aircraft aeroelasticity and flight control, which is directly related to the flight safety of the aircraft; and the structural mode coupling test is a necessary ground for testing the aeroservoelastic stability of the aircraft. The test, through the structural modal coupling test, can grasp the aerodynamic servo elastic performance of the aircraft, and provide reference for the design of the structural notch filter; during the structural modal coupling test, the control surface is vibrated by giving the control surface a sinusoidal excitation , and drives the aircraft body to vibrate; the amplitude of this sinusoida...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60G01M5/00G01M7/02
CPCB64F5/60G01M5/0066G01M5/0075G01M7/02
Inventor 罗务揆马艳峰柴睿曾宪昂程芳
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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