Heat design method of cubesat

A thermal design and cube star technology, applied in computing, special data processing applications, instruments, etc., can solve the problems of cumbersome calculation iteration process and many calculation parameters

Active Publication Date: 2014-12-17
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

This method overcomes the shortcomings of the traditional thermal design method in the process of calculating the dynamic characteristics of the thermal control system, the calculation par

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  • Heat design method of cubesat

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Embodiment Construction

[0052] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0053] Such as figure 1 As shown, a thermal design method of a cube star includes the following steps:

[0054] (1) External heat flow analysis: calculate the periodic average of solar radiation heat flow, earth albedo heat flow and earth radiation heat flow;

[0055] The specific way to calculate the period average value of solar radiation heat flow, earth reflection heat flow and earth radiation heat flow is as follows:

[0056] (1a) On each surface of the satellite +X, -X, +Y, -Y, +Z, -Z, according to the thermal radiation theory, the solar radiation heat flux incident on the micro-element dA on the satellite dq 1 for: Among them, Se is the solar constant, take 1354W / m 2 , Respectively, the solar radiation angle coefficient; figure 2 As shown, according to the spherical geometry and spherical trigonometric functions, the he...

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Abstract

The invention relates to a heat design method of a cubesat. The heat design method comprises the following steps of external heat flow calculation: the periodic average values of solar radiation heat flow, earthlight heat flow and earth radiation flow are calculated; heat radiation mode selection: according to the solar radiation heat flow, the earthlight heat flow and the earth radiation flow, the corresponding space heat sink temperature on each surface of a satellite and on the satellite skin can be calculated, in addition, the maximum space heat sink temperature and the minimum space heat sink temperature of each surface are determined, and the heat radiation surface is selected according to the space heat sink temperature obtained through calculation; heat radiation surface area calculation: the heat radiation surface area is determined according to the highest work temperature and the greatest space heat sink temperature required by satellite single-machine equipment; and active temperature control power determination. The heat design method has the advantages that parameters such as the heat radiation area and the active control power are accurately calculated, the problems of many parameters (for example, the heat radiation area and the active control power are set according to the experience of engineers), control equation nonlinearization and calculation iteration complexity of the traditional heat design analysis method are solved, and the development period is greatly shortened.

Description

technical field [0001] The invention relates to a thermal design method of a cube star, belongs to the technical field of spacecraft thermal control, and is suitable for a thermal design method of a cube star (CubeSat). This method has stronger predictability and adaptability, and is especially suitable for an integrated and generalized cubesat thermal control platform. Background technique [0002] With the rapid development of microelectronics and micromechanical systems (MEMS) technology and lightweight manufacturing industry, the comprehensive application of electronic packaging integration technology, payload miniaturization technology and new materials and new processes has brought a new product of the satellite industry— — Cube star. California State Polytechnic University and Stanford University proposed the CubeSat specification in 1999: a regular hexahedron satellite with a size of 10cm×10cm×11cm and a mass of about 1.33kg is a 1U cube star with a size of 10cm×10c...

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Application Information

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IPC IPC(8): G06F17/00
Inventor 刘佳黎明付伟达孙骥施思寒
Owner AEROSPACE DONGFANGHONG SATELLITE
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