Abstract
Abstract In this manuscript, the temperature model of multilayer insulation (MLI) on a spacecraft solar panel in thermal radiation is considered. The thermal insulation performance of MLI and the stress of the spacecraft are also considered. The thermal equilibrium equation of the surface temperature of MLI spacecraft in the presence of current transfer, and the iterative temperature acquisition algorithm of the front and back surface of solar panel MLI are derived. The Gaussian elimination method is used to invert the high order sparse matrix composed of error coefficients, thus realizing the real-time calculation of thermal re-radiation(TRR). The thermodynamic model was applied to the motion simulation of GPS Block IIR satellites, and the theoretical model was verified based on the actual temperature measurement data of several GPS Block IIR satellites. The simulation results have certain reference value for studying the thermodynamic modeling of MLI spacecraft and TRR perturbation calculation.
Highlights
In recent years, great progress has been made in the fields of gravity, the sea surface measurement, global land surface, and glacier measurement
The Gaussian elimination method is used to invert the high order sparse matrix composed of error coefficients, realizing the real-time calculation of thermal re-radiation(TRR)
The thermodynamic model was applied to the motion simulation of GPS Block IIR satellites, and the theoretical model was verified based on the actual temperature measurement data of several GPS Block IIR satellites
Summary
Great progress has been made in the fields of gravity, the sea surface measurement, global land surface, and glacier measurement. One of the problems is to improve the precision of the perturbation models of spacecraft by analyzing and modeling some perturbation terms which have not been given enough attention before These effects include solar radiation pressure (SRP), thermal re-radiation (TRR), earth radiation pressure (ERP) and effects due to satellite transmission. Fliegel and Gallini (1996) explained the importance of the spacecraft thermodynamic model and pointed out that it accounts for approximately 5% of the total solar perturbation It is called the T20 model in the satellite model of GPS Block II. Marquis and Krier (2000) outlined the mechanism of partial nonconservative force, including SRP and TRR perturbations of solar panels, radiators, antennas and other spacecraft surfaces covered by multilayer insulation (MLI). Darugna et al (2018) established a ray-tracing model for Japan QZS-1 satellite and discussed the deviation from orbit determination caused by ignoring the thermal effect in this model
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