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Novel landing-gear-drop-test driving rotating device and test method

A landing gear and test belt technology, applied in the field of aeronautical engineering, can solve the problems of not meeting the requirements of belt rotation, affecting the stability of belt rotation, and vibration of the motor, and achieving the effects of simple structure, convenient height adjustment and low cost.

Pending Publication Date: 2018-06-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that the length of the connecting rod and the evacuation speed of the belt runner are limited by the size of the bench, and for the test of large height and the test of the tail sinking condition, this friction wheel belt rotation method cannot meet the belt rotation requirements, and more importantly The motor will vibrate at high speed, which will affect the stability of the belt rotation

Method used

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  • Novel landing-gear-drop-test driving rotating device and test method
  • Novel landing-gear-drop-test driving rotating device and test method
  • Novel landing-gear-drop-test driving rotating device and test method

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Embodiment Construction

[0021] The patent will be further described below in conjunction with the accompanying drawings and specific examples, but not as a limitation of the patent.

[0022] A novel undercarriage drop test belt rotating device provided by the present invention, the device to be rotated includes a motor 1, a friction wheel 2, a lifting screw 3, a support stand 4, a sliding guide rail 5, an actuator 6 and an air pressure adjustment Valve 7, wherein, described sliding guide rail 5 is provided in pairs, is fixed with support stand 4 in its inner side; Described support stand 4 is fixed with slide guide rail 5 as a whole, and slides on slide guide rail 5; A lifting screw 3 is arranged in the frame 4, and the direction of the lifting screw 3 is approximately perpendicular to the direction of the sliding guide rail 4; a motor 1 is provided at the end of the lifting screw 3 away from the sliding guide rail, and a friction wheel 2 is connected to the motor;

[0023] One end of the support sta...

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Abstract

The invention discloses a novel landing-gear-drop-test driving rotating device and a test method, belongs to the technical field of aeronautical engineering, and relates to a driving rotating mechanism in a landing-gear drop test. The novel landing-gear-drop-test driving rotating device is mainly composed of a friction wheel, a motor, lifting threaded rods, supports, guiding rails, an actuator cylinder, an adjusting air valve, a motor rotating speed controller and the like. The device is used for providing the pre-rotating speed for airplane wheels in the landing-gear drop test; according to the actual requirement, the motor and the type of a driving rotating wheel can be replaced, the height of the motor is adjusted, the rotating speed of the airplane wheels is controlled, and the test shows that the novel landing-gear-drop-test driving rotating device is stable and reliable.

Description

technical field [0001] The invention belongs to the technical field of aeronautical engineering, and relates to a belt rotation mechanism in a landing gear drop test, in particular to a novel landing gear drop test belt rotation device. Background technique [0002] This mechanism is used to provide pre-rotating speed for the wheel in the landing gear drop test. In the landing gear drop test, the horizontal speed of the aircraft is simulated by pre-providing the rotation speed to the wheel, so as to simulate the motion state of the landing gear when it touches the ground. Commonly used rotating mechanisms are: hard shaft belt rotation, follower belt rotation and friction wheel belt rotation. The hard shaft belt rotation of the machine wheel needs to connect the hard shaft with the wheel hub, and drive the machine wheel to rotate through the hard shaft. Interference with the measurement of the test results, especially the impact on the test data of the small aircraft landin...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 薛彩军戚兴江徐辉盛旭东
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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