Engineering aspect of the microwave ionosphere nonlinear interaction experiment (MINIX) with a sounding rocket |
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| Affiliation: | 1. Indian Institute of Geomagnetism, New Panvel, Navi Mumbai 410 218, India;2. RISH, Kyoto University, Uji-city, Kyoto 611-0011 Japan;3. Department of Physics, Andhra University, Visakhapatnam 530 003, India;1. Southwestern Institute of Physics, P.O. Box 432, Chengdu, Sichuan, 610041, China;2. Chengdu CAE Technology Ltd, Rm.908, Yu Lin Feng Shang Business Centre, No.47 Yong Feng Rd, 1st Ring Rd., High-tech Zone, Chengdu, Sichuan, 610041, China;1. Department of Engineering and Applied Physics, University of Science and Technology of China, Hefei, 230026, China;2. Institute of Plasma Physics, Chinese Academy of Sciences, Hefei, 230031, China;3. Institute for Fusion Studies, the University of Texas at Austin, Austin 78712, Texas, United States;1. Key Laboratory of Radiation Physics and Technology (Sichuan University), Ministry of Education, Institute of Nuclear Science and Technology, Sichuan University, Chengdu 610064, PR China;2. Key Laboratory of Material Corrosion and Protection of Sichuan Province, School of Materials Science and Engineering, Sichuan University of Science and Engineering, Zigong 643000, PR China;3. Southwestern Institute of Physics, Chengdu 614000, PR China |
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| Abstract: | The Microwave Ionosphere Nonlinear Interaction Experiment (MINIX) is a sounding rocket experiment to study possible effects of strong microwave fields in case it is used for energy transmission from the Solar Power Satellite (SPS) upon the Earth's atmosphere. Its secondary objective is to develop high power microwave technology for space use. Two rocket-borne magnetrons were used to emit 2.45 GHz microwave in order to make a simulated condition of power transmission from an SPS to a ground station. Sounding of the environment radiated by microwave was conducted by the diagnostic package onboard the daughter unit which was separated slowly from the mother unit. The main design drivers of this experiment were to build such high power equipments in a standard type of sounding rocket, to keep the cost within the budget and to perform a series of experiments without complete loss of the mission. The key technology for this experiment is a rocket-borne magnetron and high voltage converter. Location of position of the daughter unit relative to the mother unit was a difficult requirement for a spin-stabilized rocket. These problems were solved by application of such a low cost commercial products as a magnetron for microwave oven and a video tape recorder and camera. |
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