Space remote sensor support frame made of carbon fiber composite

A space remote sensor and composite material technology, applied in the field of high-strength space remote sensor support frame structure, to achieve the effects of high structural strength, lower center of gravity, and improved stability

Inactive Publication Date: 2012-06-27
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Application Information

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Problems solved by technology

However, limited by the rocket's carrying capacity and launch cost, it is required that the structural parts of the spacecraft must be as light as possible while ensuring the strength, and must also adapt to the complex and harsh space environment

Method used

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  • Space remote sensor support frame made of carbon fiber composite
  • Space remote sensor support frame made of carbon fiber composite
  • Space remote sensor support frame made of carbon fiber composite

Examples

Experimental program
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Embodiment Construction

[0016] Such as figure 1 , 2 , 3, and 4, the carbon fiber composite space remote sensor support frame of the present invention includes a first embedded part 1, a second embedded part 2, a first horizontal lifting ring 3, a third embedded part 4, a fourth embedded part Embedded part 5, second horizontal lifting ring 6, remote sensor support frame main body 7, third horizontal lifting ring 8, fifth embedded part 9, first vertical lifting ring 10, second vertical lifting ring 11, sixth embedded Part 12, the fourth horizontal lifting ring 13, the seventh embedded part 14, the eighth embedded part 15, the third vertical lifting ring 16, the fourth vertical lifting ring 17, the ninth embedded part 18, the tenth embedded part 19. The main body 7 of the remote sensor support frame is made of epoxy resin matrix material of model TDE-85 and carbon fiber of model T700, the external dimensions are 900mm long, 900mm wide, 400mm thick, and the diameter of the inner cylinder is Φ750mm. The...

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Abstract

The invention relates to a space remote sensor support frame made of carbon fiber composite, comprising a horizontal lifting ring, a remote sensor support frame body and a vertical lifting ring. The remote sensor support frame body is formed into a three-dimensional grid-like structure by a closed shell, internally peripherally radiating reinforcing ribs and axially parallel reinforcing ribs. Theshape of the inner side wall of the shell corresponds to the shape of a space remote sensor; the outer side wall of the shell comprises an circular-arc shaped plate, a left vertical plate, a right vertical plate, a front plate, a rear plate and a bottom plate; the left vertical plate is connected with the bottom plate through a left horizontal plate and a left inclined plate; the right vertical plate is connected with the bottom plate through a right horizontal plate and a right inclined plate; the space remote sensor is fixedly connected with a round flange of the remote sensor support framebody; and the horizontal lifting ring and the vertical lifting ring are connected with the remote sensor support frame body through pre-buried components. The space remote sensor support frame made of carbon fiber composite has a light weight, high structural strength and high lightweight rate and can be applied to the space remote sensing field and the rocket, aviation and machinery industries.

Description

technical field [0001] The invention belongs to the technical field of space remote sensing applications, and relates to a high-strength space remote sensor support frame structure made of carbon fiber composite materials. Background technique [0002] Space remote sensors are used to conduct general surveys and detailed surveys of earth and space resources, and their applications in fields such as earth observation and space exploration have important scientific and military significance. In order to improve the resolution of the space remote sensor, it is necessary to increase the aperture of the remote sensor to absorb more energy. However, limited to the rocket's carrying capacity and launch cost, it is required that the structural parts of the spacecraft must be as light as possible while ensuring the strength, and must also adapt to the complex and harsh space environment. As one of the most excellent materials at present, carbon fiber composite materials are being us...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16M13/02
Inventor 董吉洪郭权锋李威
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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