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

A technology of servo actuation and test system, applied in the field of measurement and control, which can solve problems such as flutter and jitter

Active Publication Date: 2020-04-14
JIANGXI HONGDU AVIATION IND GRP
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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 requirem...

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

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Embodiment Construction

[0015] The following will combine figure 1 , clearly and completely describe the technical solutions in the embodiments of the present invention.

[0016] Such as figure 1 , Complete the installation and system connection of the horizontal tail servo actuating mechanism and the mechanical platform of the dynamic stiffness test bench.

[0017] Firstly, the system tester 3 sends commands to the flight control computer 2 for retracting the landing gear, loading the wheels, static pressure 101.325 MPa, and dynamic pressure 0 MPa.

[0018] Then, the ground maintenance detection equipment 1 sends a ground maintenance command to the flight control computer 2; the flight control computer 2 sends a position command signal of the horizontal tail servo actuator, and transfers it to the horizontal tail servo actuator 6 through the system tester 3; at the same time , the horizontal tail servo actuator 6 transfers the position feedback signal to the flight control computer 2 through the s...

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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...

Claims

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Application Information

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IPC IPC(8): B64F5/60G01M99/00
CPCB64F5/60G01M99/007
Inventor 胡海英谭磊梁琼花裴登洪黄祖丹殷晓华朱辉杰王晓坤韩占朋黄勇强
Owner JIANGXI HONGDU AVIATION IND GRP
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