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A method for measuring the rotation mode of aircraft full-motion horizontal tail

A measurement method and technology of rotating mode, applied in the direction of aircraft component testing, etc., can solve problems such as insufficient excitation force, lack of versatility, and only obtaining the modal characteristics of horizontal tail rotation, so as to achieve comprehensive and reasonable consideration and ensure flutter safety. Effect

Active Publication Date: 2022-07-22
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology

However, the connection between the full-motion horizontal tail shaft and the body is a nonlinear connection, and its rotational modal characteristics are mainly affected by the combined effects of friction and clearance. The modal frequency usually changes significantly with the magnitude of the exciting force. Test method: one is based on the phase separation mode extraction technology, the disadvantage of this method is that usually only the horizontal tail rotation mode characteristics can be obtained when the vibration is small force; the second is based on the phase resonance mode extraction technology, this method can obtain the horizontal tail rotation mode characteristics The force-frequency curve of the rotating mode, but when calculating the excitation force, there is no fixed standard for each type of aircraft, and it is not universal. When the main excitation force point is not selected properly, the excitation force may be insufficient, and the modal test The results cannot fully describe the rotational modal characteristics of the full-motion stabilizer

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  • A method for measuring the rotation mode of aircraft full-motion horizontal tail
  • A method for measuring the rotation mode of aircraft full-motion horizontal tail
  • A method for measuring the rotation mode of aircraft full-motion horizontal tail

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Embodiment Construction

[0017] In order to make it easy to understand the technical means, creation features, achieved goals and effects of the present invention, the present invention will be further described below with reference to the specific figures.

[0018] like Figure 1 to Figure 3 A method for measuring the rotation mode of an aircraft full-motion horizontal tail as shown, the specific steps are as follows:

[0019] Four exciters numbered 1, 2, 3, and 4 are used to obtain the exciting force, and the vertical distances from the four exciter points to the axis of the full-motion horizontal tail are l respectively. 1 =485mm, l 2 =610mm, l 3 =410mm, l 4 = 515mm, the exciter obtains the excitation force F in real time on the computer through the data acquisition card force signal channel 1 , F 2 , F 3 , F 4 , in the full-motion horizontal tail modal test, the phase separation technique is used first to identify the initial dimensionless frequency of the full-motion horizontal tail rotati...

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Abstract

A method for measuring the rotation mode of aircraft full-motion horizontal tail. First, the phase separation technology is used to identify the initial dimensionless frequency of the full-motion horizontal tail rotation mode, and then the phase resonance mode extraction technology is used near this frequency. When the excitation force is large, the force-frequency curve of the full-motion horizontal tail rotation mode can be obtained; when the force-frequency curve of the full-motion horizontal tail rotation mode is obtained, the force of the exciting force is calculated as the resultant moment. M The present invention can more completely consider the nonlinear effect of friction and clearance on the rotation mode of the full-motion horizontal tail, and the force-frequency curve of the full-motion horizontal tail rotation mode measured by the present invention can be used as the input of the horizontal tail flutter calculation. The vibration calculation is considered more comprehensive and reasonable, and the flutter safety of the aircraft is effectively guaranteed.

Description

technical field [0001] The invention relates to the technical field of aircraft structure dynamics test, in particular to a method for measuring the rotation mode of an aircraft full-motion horizontal tail. Background technique [0002] Ground vibration modal test (GVT) is a key test technique to obtain the dynamic characteristics of aircraft structure. The GVT results can be used as an important input for the simulation of aircraft structure dynamics and the calculation of flutter characteristics. For the combat aircraft with full-motion horizontal tail, the horizontal tail rotation mode is usually the main mode that affects its flutter characteristics. How to accurately obtain the horizontal tail rotation mode characteristics in GVT is the key to ensure the safety of aircraft flutter. However, the connection between the full-motion horizontal tail shaft and the body is nonlinear, and its rotational modal characteristics are mainly affected by friction and clearance. The mo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 吴成林陈立勇朱亲强王钱伟罗士超亓洪玲孙超胡豪
Owner JIANGXI HONGDU AVIATION IND GRP
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