System and method for testing dynamic stiffness of airplane horizontal tail servo actuating mechanism

Abstract

The invention provides a system and a method for testing the dynamic stiffness of an airplane horizontal tail servo actuating mechanism. The system comprises ground maintenance and detection equipment(1), a flight control computer (2), a system tester (3), a dynamic stiffness test bed and the like (4), wherein the dynamic stiffness test bed (4) comprises a dynamic stiffness test bed body (41) anda dynamic stiffness test bed control system (42). The method comprises the following steps: drawing a required dynamic stiffness amplitude-frequency characteristic curve through loading force and corresponding position feedback, and finding out the lowest point of the dynamic stiffness amplitude and the corresponding frequency value according to the drawn characteristic curve. The system can truly and effectively measure the dynamic stiffness amplitude-frequency characteristic curve, and according to the testing method, the lowest point of the dynamic stiffness amplitude of the horizontal tail servo actuator and the frequency corresponding to the lowest point can be found out, and necessary data support is provided for analyzing the airplane servo flutter phenomenon and optimizing the horizontal tail servo actuator and a gap eliminating connecting mechanism between the horizontal tail servo actuator and a control surface.

Description

technical field [0001] The invention belongs to the technical field of measurement and control, and specifically relates to a dynamic stiffness test system and a test method of an aircraft horizontal tail servo actuator. Background technique [0002] The servo actuation mechanism of the aircraft's horizontal tail is the core component to realize the change of the pitch direction of the aircraft. With the maturity of the current aircraft design level, substantial breakthroughs have been made in the expansion of the traditional flight envelope. However, when the clearance of the rudder surface of the aircraft is within the design range and the dynamic and static indicators of the horizontal tail servo actuator meet the design requirements, there will be non-command ups and downs in the pitch direction when performing tasks such as high altitude-high speed, low altitude-high speed, etc. Jitter, more serious can induce flutter. The fundamental reason is that the aerodynamic lo...

AI Technical Summary

Problems solved by technology

However, when the clearance of the rudder surface of the aircraft is within the design range and the dynamic and static indicators of the horizontal tail servo actuator meet the design requirements, there will be non-command ups and downs in the pitch direction when performing tasks such as high altitude-high speed, low altitude-high speed, etc. Shaking, more serious can induce chattering

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