Sun wing hinge moment testing device

A technology of hinge moment and testing device, which is applied in the direction of measuring device, testing of mechanical parts, testing of machine/structural parts, etc., can solve the problems that affect the cooperation relationship, the working conditions of the friction pair of hinge components are difficult to analyze and determine, and the hinge cannot be accurately calculated. Drive torque and other issues to achieve the effect of small temperature drift, good load matching performance and high test accuracy

Inactive Publication Date: 2008-09-24
NO 510 INST THE FIFTH RES INST OFCHINA AEROSPAE SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the hinge assemblies used for star and ship solar wing deployment mechanisms are generally in the form of root hinge assemblies (single hinge) or inter-plate hinge assemblies (double hinge), each hinge assembly includes a locking hook, a locking hook shaft, U6 Joint bearings, bearing sleeves, bearing retaining rings, slideways, outer gaskets, planar scroll spring movable parts, etc., because the driving torque, pressing torque and frictional torque of the solar wing hinge assembly are the indicators that reflect the comprehensive performance of the product, so it is important for the solar wing The torque test of the wing hinge is particularly important. The structure of the solar wing hinge assembly is relatively complex. It has complex working conditions such as surface contact, line contact, sliding friction, and "edge-edge" friction, and the thermal vacuum environment affects the cooperation between the parts. , in the harsh space environment, the contact stress of the friction pairs is constantly changing, especially during the deployment of the solar wing, the contact stress of each friction pair of the hinge assembly changes even more, and the working conditions of the friction pairs of the entire hinge assembly Difficult to analyze and determine
Therefore, it is impossible to accurately calculate the driving torque of the hinge. In order to realize the quality control of the hinge components, it is necessary to use a combined test method to test under the conditions of the simulated space environment on the ground to obtain accurate and reliable test data to improve the reliability of space application equipment. and the level of research and development, there is currently no dedicated solar wing hinge torque testing equipment

Method used

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Embodiment Construction

[0017] Referring to Fig. 1~2, the present invention comprises motor 3, support 14, base 18, speed reducer 19, base 18 is vertically fixedly connected with the support 14 that is provided with rack 13, and base 18 is provided with fixed top 16, base 18 Motor 3 and reducer 19 are provided inside. Motor 3 is a stepping motor with two shaft extensions. Supported by the bearing 1, the middle part of the main shaft 24 of the reducer 19 is fixed to the worm wheel 23, one shaft end is fixed to the fixed top 16, and the other shaft end is fixed to the angle sensor 22 by the coupling 20, the worm wheel 23 meshes with the worm 25, and the main shaft 24 is supported by bearing 17. The bracket 14 is provided with a movable top 10 which is movably connected with the rack 13 . Adjusting knobs 9 are provided on both sides of the movable top 10 , and a torque sensor 8 is provided at its top. The bottom plate of base 18 is fixedly connected with 4 adjustable legs 6, and the shells of motor 3, ...

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Abstract

The invention discloses a solar array hinge torque tester which includes a motor, a support, a base and a reducer, and is characterized in that the base and the support with rack are vertically fixed and connected; a fixed tip is arranged on the base; the motor and the reducer are arranged in the base; the motor and the reducer are fixed and connected by a coupler; the fixed tip is fixed on the reducer; the support is provided with a movable tip movably connected with the rack; the reducer is provided with an angle sensor; the movable tip is provided with a torque sensor; the tested data is connected to a PC to be processed; the invention is integrated with movement, control and measurement, adopts a special heating structure of initiative temperature control, can work under -100 DEG C to +70 DEG C of wide temperature, solves the problems of poor adaptability and stability of the tester under vacuum, high-temperature and low-temperature environment, is very applicable in ground simulation test of hinge assembly components of all star and ship solar array unfolding mechanisms, and has the advantages of high test precision, good load matching performance, little temperature drift of the torque and angle sensors.

Description

technical field [0001] The invention relates to the testing field of space application equipment, in particular to a solar wing hinge moment testing device. Background technique [0002] At present, the hinge assemblies used for star and ship solar wing deployment mechanisms are generally in the form of root hinge assemblies (single hinge) or inter-plate hinge assemblies (double hinge), each hinge assembly includes a locking hook, a locking hook shaft, U6 Joint bearings, bearing sleeves, bearing retaining rings, slideways, outer gaskets, planar scroll spring movable parts, etc., because the driving torque, pressing torque and frictional torque of the solar wing hinge assembly are the indicators that reflect the comprehensive performance of the product, so it is important for the solar wing The torque test of the wing hinge is particularly important. The structure of the solar wing hinge assembly is relatively complex. It has complex working conditions such as surface contact...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00G01M19/00G01L3/00G01B21/22G01M99/00
Inventor 翟少雄温庆平王长胜周晖郝宏
Owner NO 510 INST THE FIFTH RES INST OFCHINA AEROSPAE SCI & TECH
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