A belt type compression release device for transmission shaft

A release device and transmission shaft technology, which is applied in the application field of aerospace technology, can solve problems such as no reports on the pressing and releasing device of a dual-axis solar wing drive mechanism, and achieve the effect of improving product reliability.

Active Publication Date: 2014-05-28
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] After searching, there is no report at home and abroad about the compression release device for protecting the dual-axis solar wing drive mechanism

Method used

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  • A belt type compression release device for transmission shaft
  • A belt type compression release device for transmission shaft
  • A belt type compression release device for transmission shaft

Examples

Experimental program
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Embodiment Construction

[0023] The present invention will be further described below in conjunction with the accompanying drawings.

[0024] Such as figure 1 As shown, the compression release device of the present invention includes a strap assembly and a storage assembly. Wherein the strap assembly is composed of two separated straps 1 connected by the left strap connector 2 and the right strap connector 3 at both ends; the separated strap 1 is connected with the left strap connector 2 and the right strap connector 3 by spot welding. Considering the unlocking reliability in the design, it is designed into two sections, which are connected into a circular ring through a titanium alloy pull rod 5 with a nut. Clamped to withstand various loads in flight. The manufacturing material of the separation tape 1 is a titanium alloy strip, which has good forming processability, small internal stress after forming, high modulus of elasticity, and easy to achieve the required pre-tightening force.

[0025] Th...

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Abstract

The invention discloses a belt-type compression release device for a transmission shaft, which comprises a belt assembly and a storage assembly; the belt assembly is composed of two separated belts (1) butted through belt joints at both ends; two pull rods ( 5) Pass through the pull rod holes and the cutter (4) on the two separation tape heads respectively, connect the two separation tapes (1) bent into a semicircle into a ring, and tighten the drive shaft; each separation tape There are V-shaped clamps (22) and W-shaped clamps (23) staggered and fixed on the inner side of the belt (1); the storage assembly is composed of two sets of the same storage devices, which are symmetrically distributed on both sides of the belt assembly, and fixed on the star (10) superior. The device of the present invention adopts the form of tape + clamping block, which greatly reduces the load on the dual-axis solar wing drive mechanism during satellite launch, protects the dual-axis solar wing drive mechanism from being able to withstand the mechanical environment during launch, and has basically no performance. decline.

Description

technical field [0001] The invention belongs to the application field of aerospace technology, in particular to a compression release device for a transmission shaft of a spacecraft. Background technique [0002] Since the 1980s, my country began to study the satellite single-axis solar wing drive mechanism, which has been successfully applied to dozens of satellites so far. In the early 21st century, with the diversification of satellite missions in our country, higher requirements were put forward for the solar wing drive mechanism, and the development of the dual-axis solar wing drive mechanism was started. [0003] The single-axis solar wing drive mechanism has a "one"-shaped structure and good rigidity; the dual-axis solar wing drive mechanism has a "T"-shaped structure, and one of the shafts is suspended outside the body of the satellite. The force-bearing form is not good and the rigidity is poor, so it cannot Meet the mechanical environment requirements when the sat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44
Inventor 刘宾姜水清赵永涛徐燕菱史谨文鲁秀敏
Owner BEIJING INST OF SPACECRAFT SYST ENG
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