Fig. 5. Concept of plasma plume measurements. TABLE 3 ORBITAL OPERATIONS REQUIREMENTS (Operation Constraints) APPLICATIONS In the case that the electric thruster is applied to one way orbit transfer to the synchronous orbit, it must be operated for three months at least. If it takes longer, more payload can be carried. The thruster will be used as a space tug several times, if its life is much longer. For the present, the useful life goal is 5000 h. Therefore, in this mission, the duration of test operation should be 5000 h at least, for all thrusters to be tested, and, if possible, operation over 10,000 h is desired to be conducted for one of both MPD and ION thrusters. During and after the testing, the system can be used as an economical rebooster or for the attitude control of MSS. After verifying its functions, the system can work for COTV and, further, for the propulsion system of a planetary explorer. REFERENCE 1. K. Kuriki. MPD Solar Electric Propulsion, in Preliminary Concepts of Space Station Missions, Part 2 (MS-SS-02), edited by Japan Space Station Task Team, pp. 2-30, Tokyo, 1983. 2. Y. Nakamura and S. Kitamura, Ion Engine Test, in Preliminary Concepts of Space Station Missions, Part 2, (MS-SS-02), edited by Japan Space Station Task Team, pp. 2-30, Tokyo, 1983.
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