Design and Analysis of Thermal Control System for IRS-1C

摘要

The change in size, mass, power dissipation, duty cycle of operation, layout pattern and the additional packages used in the IRS-1C spacecraft for obtaining enhanced capabilities and improved resolution compared to the IRS-1A/1B spacecraft require a new thermal design mandatory. A passive thermal control system (TCS) is used to maintain the spacecraft and its subsystems within the specified temperature limits. The adequacy of the TCS is verified theoretically with the help of thermal mathematical models. The lumped parameter approach is used. A detailed global thermal model and a few other specific models of many subsystem packages are developed. Temperature distribution of the overall spacecraft and some subsystem packages are presented and discussed.