Low-impact repeatable locking and separation device for space effective load

A separation device and payload technology, which is applied in the direction of the docking device of aerospace vehicles, can solve the problems of large unlocking impact force and other problems, and achieve the effect of good expansion.

Active Publication Date: 2018-03-06
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Traditional space payloads represented by satellites are locked by locking devices during l

Method used

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  • Low-impact repeatable locking and separation device for space effective load
  • Low-impact repeatable locking and separation device for space effective load
  • Low-impact repeatable locking and separation device for space effective load

Examples

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Embodiment Construction

[0028] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0029] Such as figure 1 with 2 As shown, the device of the present invention includes a load platform 21, 4 support bases 4 and 2 slider crank assemblies 1; the four support bases 4 are symmetrically arranged on the load platform 21 at four corners, and are independently connected to the load platform 21, Used to fix the captured payload 3; the crank slider assembly 1 is installed on both sides of the load platform 21, and its position corresponds to the compression rod 3-1 connected to the payload 3; each of the support bases 4 A guide piece 2 is provided on each of the two outer end faces for catching the payload 3 .

[0030] Such as image 3 (a) to (c), the slider crank assembly 1 includes a lock hook 1-4, a slider 1-12, a connecting rod 1-9, a crank 1-10, a driving mechanism, a torsion spring 1-3, a left support plate 1-2 and right support plate 1-...

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Abstract

The invention discloses a low-impact repeatable locking and separation device for a space effective load. Large-scale capturing and locking of the effective load can be well achieved through rotary swinging and a straight line movement coupling design of a latch hook in a crank slide block assembly; effective resistance to in-plane load borne by the effective load in the launching process can be achieved through cooperation using of a supporting seat oblique plane structure and a compression block oblique plane structure; speed reduction and torque increasing effects can be achieved by arranging a worm and a gear between a motor and the crank slide block assembly, and meanwhile, the locking reliability of the device to the effective load can be ensured through the self-locking property; the device has good expansion performance, can adapt to locking and separation of effective loads with different sizes and volumes, and not only can meet the requirements for spaceflight locking and separation missions, but also can meet repeated locking and separation requirements of various cargoes in the industrial transporting process by changing the physical dimension of the effective load according to needs.

Description

technical field [0001] The invention belongs to the technical field of aerospace equipment, and in particular relates to a low-impact repeatable locking and separating device for space payloads. Background technique [0002] Traditional space payloads represented by satellites are locked by locking devices during launch, and unlocked by pyrotechnic devices when they reach the predetermined orbit. Unlock the impact. In order to meet the needs of space missions such as on-orbit modular assembly, construction and upgrade of large spacecraft cabins, payloads such as cube stars can be reliably locked during the launch phase, and payloads can be repeatedly locked on-orbit The device with the separation function has become one of the hotspots of research at home and abroad. At the same time, the device is required to have the advantages of low impact, miniaturization, light weight, and scalability during the locking and separation process, so as to improve and promote the applicat...

Claims

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Application Information

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IPC IPC(8): B64G1/64
Inventor 王文龙杨哲史文华杨飞郝丽敏
Owner BEIJING INST OF SPACECRAFT SYST ENG
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