A hot knife structure with adjustable resistance applied to micro-nano-satellites
A micro-nano satellite and adjustable technology, which is applied to the power supply system of space navigation aircraft and other directions, can solve the problems of large forbidden area and large separation impact of solar wings, and achieve the effects of simple structure, easy assembly and short production cycle.
Active Publication Date: 2022-04-15
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology
[0004] The present invention is to solve the problem that the existing solar wing unlocking method has a large separation impact and the solar wing requires a large forbidden area, and further provides a hot knife structure with adjustable resistance applied to micro-nano satellites
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specific Embodiment approach 1
[0018] Specific implementation mode one: combine Figure 1~2 Describe this embodiment, a hot knife structure applied to micro-nano-satellites with adjustable resistance, which includes a package case 1, a cable board 2 mounted in the package case 1, and an axial sliding sleeve on the package case The mounting seat 3 on the 1 and the limit nut 4 threaded on the package shell 1, the resistance wire 5 is arranged on the cable plate 2, and the two sides of the cable plate 2 and the inner wall of the package shell 1 An insulating pressing plate 6 is interposed, and the two ends of the wiring board 2 are respectively connected to the two insulating pressing plates 6 by screws 7. The mounting base 3 is fixed to the surface of the star body, and the distance between the limit nut 4 and the mounting base 3 A pre-tension spring 8 is sheathed on the encapsulation shell 1 between them, and a fuse part 9 is fixedly mounted on one end of the cable board 2 . The through hole formed on the i...
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The invention relates to a hot knife structure with adjustable resistance applied to micro-nano satellites, which belongs to the technical field of spacecraft solar sail panel deployment. The invention solves the problems that the existing solar wing unlocking method has a relatively large separation impact and a large forbidden area for the solar wing. Including the package case, the cable board installed in the package case, the mounting seat which is axially slid on the package case and the limit nut which is threaded on the package case, and the resistance wires are arranged on the cable board , there is an insulating pressure plate sandwiched between both sides of the cable board and the inner wall of the package shell, and the two ends of the cable board are respectively connected to the two insulating pressure plates by screws, and the mounting base is fixed to the surface of the star body. A pre-tightening spring is sheathed on the packaging shell between the bit nut and the mounting seat, and a fuse part is fixedly installed at one end of the wiring board. The application is simple in structure, easy to assemble, light in weight, small in impact, low in production cost, short in production cycle, and does not occupy space, and can meet the requirements of low research and development costs and high reliability of micro-nano satellites.
Description
technical field [0001] The invention relates to a hot knife structure with adjustable resistance applied to micro-nano satellites, and belongs to the technical field of spacecraft solar sail panel deployment. Background technique [0002] With the rise of commercial aerospace, more and more cube stars and micro-nano satellites have been successfully launched into space. As an important part of the power subsystem, the solar wing plays a vital role in the satellite. In the cube star Some technology verification satellites usually use the method of attaching battery sheets to the surface of the structure. However, with the development of commercial satellites, micro-nano satellites are endowed with more business requirements due to their advantages such as small size, light weight, and short development cycle. , and when the whole star has many loads and functions, considerate solar cells are far from meeting the mission requirements on the star. At this time, the whole star n...
Claims
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IPC IPC(8): B64G1/44
CPCB64G1/44
Inventor 赵相禹张道威赵春娟张雷谷松陈善搏高飞段胜文孙洪雨
Owner CHANGGUANG SATELLITE TECH CO LTD