PROPULSION SYSTEM FOR SPACECRAFT
    1.
    发明公开

    公开(公告)号:US20230150697A1

    公开(公告)日:2023-05-18

    申请号:US17918303

    申请日:2020-10-09

    CPC classification number: B64G1/401 B64G1/402 F02K9/62 F03H1/0075 B64G1/405

    Abstract: A thrust generator is provided for producing thrust to move a spacecraft. The thrust generator includes a housing having a first end and an opposing second end. The first end is associated with a mount for coupling to the spacecraft. The housing further defines a central axis extending through the first end and the second end. The second end defines an annular propulsion outlet. At least one nozzle is positioned proximate the second end. The thrust generator is selectively operable in a first mode in which the thrust generator uses propellant to electrostatically generate thrust via the annular propulsion outlet, and a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust via the at least one nozzle.

    HALL-EFFECT THRUSTER
    3.
    发明公开

    公开(公告)号:US20230279845A1

    公开(公告)日:2023-09-07

    申请号:US18117977

    申请日:2023-03-06

    CPC classification number: F03H1/0075 F03H1/0068 F03H1/0081 H01J27/146

    Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.

    PROPULSION SYSTEM FOR SPACECRAFT
    4.
    发明公开

    公开(公告)号:US20230192322A1

    公开(公告)日:2023-06-22

    申请号:US17918309

    申请日:2020-10-09

    CPC classification number: B64G1/402 F02K9/80

    Abstract: A control assembly for a spacecraft includes a propellant management assembly configured to adjust a supply of propellant from a storage unit to a thrust generator. The control assembly further includes a controller having a processor configured to receive an input from the spacecraft, and receive at least one input from the propellant management assembly or from the thrust generator. The processor is further configured to, based on the inputs, determine a desired operating mode of the thrust generator, and based on the determination, either 1) send an output to the propellant management assembly to operate in a first mode in which the thrust generator uses propellant to electrostatically generate thrust or 2) send an output to the propellant management assembly to operate in a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust.

    HALL-EFFECT THRUSTER
    6.
    发明申请

    公开(公告)号:US20210310466A1

    公开(公告)日:2021-10-07

    申请号:US17050770

    申请日:2020-04-02

    Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.

    Propulsion system for spacecraft
    8.
    发明授权

    公开(公告)号:US12157586B2

    公开(公告)日:2024-12-03

    申请号:US17918303

    申请日:2020-10-09

    Abstract: A thrust generator is provided for producing thrust to move a spacecraft. The thrust generator includes a housing having a first end and an opposing second end. The first end is associated with a mount for coupling to the spacecraft. The housing further defines a central axis extending through the first end and the second end. The second end defines an annular propulsion outlet. At least one nozzle is positioned proximate the second end. The thrust generator is selectively operable in a first mode in which the thrust generator uses propellant to electrostatically generate thrust via the annular propulsion outlet, and a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust via the at least one nozzle.

    PROPULSION SYSTEM FOR SPACECRAFT
    9.
    发明公开

    公开(公告)号:US20230150698A1

    公开(公告)日:2023-05-18

    申请号:US17918293

    申请日:2020-10-09

    Abstract: A propulsion system for a spacecraft includes a thrust generator for producing thrust to move the spacecraft. A propellant storage unit is in fluid communication with the thrust generator. A control assembly is in communication with the spacecraft. The control assembly includes a propellant management assembly configured to adjust a supply of propellant from the storage unit to the thrust generator. A controller is configured to control the propellant management assembly. The control assembly is configured to selectively operate the thrust generator in a first mode in which the thrust generator uses propellant to electrostatically generate thrust, and a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust.

    Hall-effect thruster
    10.
    发明授权

    公开(公告)号:US11598321B2

    公开(公告)日:2023-03-07

    申请号:US17050770

    申请日:2020-04-02

    Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.

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