DESIGN AND OPERATION OF AN IR - CAGE FOR THERMAL VACUUM TESTING OF A COMMUNICATION SATELLITE

摘要

A specific infrared radiation device was designedand manufactured for infrared simulation on acommunication satellite. For the thermal vacuumtest of this satellite, radiation fields with differentsizes, shapes and radiation intensities were requiredto deliver additional heating power onto the spacecraftpanels. Five of the six sides of the cubeshapedsatellite had to be equipped with flat IRframesso that a cage surrounding the S/C had to bedesigned.The following features of the IR-cage were required:A lightweight, but still rigid construction ofthe frame with space-proofed materials; using ofstandard components for cost reasons; radiationintensities of 400 to 1100 W/m~2; a computer-basedsystem for individual control of the heating circuits;a user friendly and safe handling of the operationpanel and the recording of all operational parameter.The mechanical construction was realised by usingaluminium profiles. The standard components allowedcompleting the mechanical set-up within ashort time. After some investigation concerning theheating devices it was decided to use heating stripsfor the radiation fields of low intensity and commercialIR-quartz radiators for fields with higherintensity. A special suspension for the heating stripswas designed to keep them under defined tension.The power supplies for the heating circuits werecomputer-controlled. The software allowed theindividual power setting of each heater. Additionallyan automatic mode for controlling the heatersby a reference thermocouple was foreseen.Beside design features of the cage, this paper willalso describe the heater concept and the controlsystem, and it will have a look at QA relevant matters.