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A follow-up deployment locking assembly

A locking component and follow-up technology, which is applied in the direction of motor vehicles, aerospace equipment, aerospace vehicles, etc., to achieve the effect of fewer components, no energy consumption, and small size

Inactive Publication Date: 2018-12-21
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the deployment and locking of the space deployable mechanism, the present invention provides a follow-up deployment and locking assembly to achieve the technical problems of reducing the volume, reducing the mass, reducing the degree of complexity, and improving the rigidity and stability.

Method used

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  • A follow-up deployment locking assembly
  • A follow-up deployment locking assembly
  • A follow-up deployment locking assembly

Examples

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Embodiment Construction

[0018] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0019] Such as Figure 1 to Figure 7 As shown in , a follow-up deployment and locking assembly is used to realize the deployment and locking of space deployable components to meet the needs of spacecraft ground tests and on-orbit operations.

[0020] A follow-up type deployment locking assembly includes a positioning pin 1, a lever shaft 2, a lever seat 3, a locking lever 4, a ejector seat 5, a ejector 6 and an ejector spring 7.

[0021] The positioning pin 1 is installed on the movable part 10 , the lever seat 3 is installed on the fixed part 8 , and the movable part 10 and the fixed part 8 are connected by a hinge 9 .

[0022] The locking lever 4 is installed on the lever seat 3 through the lever shaft 2, and the locking lever 4 can rotate around the lever shaft 2. The locking lever 4 includes an upper profile surface 4-1 and a lower profile surface 4-2, the uppe...

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Abstract

A follow-up deployment locking assembly belongs to the spacecraft mechanism field. In order to solve the technical problems of the deployment locking of the spatial deployable mechanism, reducing thevolume, lightening the mass, lowering the complexity and improving the rigidity and stability, the module is used to realize the deployment locking of the spatial deployable mechanism. This assembly includes locating pins, lever shaft, locking lever, Ejector seat, ejector bar and ejector bar spring, the locating pin is installed on the movable part, the lever seat is installed on the fixing part,the movable part and the fixing part are hinged, the locking lever is installed on the lever seat through the lever shaft, the locking lever is rotated around the lever shaft, the ejector seat is installed on the lever seat, the ejector spring is installed inside the ejector seat, the ejector rod is installed in the ejector seat, and the ejector rod is translated along the ejector seat; The assembly has the advantages of small number of components, small volume, light weight, simple structure, convenient disassembly and assembly, no energy consumption, belonging to a passive passive mechanism,high reliability, good self-locking performance, and ensuring the rigidity and stability after locking.

Description

technical field [0001] The invention belongs to the field of spacecraft mechanisms, and in particular relates to a follow-up type deployment locking assembly. Background technique [0002] In the past 20 years, the spatial deployment mechanism has been greatly developed, with more and more forms, more and more complex components, and more and more applications. One of the key components of the deployment mechanism is the deployment locking assembly, which is used to realize the locking of the deployable member after deployment. At present, space deployable components such as solar wings and satellite antennas use a large number of deployable locking components. There are many types and different forms. and other shortcomings. Contents of the invention [0003] In order to solve the deployment and locking of the space expandable mechanism, and at the same time achieve the technical problems of reducing volume, reducing mass, reducing complexity, and improving rigidity and...

Claims

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Application Information

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IPC IPC(8): B64G1/22
CPCB64G1/222
Inventor 杨利伟李志来徐宏董得义柴方茂
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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