CALCULATION METHOD OF THE TRANSIENT TEMPERATURES FOR MOVING SPACE OBJECT ON THE ELLIPTICAL ORBIT
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Despite the large number of publications on this subject, there are no currently analytical methods of calculation that can evaluate the temperature changes of the space object, moving on the extended elliptical orbit. Calculation method of the transient temperatures of the isothermal spherical shell space object, moving on the elliptical orbit, is suggested. It includes the calculation of time dependence of the space object altitude above the Earth based on the solution of the equation of motion on the elliptical orbit. Irradiance coefficients are calculated at each time point and are used for calculation of heat fluxes from the Earth and solar radiation reflected by the Earth and falling on the object. Then calculation of the transient heat balance is done including heat flux from the sun and average surface temperatures. Calculation results of the transient thermal condition of the space object for specific characteristics of orbit and specific heat, depending on thickness of the wall, is presented as an example. The proposed mathematical model is easy and convenient for calculations. The proposed algorithm can be extended to the other convex design configuration.
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