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

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...

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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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