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- W114214161 abstract "ABSTRACT The Communications Technology Satellite (CTS) will be launched into synchronous orbit with a Thor Delta 2914 vehicle in early 1976. CTS is a joint program of the Canadian Department of Communications (DOC), the National Aeronautics and Space Administration (NASA), and the European Space Agency (ESA). The agreements between DOC and NASA formally identify several communications satellite systems technologies to be developed and flight tested in the course of the program, among which are a 3-axis stabilization system to maintain accurate antenna boresight pointing on a spacecraft with flexible appendages, and an extendible lightweight solar array with an initial power output greater than one kilowatt. The present paper describes the corresponding plan and technical activity which is presently being implemented by the Department of Communications in conjunction with SPAR Aerospace Products Limited, University of Toronto Institute for Aerospace Studies, and Telesat Canada. The 3-axis attitude stabilization system for CTS utilizes the ‘momentum wheel with offset thrusters’ principle for on-orbit stabilization. The accuracy of stabilization is projected to be ±0.1° in roll and pitch, and 1.1° in yaw. The solar array for CTS has a beginning-of-life power of 1.2 kilowatt. It employs two solar panels, each 653 cm long and 130 cm wide. The array folds up concertina fashion for stowage, and in deploying and deployed states has significant structural flexibility. CTS will carry instruments to enable flight test, among which are array accelerometers, an array deflection sensing system, array load cells, and temperature sensors. A number of passive ‘monitoring’ and active ‘special excitation’ events will be performed during the two-year mission, to flight test attitude stabilization and solar array design, and to explore structural flexibility and the flexibility and control interaction. In the paper, the stabilization system and solar array are briefly described. Pre-launch analysis, ground test, and parameter determination are discussed. Basic uncertainties which require flight test validation are discussed, and corresponding flight test objectives are outlined. The flight instrumentation to be carried on CTS is described. A computer-based data processing system to be used to handle, distribute, and analyse the flight data, is described. The passive and active events to be monitored during the CTS mission are outlined and discussed." @default.
- W114214161 created "2016-06-24" @default.
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- W114214161 date "1977-01-01" @default.
- W114214161 modified "2023-09-26" @default.
- W114214161 title "PLAN FOR FLIGHT EVALUATION OF ATTITUDE STABILIZATION AND FLEXIBLE SOLAR ARRAY DYNAMICS FOR THE COMMUNICATIONS TECHNOLOGY SATELLITE" @default.
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- W114214161 doi "https://doi.org/10.1016/b978-0-08-021053-7.50010-0" @default.
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