Multi-dimensional vibration control method of fulcrum bar tail supporting type aircraft model

Abstract

The invention provides a multi-dimensional vibration control method of a fulcrum bar tail supporting type aircraft model, belongs to the field of vibration active control, and relates to the multi-dimensional vibration control method of the fulcrum bar tail supporting type aircraft model based on a piezoelectric ceramic actuator and applied to an aircraft model wind tunnel test. The multi-dimensional vibration control method comprises the steps that two components of main vibration acceleration of the aircraft model are measured by a pitch acceleration sensor and a yaw acceleration sensor which are arranged on the centroid of the aircraft model, a main vibration vector of the aircraft model is obtained, and the real-time vibration plane of a fulcrum bar is determined; and the inertial force is introduced to solve a dynamic bending moment on an active section of a multi-dimensional vibration damper, and then the stress distribution on the active section is obtained, and the vibration control force is solved in real time according to the stress of the piezoelectric ceramic actuator on the active section. A multi-dimensional vibration active control system is adopted, the stability and reliability of the active vibration control system of a wind tunnel model are improved, the service life of the piezoelectric ceramic actuator is prolonged, and thus the wind tunnel test data quality and wind tunnel test safety are ensured.

Description

technical field [0001] The invention belongs to the field of active vibration control, and relates to a new multi-dimensional vibration control method of a strut and tail support type aircraft model based on a piezoelectric ceramic actuator, which is applied to the wind tunnel test of the aircraft model. Background technique [0002] Wind tunnel test is an important means in the research and development of core operating equipment or components in the aviation field, and its role is irreplaceable. In tests such as full-model measurement and pressure measurement, the aircraft model is fixed on the angle-of-attack adjustment mechanism by connecting the force-measuring balance to the wind tunnel tail support strut. This strut tail support test support system is a typical cantilever beam system. . As the test angle of attack increases, the gas passing through the upper surface of the aircraft airfoil will no longer adhere to the surface of the airfoil, and will fall off from th...

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is to overcome the defects of the existing technology. The existing single-dimensional vibration active control system cannot effectively solve the multi-dimensional vibration generated during the wind tunnel test of the aircraft model, which seriously affects the quality of the test data and threatens the safety of the wind tunnel test. , invented a multi-dimensional vibration control method for strut tail brace aircraft model

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