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Composite material structure applicable to point-connected spacecraft

A composite material and spacecraft technology, which is applied in the field of point-connected spacecraft composite material structure, can solve the problem of unsatisfactory strength, failure to guarantee connection strength and stiffness, and inability to solve the lightweight design requirements of the Mars rover structure platform load-bearing cylinder, etc. problems, to achieve the effect of high rigidity, direct force transmission path and wide application range

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AI Technical Summary

Problems solved by technology

However, the installation structure is not ideal in terms of lightweight design and strength, and cannot meet the lightweight design requirements of the structural platform of the new generation of Mars rover in my country, nor can it guarantee the connection strength and rigidity with the carrier.

Method used

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  • Composite material structure applicable to point-connected spacecraft
  • Composite material structure applicable to point-connected spacecraft
  • Composite material structure applicable to point-connected spacecraft

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Embodiment

[0031] The point-connected spacecraft composite material structure of the present invention is composed of the lower end frame 1 of the load-bearing cylinder and the reinforced corner box 2, such as figure 1 shown. The section of the lower end frame 1 is F-shaped, such as figure 2 shown. The lower end frame 1 mainly includes: inclined plane 101, riveting hole 102, flanging flange 103, connecting flange 104, corner box connecting hole 105, parking bracket connecting hole 106 and cross-shaped boss embedded installation hole 107, such as image 3 shown. Reinforced corner box 2 mainly includes: riveting hole 201, reinforcing rib 202, parking bracket connection hole 203, explosion bolt connection hole 204, flange connection hole 205 and explosion bolt connection hole 206, such as Figure 4 shown.

[0032] In order to achieve the design goal of lightweight, the lower end frame 1 of the bearing tube is made of T800 / AG80 carbon fiber material with high specific strength and high ...

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Abstract

The invention relates to a composite material structure applicable to a point-connected spacecraft in the field of star-arrow connecting structures. The composite material structure comprises a force-bearing barrel lower end frame and reinforcing corner boxes, wherein the section of the force-bearing barrel lower end frame is F-shaped; the force-bearing barrel lower end frame mainly comprises an inclined plane, riveting holes, a flanging flange and connecting flanges; the section of the reinforcing corner boxes is L-shaped; riveting holes are formed in the reinforcing corner boxes; the reinforcing corner boxes are riveted to the inclined plane of the lower end frame; the sections of the reinforcing corner boxes are fitted to the surfaces of the inclined plane and the connecting flanges. The composite material structure meets a lightweight design requirement of a force-bearing barrel of a new-generation Mars probe structural platform in China and also guarantees the connecting strengthand the connecting rigidity during connection with a carrier.

Description

technical field [0001] The invention relates to the technical field of star-rocket connection structures, in particular to a composite material structure suitable for point connection of spacecraft. Background technique [0002] With my country's demand for high-precision and high-resolution imaging of spacecraft, especially high-orbit spacecraft put forward strict requirements on the thermal deformation of the installation structure of attitude control instruments, it is almost impossible for the current traditional design form to meet high-orbit spacecraft. High-precision attitude determination and image navigation registration requirements. [0003] Conventional structures of this kind generally require light weight, high rigidity, good electrical conduction and heat transfer characteristics, and sufficient strength, so they are often machined from lightweight aluminum alloy or magnesium alloy materials. When the spacecraft is in orbit, these installation structures are i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/10
Inventor 王建炜赵鑫光杜冬孔祥森陶炯鸣李应典
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