Completion of Optical Inter-Orbit Communications Engineering Test Satellite (OICETS)

Details Completion of Optical Inter-Orbit Communications Engineering Test Satellite (OICETS) Completion of Optical Inter-Orbit Communications Engineering Test Satellite (OICETS)

Jan 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.586n&link_type=abstract

IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,

Computer Science

Performance

Scientific paper

National Space Development Agency of Japan (NASDA) has developed the Optical Inter-orbit Communications Engineering Test Satellite (OICETS) since 1993 in order to perform the optical inter-satellite communication experiment with ARTEMIS developed by European Space Agency (ESA). The system proto-fright test was completed in January 2002 and OICETS is ready for launch. OICETS has the free space laser communication equipment (so called LUCE) on the anti-earth plane of the main body. The optical source is the semiconductor laser whose output is maximum 200mW. The telescope with 26cm diameter is installed on the 2-axis gimbals. The optical and ATP (Acquisition, Tracking and pointing) performances of LUCE were evaluated during its thermal vacuum test. OICETS is a small satellite whose weight is 570kg and its main body size is 0.8m x 1.0m x 1.5m (height). The orbit is circular with approximately 600km altitude and 35degree inclination. The 2 solar paddles generate the electrical power of more than 1220W at the end of life. The 4 reaction wheels are installed and control the satellite attitude in the response to the attitude error signals from the Inertial Reference Unit (IRU). The attitude is determined according to the signals from the earth sensors and the fine fun sensors. OICETS has the 2-way communication links, which are S- band inter-satellite link and S-band link with the ground station. Following the LUCE test the system proto-flight test were performed. The electrical performance of the satellite system was tested after the system integration, during the thermal vacuum test and at the end of a series of the system proto-flight tests. The critical parameters that characterize the system and component performances were measured and evaluated through the tests. As the mechanical environmental test, the sine vibration test, acoustic test and shock test (due to the separation from the rocket payload attach fitting and the solar paddle deployment) were performed. Before and after each mechanical test the variation of the telemetries and the power consumption were checked. In the vacuum chamber thermal balance test and thermal cycle test were performed. The data of the thermal balance test showed the thermal mathematical model is adequate. After the mechanical environmental tests the alignments of the sensors and actuators were measured and they were evaluated that their variations were within the allowable ranges. In this paper the performance test data of the OICETS flight model will be reported including LUCE.

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