dc.description.abstract | In response to the environmental test for missions, like Aspectmeter for Sounding Rocket VIII(SR-VIII), Multifunction Integrated Optical Circuit made by NCU, Space Plasma Sensor Package and Fiber Optical Gyroscope for Sounding Rocket IX(SR-IX), Advanced Ionospheric Probe for FORMOSAT-5 satellite, etc. A thermal vacuum test system is constructed in Space Payload Laboratory, National Central University, to provide a space environmental test for space payloads. The system consists a vacuum chamber, a copper thermal exchange base plate, a thermal source, and a set of control module. The chamber can be pumped down to high vacuum (under 10-3 Pa) in 30 minutes from 1atm to 3.9×10-3 Pa. A Device Under Test (DUT) can be placed on the base plate inside the chamber pumped down to high vacuum to experience temperature cycle provided by the thermal source. An in-house temperature cycling program is developed to control the temperature on the surface of thermal base plate (or DUT) from ambient to 80°C in 20 min, from 80°C to -40°C in 40 min, and from -40°C to ambient in 20 min. The program can minimize temperature overshoot and undershoot within ±2°C and rapidly reduce temperature fluctuation within ±1°C in 10 min. Furthermore, temperature variances between an input temperature cycling profile and a temperature measurement result can be smaller than 0.5 for a test process. The program can also conduct thermal cycling test inside thermal cycling chamber with the same performance. With a 3-D model simulation and flow setting, we can copy the same condition of real test and get the simulation result of temperature on thermal plate. Compare with the result with real test data, we can contribute a bigger and better thermal exchange base plate in the future. | en_US |