Method for measuring full-motion horizontal tail rotating mode of airplane

Abstract

The invention relates to a method for measuring a full-motion horizontal tail rotating mode of an airplane, which comprises the following steps of: firstly, identifying an initial dimensionless frequency of a full-motion horizontal tail rotating mode by adopting a phase separation technology, and then obtaining a force frequency curve of the full-motion horizontal tail rotating mode by adopting aphase resonance mode extraction technology near the frequency and gradually increasing exciting force from small to large; when the force frequency curve of the full-motion horizontal tail rotating mode is obtained, processing the force of the exciting force by a resultant moment M. According to the method, the nonlinear influence of friction and gaps on the full-motion horizontal tail rotation mode can be more completely considered, the force-frequency curve of the full-motion horizontal tail rotation mode measured by the method is used as the input of horizontal tail flutter calculation, theflutter calculation can be considered more comprehensively and reasonably, and the flutter safety of an airplane is effectively guaranteed.

Description

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

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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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