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Thermal Control Method for Attitudeless Satellite

A thermal control and satellite technology, which is applied in the direction of space vehicle life condition control devices, etc., can solve the problem of no attitude control satellite thermal control method, etc., to save weight, enhance isothermal level, and enhance radiation heat transfer Effect

Active Publication Date: 2013-10-23
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0005] Some non-attitude control satellites have been developed in the world, but no relevant reports on thermal control methods for non-attitude control satellites have been found

Method used

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  • Thermal Control Method for Attitudeless Satellite
  • Thermal Control Method for Attitudeless Satellite
  • Thermal Control Method for Attitudeless Satellite

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Experimental program
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Embodiment

[0064] 1. Due to the unclear direction of external heat flow, in terms of equipment layout,

[0065] a. In the structural layout design, the instruments and equipment should be avoided to be installed on the starboard cabin, and each instrument and equipment should be installed on each partition in the cabin, and the energy flow can be controlled through radiation heat exchange and conduction heat transfer between the structural frames;

[0066] b. According to the shape of the whole star as an octagonal prism with the Z axis as the axis of symmetry, the layout principle of the instruments and equipment is to use the Z axis as the axis of symmetry, and the power consumption is distributed symmetrically.

[0067] 2. Considering the isothermal temperature of the whole star, according to the size of the satellite, layout restrictions and orbital parameters, it needs to be arranged as follows: figure 2 The 3D isothermal device composed of the 3D heat pipe combination in the three...

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Abstract

The thermal control method of the non-attitude satellite, paste or spray the high-emissivity thermal control coating on the equipment in the star, fill the thermal conductive filler between the equipment installed on the partition and the installation surface, and spray the high-emissivity thermal control coating on the inner surface of the rest of the structure star Floor. The inner surface of the cabin board is covered with multi-layer heat insulation components to reduce the impact of drastic changes in heat flow outside the outer orbit of the star. Except for the installation surface of the instrument and equipment, the structural star module is pasted with third-order gallium arsenide solar cells. From the perspective of top-level system design, the present invention is based on the whole star isothermal design idea, fully utilizes the whole star structure heat storage, and utilizes solar cells as energy supply equipment and temperature control means at the same time, and adopts three-dimensional direction 3D isothermal heat pipe combination and integration The 3D isothermal device composed of a metal frame solves the problem of ensuring the temperature level of the entire satellite when there is no attitude control.

Description

technical field [0001] The invention belongs to the field of thermal control of spacecraft, and relates to a thermal control method for the temperature level of satellite instruments and equipment. Background technique [0002] In recent years, small satellites have attracted the attention of experts due to their high technology integration, low cost, and short development cycle, and have achieved rapid development. With the advancement of electronic integration technology and payload miniaturization technology, microsatellites smaller than small satellites will also emerge, which is also the inevitable product of the rapid development of microelectronics and micromechanical systems (MEMS) in the field of science and technology. The weight of a microsatellite is generally less than 100 kilograms, and the smallest is more than ten kilograms, or even several kilograms. The biggest advantage of micro-satellites is that they can be mass-produced and deployed in large numbers in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/50
Inventor 范庆梅易桦江海麻慧涛
Owner BEIJING INST OF SPACECRAFT SYST ENG
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