A simulation method of heat flow outside the thermal vacuum test of a high-orbit remote sensing satellite platform

A thermal vacuum test and remote sensing satellite technology, which is applied in the field of heat flow simulation outside the thermal vacuum test of the high-orbit remote sensing satellite platform, can solve problems such as deviations, achieve high precision, high simulation accuracy, and small occlusion effects

Active Publication Date: 2020-07-14
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

Therefore, under normal circumstances, when the conventional infrared cage is used to simulate the external heat flow, the test results of low temperature and high temperature conditions will have a large deviation from the on-orbit results.

Method used

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  • A simulation method of heat flow outside the thermal vacuum test of a high-orbit remote sensing satellite platform
  • A simulation method of heat flow outside the thermal vacuum test of a high-orbit remote sensing satellite platform
  • A simulation method of heat flow outside the thermal vacuum test of a high-orbit remote sensing satellite platform

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

[0018] An embodiment of the present invention provides a method for simulating heat flow outside a thermal vacuum test of a high-orbit remote sensing satellite platform, comprising the following steps:

[0019] S1, such as figure 1 As shown, the infrared cage 3 is placed on the heat dissipation surface 2 side of the star body 1 to be measured by the rotating mechanism 4, and the distance between the heat dissipation surface 2 and the infrared cage 3 is 200mm, as figure 2 As shown, the material o...

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Abstract

The invention discloses a thermal vacuum test external heat flux simulation method of a high-orbit remote sensing satellite platform, which comprises the following steps of placing an infrared cage onone side of the heat dissipation surface of the star to be measured through a rotating mechanism, wherein the infrared cage adopts a heating belt material of nickel-cadmium alloy, the heating belt width is 8mm, the spacing is 12mm, the thickness is 0.1 mm, the heating belt resistivity is 1.02 E. 06 Omega . m, sprayed black on both sides of the heating zone; The infrared cage is rotated along theaxial direction by the rotating mechanism, and the external heat flux is calibrated by the method of constant heat flux density. The invention can meet the external heat flux simulation requirements of extremely low temperature and high temperature of the satellite in orbit. High simulation accuracy; So that that shield effect is small.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for simulating heat flow outside a thermal vacuum test of a high-orbit remote sensing satellite platform. Background technique [0002] In order to verify the correctness of the thermal design of the spacecraft and ensure the reliable operation of the spacecraft in space, sufficient space thermal environment simulation tests must be carried out during the development process. The accuracy of heat flow simulation outside space directly affects the level of spacecraft heat balance test. The simulation technology of heat flow outside the space is relatively difficult, and infrared heating cages, heating sheets, infrared lamps, and solar simulators are mainly used. Among them, the solar simulator has the highest accuracy, but the cost is very high, and it is generally used for small optical loads. The size of the whole star is relatively large, and the thermal balance t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 付鑫曹建光俞洁江世臣胡炳亭康奥峰杨剑陈彬彬程梅苏王彦刘炜葳
Owner SHANGHAI SATELLITE ENG INST
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