Comparison between Solar Simulation and Infrared Technique for Thermal Balance Test
The precision of heat flux simulation influences the temperature field and test aberration for TB test and also reflects the test level for spacecraft development. This paper describes TB tests for a small satellite using solar simulator, electric heaters, calrod heaters to evaluate the difference of the three methods. Under the same boundary condition, calrod heaters cases were about 6C higher than solar simulator cases and electric heaters cases for non-external-heat-flux cases (extreme low temperature cases). While calrod heaters cases and electric heaters cases were 5~7C and 2~3C lower than solar simulator cases respectively for high temperature cases. The results show that the solar simulator is better than calrod heaters for its better collimation, non-homogeneity and stability. Keywords—solar simulation, infrared simulation, TB test, TMM
Design and construction of the JPL SS15B solar simulator.
Space simulator modification to incorporate larger solar simulator, noting beam diameter and luminous intensity uniformity
MARS PATHFINDER ACTIVE THERMAL CONTROL SYSTEM: GROUND AND FLIGHT PERFORMANCE OF A MECHANICALLY PUMPED COOLING LOOP
The Mars Pathfinder spacecraft was launched on December 3, 1996. The major objectives of the Mars Pathfinder are to demonstrate low cost entry, descent, and landing technologies for use in the subsequent flights to Mars. Further, the Pathfinder includes a lander that will operate for one month on the Martian surface conducting surface science studies assisted by a microrover. The temperature control requirements of the spacecraft during launch, cruise, and Martian surface operation necessitated the design of an active thermal control system for the heat rejection system. A mechanically pumped single phase Freon cooling loop is used to transfer excess heat generated in the electronics shelf to an external radiator. This is the first time a mechanically pumped cooling loop has been used on a planetary mission. Several lessons were learned from this experience about the design and operation of the active cooling loops. These lessons are expected to help in building lighter and higher performance loops for the future spacecraft missions. This paper describes the performance of the mechanically pumped cooling loop during ground and flight operations. It describes some of the tests done on the ground and operational procedures developed for the flight based on the ground test experience to ensure higher reliability for the cooling loop.