Transient Thermalanalysis Of Spacecraft In Launch And Transform

The thermal control platform, including thermal analysis and thermal controltechnology, is to ensure that is an important part of the spacecraft safe and reliablework. Thermal analysis is a guarantee of the reasonable thermal control design. Atpresent, thermal analysis calculation of multi-spacecraft researched in orbit stage,ignoring the thermal characteristics of the spacecraft in launch and transfer process.In contrast, the launching spacecraft, although there were shells to protect it, was ina more complex thermal environment, that effect of internal equipments temperaturewas obvious; in the transfer process, external heat flux of the orbit varied, and alsodetermineed the temperature characteristics of equipments. Therefore, carrying outthe thermal analysis of these two stages, played a crucial role in the normal workingof the spacecraft.In this paper, based on the thermal environment in launch and transform, acombination of SINDA/FLUINT software and self programming was to carried outthermal analysis calculations for a closed system consisting of spacecraft shell andequipments. The main contents included:1.An analysis of the thermal environment in the vehicle during launch wascarried out, which convective heat transfer was formed by reducing the internalpressure with increasing altitude, and it was got temperature properties aboutspacecraft equipments;2.Based on relationship among of the geocentric coordinate system, the vehiclebody coordinate system and solar. External heat flux of the orbit was receiced inMonte Carlo method;3.The temperature characteristics of equipments was obtained by influence ofthe heat flow of outer space and work of equipments in the transfer process aboutspacecraft, changes of temperature of equipments were gained after analysis of atypical thermal control technology implementation.Through the above research, it can grasp the calculation method of externalheat flux of the orbit in the process of spacecraft transform, and it can be to obtaininfluence of convective heat transfer for spacecraft and provide theoretical supportfor further thermal control design.