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公开(公告)号：US12044220B2
公开(公告)日：2024-07-23
申请号：US17802468
申请日：2021-02-22
CPC分类号： F03H1/0081 , B64G1/411 , B64G1/413 , B64G1/415 , F03H1/0068
摘要： A satellite propulsion system and methods of operating the same include a first ionization stage and a second acceleration stage. The first ionization stage has a plasma source configured to produce an arc discharge and emit a preliminary plasma. The plasma source includes an external magnetic field configured to magnetize the arc discharge. The second acceleration stage has an accelerator positioned in series with the plasma source. The accelerator is configured to accelerate the preliminary plasma out through the accelerator, thereby creating an accelerated plasma flow. The application of an activation threshold voltage to the accelerator results in a surge in system performance parameters.
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公开(公告)号：US11760508B2
公开(公告)日：2023-09-19
申请号：US16645334
申请日：2018-10-10
CPC分类号： B64G1/405 , B64G1/10 , F03H1/0081
摘要： A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.
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公开(公告)号：US20230406544A1
公开(公告)日：2023-12-21
申请号：US18238249
申请日：2023-08-25
CPC分类号： B64G1/413 , F03H1/0081 , B64G1/10
摘要： A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.
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