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Sun orientation device main structure suitable for space station

A technology of orientation device and main structure, applied in transportation and packaging, space navigation equipment, space navigation aircraft, etc., can solve the problems of large size and short life, and achieve the effect of light weight and high rigidity

Pending Publication Date: 2022-03-11
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing sun-oriented structures have the problems of large size, light weight, and short life, which urgently need to be solved

Method used

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  • Sun orientation device main structure suitable for space station
  • Sun orientation device main structure suitable for space station
  • Sun orientation device main structure suitable for space station

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0028] The present invention will be further elaborated below in conjunction with embodiment.

[0029] The invention provides a main structure of a sun-orientation device suitable for a space station, which adopts a combined configuration of three large carbon fiber composite material cone structures and one carbon fiber composite material flat disk flange structure. A carbon fiber composite material cone structure is used to transmit the load of the top truss end to the maximum extent, and another two carbon fiber composite material material cone structures and a carbon fiber composite material flat disk structure are used to provide an installation platform for the internal components of the sun orientation device. Guarantee the rigidity and strength requirements of the solar orientation device.

[0030] The main structure of the sun orientation device, such as figure 1 As shown, it specifically includes a main bearing frame 1, an upper mounting frame 2, a lower mounting fr...

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Abstract

The invention relates to a sun orientation device main structure suitable for a space station, and belongs to the field of sun orientation device design. Comprising a main heavy frame, an upper mounting frame, a lower mounting frame and a cabin interface flange, wherein the cabin body interface flange is of an annular structure which is vertically arranged in the axial direction; the upper mounting frame and the lower mounting frame are both of a conical disc-shaped structure; the upper mounting frame is coaxially mounted at the top of the cabin body interface flange, and the large-diameter end of the upper mounting frame is in butt joint with the cabin body interface flange; the lower mounting frame is coaxially mounted at the bottom of the cabin body interface flange, and the large-diameter end of the lower mounting frame is in butt joint with the cabin body interface flange; the main heavy frame is of a hollow conical column structure; the main heavy frame is coaxially installed on the top of the cabin body interface flange, and the large-diameter end of the main heavy frame is in butt joint with the cabin body interface flange. The main heavy frame sleeves the outer side of the upper mounting frame; in order to meet the requirements of light weight and high rigidity of the space station, the composite material structure is adopted for the first time, and the requirement of 15-year on-orbit long service life is met.

Description

technical field [0001] The invention belongs to the design field of a sun orientation device, and relates to a main structure of a sun orientation device suitable for a space station. Background technique [0002] The main structure of the conventional sun-orientation device of a spacecraft is mostly a metal structure, which is mainly used as the shell of the sun-orientation device to form a whole with the internal components of the sun-orientation device. Cooperate to complete the function of the sun-orienting device to drive the solar wing to orient itself to the sun. [0003] The main structure of the sun-orientation device of the space station needs to be used as the main load-bearing structure in addition to the function of integrating the individual components of the sun-orientation device into a whole. The main structure of the space station’s sun orientation device is arranged between the resource cabin and the truss at the tail of the space station’s experimental c...

Claims

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Application Information

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IPC IPC(8): B64G1/22
CPCB64G1/22
Inventor 刘子仙马志飞傅质彬钱志源李红史立涛许文彬汤亮刘鲁江
Owner SHANGHAI AEROSPACE SYST ENG INST
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