Six-unit cubesat main force bearing structure

A six-unit, cubic star technology, applied in the field of the main bearing structure of the six-unit cubic star, can solve the problems of the cubic star cannot be pushed into space, the parallelism cannot be guaranteed, and the work is meaningless, so as to reduce the quality and The effect of space constraints, structural integrity, and practicality

Pending Publication Date: 2018-04-13
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The contact between the Cubestar and the POD is the sliding fit between the four guide rails and the parallel groove-shaped guide rails inside the POD. Therefore, once the parallelism between the four guid

Method used

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  • Six-unit cubesat main force bearing structure
  • Six-unit cubesat main force bearing structure
  • Six-unit cubesat main force bearing structure

Examples

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Embodiment

[0042] The present invention is a six-unit cube star main load-bearing structure, comprising a first cube star unit 1, a second cube star unit 2, a connecting frame 3 and six hinges 4, the first cube star unit 1 and the second cube star unit The units 2 are symmetrically fixed on both sides of the connecting frame 3 and are respectively connected by eight screws; the connecting frame 3 , the first cube star unit 1 and the second cube star unit 2 are respectively provided with two hinges 4 .

[0043] The connecting frame 3 adopts an escalator structure, including two side plates 3-1 and four connecting plates 3-2 for connecting the two side plates 3-1, the two side plates 3-1 are arranged in parallel, and the two connecting plates 3-2 is located on the top surface and the bottom surface of the side plate 3-1, and the remaining two intervals are arranged between the above two connecting plates 3-2. The two side plates 3-1 are used to fasten the first main frame 1-1 and the secon...

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PUM

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Abstract

The invention discloses a six-unit cubesat main force bearing structure. The six-unit cubesat main force bearing structure is formed by means of the method that two three-unit cubesat main frames cooperate with each other through a connecting frame. The main frames are each of a cuboid frame structure, end covers are arranged at the two ends of each main frame in the direction of the long edge, and middle frameworks are arranged in the middles of the main frames. Four screws are arranged in each main frame and penetrate through the corresponding middle framework to be fixed to the end covers of the two ends of the corresponding main frame, and six hinges are arranged on the connecting frame and the two main frames. The assembly difficulty of a cubesat is lowered, and the integrity of innerlayout is improved. According to the six-unit cubesat main force bearing structure, the main frames are of an integrated structure and connected through the connecting frame making contact with the main frames in a large area so that the parallelism between guiding rails can be ensured, the six-unit cubesat main force bearing structure and a cubesat-rocket separating device are not jammed in launching, and successful launching is ensured.

Description

technical field [0001] The invention belongs to the technical field of cube satellites, in particular to a main load-bearing structure of a six-unit cube satellite. Background technique [0002] In recent years, with the rapid development of technologies such as communications, optoelectronic components, materials, sensors, and applied fluids, the development of CubeSat technology has accelerated significantly, and it has become possible to use CubeSats for remote measurement and testing. The low cost has prompted the emergence of cubesat development programs around the world. More and more of them come from the government, enterprises, especially academic institutions with strong scientific research capabilities. The United States and Europe have launched a large number of cubesats. [0003] CubeSat (referred to as CubeSat) belongs to the category of micro-nano satellites, and its development is extremely rapid, and it has been standardized, modularized, and commercialize...

Claims

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Application Information

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IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 张翔胡豪斌梁振华陆正亮邓寒玉刘幸川刘磊
Owner NANJING UNIV OF SCI & TECH
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