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Force loading method and device for high-speed retraction and release test of landing gear

A landing gear and high-speed technology, which is applied to measurement devices, aircraft component testing, mechanical component testing, etc., can solve the problems of inability to adapt to high-speed landing gear retraction time, non-linear retraction and retraction process, and fast retraction speed. The effect of great practical application value

Active Publication Date: 2019-12-20
AVIC BEIJING CHANGCHENG AVIATION MEASUREMENT & CONTROL TECH INST +1
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  • Application Information

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Problems solved by technology

[0005] In order to solve the above problems, the present invention provides a force loading method and a loading device for the high-speed landing gear retraction test. Problems with characteristics such as nonlinearity

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  • Force loading method and device for high-speed retraction and release test of landing gear
  • Force loading method and device for high-speed retraction and release test of landing gear
  • Force loading method and device for high-speed retraction and release test of landing gear

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Embodiment Construction

[0032] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0033] See attached image 3 As shown, the device for the force loading method used in the high-speed landing gear retraction test in this embodiment includes a loading mechanism, a test measurement and control system 1, and a power supply. The loading mechanism includes an air source device 2, a solenoid valve 3, and a split air circuit 4 , pressure regulating valve 5, manual shut-off valve 6, high-speed cylinder 7, air source equipment 2 is connected to the inlet port of the diversion air circuit 4 through the solenoid valve 3, and the outlet port of the diversion air route 4 is passed through the manual shut-off valve 6, pressure regulating valve 5 is connected to the piston chamber of the high-speed cylinder 7, the piston rod of the high-speed cylinder 7 is connected to the shock absorber strut of the landing gear, and the...

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Abstract

The invention discloses a force loading method and device for a high-speed retraction and release test of a landing gear. The force loading method and device are used for simulating the aerodynamic force or other related power borne by the high-speed movement of the landing gear of an airplane in the high-speed retraction and release test process of the landing gear of the airplane. The method comprises the following steps of 1) calibrating response time of a loading mechanism; 2) calibrating each action starting time of the landing gear, 3) editing the control signal sending time, 4) startinga test; and 5) monitoring the environmental data condition of a test bed to generate a test log. The device for realizing the method is an open-loop control loading device taking a high-speed cylinder as a medium, the blank of a force loading method in the high-speed retraction and release test process of the landing gear of the airplane taking a high-pressure air source as driving force is filled, and the test means of the force loading method of the landing gear of the airplane is perfected.

Description

technical field [0001] The invention relates to a force loading method and a loading device for a high-speed landing gear retraction test, belonging to the technical field of aircraft landing gear ground tests. Background technique [0002] The landing gear system of an aircraft is one of the key components of the aircraft. The performance of the landing gear system directly affects the safety of the aircraft's ground movement, takeoff and landing. Among the key components of the aircraft, aircraft accidents caused by the failure of the landing gear system occur from time to time. Therefore, it is essential to carry out the ground test of the aircraft landing gear system, and the loading test of the landing gear system is the most critical part. [0003] During take-off or landing, the aircraft needs to retract or lower the hatch and landing gear. During this process, the hatch and landing gear will be affected by aerodynamic force. During the development cycle of an aircr...

Claims

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Application Information

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IPC IPC(8): B64F5/60G01M13/00
CPCB64F5/60G01M13/00
Inventor 孟昭阳封锦琦李燕杰江继龙王红项东
Owner AVIC BEIJING CHANGCHENG AVIATION MEASUREMENT & CONTROL TECH INST
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