Problem areas for further study As a result of the system analysis, several points which need to be scrutinized for further study have been identified as follows. Technology options As for energy conversion, solar cells arc better fitted to this system than a solar dynamic system, considering the attitude control requirement. However, the assumed amorphous silicon solar cell has to be compared with others in terms of cost and mass properties and radiation degradation. The mass of the electrical cable which is larger than the structure mass is a critical problem for the system design. Further study on the possibility of using higher voltage, and analysis to shorten the length of the current path will be required. Power transmission employing retro-directive as well as computer control is a key technology of this system in a LEO. The technology for this system is being developed with an engineering model as an experiment onboard the space station. The engineering data on the mass properties, thermal design, consistency of the high voltage of the power supply and other problems are not yet fully obtained. Selection of the type of semiconductor amplifier for the antenna elements will be most important from the standpoint of cost reduction and robustness of the system. Many options can be considered for flight unit modularization. If the launch cost is higher than the payload system cost, the size and mass of a flight unit will be affected significantly by selection of the transportation system. This problem is related to the payload integration and orbital construction work. Automated deployment and assembly with robotics will be used for the orbital construction work. The optimum combination of these two functions should be pursued for the purpose of reducing the related cost.
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