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公开(公告)号:US20230150697A1
公开(公告)日:2023-05-18
申请号:US17918303
申请日:2020-10-09
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Lyon B. King , Jason M. Makela , Jason D. Sommerville , Robert Washeleski
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.
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公开(公告)号:US20220097871A1
公开(公告)日:2022-03-31
申请号:US17549613
申请日:2021-12-13
Inventor: Lyon B. King
Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.
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公开(公告)号:US20230279845A1
公开(公告)日:2023-09-07
申请号:US18117977
申请日:2023-03-06
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Jason D. Sommerville
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.
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公开(公告)号:US20230192322A1
公开(公告)日:2023-06-22
申请号:US17918309
申请日:2020-10-09
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Lyon B. King , Jason M. Makela , Jason D. Sommerville , Robert Washeleski
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.
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公开(公告)号:US11198523B2
公开(公告)日:2021-12-14
申请号:US16982230
申请日:2019-04-05
Inventor: Lyon B. King
Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.
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公开(公告)号:US20210310466A1
公开(公告)日:2021-10-07
申请号:US17050770
申请日:2020-04-02
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Jason D. Sommerville
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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公开(公告)号:US12246855B2
公开(公告)日:2025-03-11
申请号:US17549613
申请日:2021-12-13
Inventor: Lyon B. King
Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.
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公开(公告)号:US12157586B2
公开(公告)日:2024-12-03
申请号:US17918303
申请日:2020-10-09
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Lyon B. King , Jason M. Makela , Jason D. Sommerville , Robert Washeleski
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.
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公开(公告)号:US20230150698A1
公开(公告)日:2023-05-18
申请号:US17918293
申请日:2020-10-09
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Lyon B. King , Jason M. Makela , Jason D. Sommerville , Robert Washeleski
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.
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公开(公告)号:US11598321B2
公开(公告)日:2023-03-07
申请号:US17050770
申请日:2020-04-02
Applicant: ORBION SPACE TECHNOLOGY, INC.
Inventor: Jason D. Sommerville
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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