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Large-scale deployable high-rigidity high-storage-ratio light shield

A high-rigidity, light-shielding technology, applied in the field of spacecraft structure, can solve the problems of low material utilization, low rigidity, and large weight.

Active Publication Date: 2021-05-18
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] With the development of spacecraft technology, large optical lenses and their hoods are widely used on spacecraft, and the requirements for size are increasing. However, the conventional hood configuration has high weight, low rigidity, and low material utilization. , so it is not suitable for application on future spacecraft

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Embodiment Construction

[0017] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0018] In this design, the height of the sunshade after deployment is not less than 14m, and the diameter is about 4.5m. The following configuration design is proposed for the deployment of such a super-large sunshade:

[0019] Such as figure 1 As shown, the deployment cover 1 is a non-enclosed light shield. Because it is suitable for geosynchronous orbits, it is required to use partial direction light shielding. The deployment cover 1 adopts a 180° oblique cut design. Compared with the complete cylindr...

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Abstract

The invention provides a large-scale deployable high-rigidity high-storage-ratio light shield. The light shield comprises an unfolding cover, a supporting cylinder, an unfolding mechanism, a large-bearing pressing and releasing device, a locking mechanism and backlight face heat dissipation holes, the unfolding cover is connected with the supporting cylinder, the unfolding mechanism is arranged at the connecting rotating position of the unfolding cover and the supporting cylinder, the locking mechanism is arranged at the connecting position of the unfolding cover and the supporting cylinder and on the sunshine irradiation side, and the backlight face heat dissipation holes are formed in the side, back to the sunshine, of the supporting cylinder; and when the unfolding cover is folded and tightly attached to the supporting cylinder, the large-bearing pressing and releasing device is connected with the unfolding cover and the supporting cylinder. For the mechanically unfolded light shield, the integral design of the light shield and the supporting cylinder in the folded state enables the whole light shield to have higher rigidity and smaller envelope size, the design fully considers the structural light weight, and the light shield has better rigidity, smaller envelope size and higher material utilization rate.

Description

technical field [0001] The invention relates to a spacecraft structure, in particular to a large-scale expandable light shield with high rigidity and high storage ratio. Background technique [0002] With the development of spacecraft technology, large optical lenses and their hoods are widely used on spacecraft, and the requirements for size are increasing. However, the conventional hood configuration has high weight, low rigidity, and low material utilization. , so it is not suitable for application on future spacecraft. [0003] CN201310658895.3, a large-scale deployable shading mechanism applied to spacecraft, CN201710571616.8, a space-deployable large-scale inflatable film shading structure, and a deployable shading cover for GEO laser communication driven by memory alloy, CN201610396374.9. The inflatable deployment mechanism and the deployment method of the sunshade are designed. [0004] The above technical problems have raised the demand for the light shield used f...

Claims

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Application Information

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IPC IPC(8): G03B11/02
CPCG03B11/02
Inventor 丁海鑫沈毅力王舒杨薛景赛张晓彤
Owner SHANGHAI SATELLITE ENG INST
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