Satellite roof refined thermal design device

A technology for refining heat and roof, applied in the aerospace field, can solve the problems of uneven temperature, large roof area, large temperature change, etc., to achieve low cost, high reliability, and reduce temperature gradients and fluctuations.

Inactive Publication Date: 2018-09-14
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

In addition, the area of ​​the top plate is large, which makes the temperatur

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  • Satellite roof refined thermal design device
  • Satellite roof refined thermal design device

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[0014] 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 modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0015] Such as figure 1 As shown, the embodiment of the present invention provides a refined thermal design device for a satellite roof, including a satellite roof, a multi-layer structure, a thermal insulation gasket 2, and a screw 1; and the extra-satellite multi-layer heat insulation assembly 8, the multi-layer heat insulation assembly 8 in the star is coated on the lower side of the satellite roof and is arranged towards the inner side of the star, and the extra-satellite multi-layer heat insu...

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Abstract

The invention discloses a satellite roof refined thermal design device which comprises a satellite roof, a multilayer structure, a thermal insulation gasket and screws, wherein the multilayer structure comprises a satellite interior multilayer thermal insulation assembly and a satellite exterior multilayer thermal insulation assembly; the satellite interior multilayer thermal insulation assembly is coated on the lower side of the satellite roof and arranged towards the satellite interior side; the satellite exterior multilayer thermal insulation assembly is coated on the upper side of the satellite roof and arranged towards the satellite exterior side; a load is connected onto the satellite roof by virtue of screws; the thermal insulation gasket is positioned between the load and the satellite roof. According to the satellite roof refined thermal design device disclosed by the invention, the influences of space environment and internal external heat flux on the roof can be greatly reduced, the temperature gradient and fluctuation of the roof can be reduced, and different temperature requirements of the roof on a transition section and during an in-orbit period can be met; due to athermal insulation design of the roof and the load, heat leakage of the load can be effectively reduced, and the temperature gradient and fluctuation of the roof can be reduced; the thermal design method is reasonable and feasible, full in material source, high in reliability, simple in process operation, easy to realize and low in cost.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a refined thermal design device for a satellite roof. Background technique [0002] As the main bearing surface of the satellite payload, the roof has extremely strict requirements on temperature uniformity and stability. Especially for optical loads, the temperature change of the top plate will affect the structural stability of the load, and then affect its observation accuracy. Any slight deformation will cause the pointing difference of the optical axis to be thousands of miles away. During the flight of the satellite, the illumination angle of the roof keeps changing, resulting in complex and changeable external heat flow. At the same time, satellites have multiple working modes, and the heat generated by a single unit in a satellite varies with different working modes. In addition, the area of ​​the top plate is relatively large, which makes the temperature in each are...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/22
Inventor 陈彬彬俞洁付鑫康奥峰胡炳亭江世臣杨剑刘炜葳程梅苏王彦袁荣钢夏远镜曹建光
Owner SHANGHAI SATELLITE ENG INST
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