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- W2076450164 abstract "As electric propulsion technology has improved and mission requirements have changed, a series of Ion Propulsion Module (IPM) design concepts have evolved. The most recent iteration occurred in the NASA-sponsored Halley Comet Rendezvous Mission (HCRM) study of ion drive. Spacecraft system design considerations introduced by the integration of such an IPM as the primary propulsion source are described with reference to the synthesis of the HCRM spacecraft and spacecraft design considerations for other interplanetary applications. IPM interactions with the system (especially telecommunications and science) are found to be manageable. The spacecraft design developed for the HCRM indicates the interface simplicity between the IPM and the spacecraft. Methods are shown for readily applying this IPM to a variety of planetary missions. Methods are also described for the IPM to provide up to 5 kW to the spacecraft for increasing the mission science return" @default.
- W2076450164 created "2016-06-24" @default.
- W2076450164 creator A5084977940 @default.
- W2076450164 date "1978-04-25" @default.
- W2076450164 modified "2023-10-02" @default.
- W2076450164 title "System design of an ion drive spacecraft" @default.
- W2076450164 cites W2061174301 @default.
- W2076450164 doi "https://doi.org/10.2514/6.1978-642" @default.
- W2076450164 hasPublicationYear "1978" @default.
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