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Solar wing and sectional type secondary unfolding hinge thereof

A secondary deployment and segmented technology, applied in the aerospace field, can solve the problems of not being able to unlock again, and achieve the effect of simple structure and reliable operation

Active Publication Date: 2021-02-02
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] But traditional hinges have the drawback of not being able to unlock again after being locked in place once unfolded

Method used

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  • Solar wing and sectional type secondary unfolding hinge thereof
  • Solar wing and sectional type secondary unfolding hinge thereof
  • Solar wing and sectional type secondary unfolding hinge thereof

Examples

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Embodiment Construction

[0038] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0039] The invention provides a solar wing, such as Figure 5 As shown in the structure, the solar wing includes the outer panel 16, the middle and outer panels 17, and the segmented secondary deployment hinge 18 hinged to the outer panel 16 and the middle and outer panels 17. The specific structure of the segmented secondary deployment hinge 18 is as follows:

[0040] Please refer to figure 1 , figure 2 , image 3 and Figure 4 , the present invention provides a segmented secondary unfolding hinge 18, including a male hinge 14, a female hinge 2 and a scroll spring 9, wherein:

[0041] The female hinge 2 is provided with two opposite hinge plates, and a mounting groove is formed between the two hinge plates; the male hinge 14 is rotatably connected between the two hinge plates of the female hinge 2 through the hinge shaft 11, and a part is accommodate...

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PUM

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Abstract

The invention discloses a solar wing and a sectional type secondary unfolding hinge thereof. The secondary unfolding hinge comprises a male hinge body and a female hinge body which are rotationally connected through a hinge shaft. A swing rod is installed at the tops of the two hinge plates through a swing rod shaft, a locking column is fixedly installed on the swing rod, an ejector rod is fixedlyconnected into the female hinge, a linkage wheel and a shifting fork are installed on the hinge shaft on the outer sides of the hinge plates, and the shifting fork is fixedly connected with the linkage wheel. A volute spiral spring is arranged between the male hinge and the female hinge; the male hinge is provided with a locking groove connected with the locking column in a clamped mode. The sectional type secondary unfolding hinge can be automatically unlocked after being locked in place for the first time, and secondary unfolding and locking are achieved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a solar wing and its segmented secondary deployment hinge. Background technique [0002] After the initial orbit, the existing spacecraft need to provide energy through the solar wing, especially the high-orbit communication satellites with high power requirements. However, if the solar wing is fully deployed, the inertial force of the spacecraft during orbit change will cause a high bending moment at the root of the solar wing. Larger solar wings require a second deployment. The key to the realization of the secondary deployment technology lies in the secondary deployment hinge on the solar wing. When a spacecraft such as a satellite is initially put into orbit, the solar wing is deployed through the secondary deployment hinge and locks a battery panel. At this time, the solar wing can provide some Energy, so that during the orbit change process, the bending moment generate...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/44
CPCB64G1/222B64G1/44Y02E10/50
Inventor 任守志濮海玲杨淑利王晛马腾周志清
Owner BEIJING INST OF SPACECRAFT SYST ENG
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