Landing impact test device and test method thereof

A technology of impact test and test cabin, which is applied in the field of mechanical testing, can solve the problems of lack of versatility and inability to simulate the pitch angle of the cabin, and achieve the effects of improving authenticity and reliability, shortening the development cycle, and strong bearing capacity

Active Publication Date: 2015-09-23
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Abstract
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Problems solved by technology

This device is mainly used for a 1/2 scaled-down crew cabin, which is not universal and has a relatively simple structure. It simulates t

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  • Landing impact test device and test method thereof

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Embodiment Construction

[0031] Below in conjunction with accompanying drawing and specific embodiment the present invention will be described in further detail:

[0032] Such as figure 1 As shown in the schematic diagram of the device structure, the landing impact test device of the present invention includes a test frame 1, a suspension device 2, a firing control device 3, a fixed pulley 4, a steel cable 5, a motor 6, a landing bed 7 and a test cabin 8, wherein:

[0033] The test frame 1 includes a fixed support frame and a cross arm, the fixed support frame is vertically fixed on the ground, the cross arm is vertically installed on the fixed support frame and parallel to the ground, the cross arm can move up and down smoothly on the fixed support frame, and can Rotate in the horizontal plane with the support frame as the axis.

[0034] The suspension device 2 includes a swing arm and a swing bed. The upper end of the swing arm is fixedly installed on the cross arm of the test frame 1, and the swin...

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Abstract

The invention discloses a landing impact test device, and a method for conducting the landing impact test by utilizing the device. The device comprises a test frame, a suspension unit, a percussion control unit, a fixed pulley, a steel cable, a motor, a landing bed and a test cabin. According to the technical scheme of the invention, based on the energy conservation law, the terrain clearance and the tilt angle of the test cabin are regulated, so that the potential energy is converted into the kinetic energy after the application of the test cabin. The preset vertically falling velocity and the preset horizontal velocity of the test cabin are realized. Meanwhile, the posture of the test cabin is set by a regulation tool, and a corresponding landing impact simulated medium can be laid on the landing bed according to the test requirements of different landing grounds. In this way, the soil mechanics characteristics of the simulated medium are enabled to accord with the soil properties of real landing grounds. The authenticity and the reliability of test parameters for the landing impact test on the test cabin are improved. The test method is simple and easy to operate. Meanwhile, the device and the method are strong in bearing capacity, wide in horizontal speed control range, controllable in posture and high in safety coefficient.

Description

technical field [0001] The invention relates to the technical field of mechanical tests, in particular to a landing impact test device and a test method thereof, which are suitable for landing impact tests of various spacecraft, aircraft and other aircraft. Background technique [0002] The spacecraft has to bear the landing shock during the landing process, and the shock load will cause a certain degree of damage to the personnel and equipment in the cabin. In order to ensure the safety of personnel and equipment on board, it is necessary to obtain test data through landing shock tests and analyze the test data to study the response of the spacecraft to the landing shock, obtain key performance and data of the landing shock, and verify the structural design of the spacecraft , The shock attenuation performance of the mechanism design of the buffer device, and evaluate its landing safety. [0003] Among the existing methods in China, such as "Impact Test Method for Railway ...

Claims

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Application Information

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IPC IPC(8): G01M7/08
Inventor 赵玮黄伟郭李杨
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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