-
公开(公告)号：US12269618B2
公开(公告)日：2025-04-08
申请号：US17891968
申请日：2022-08-19
Inventor： Tyson Smith , John Akagi , Greg Droge
IPC: B64G1/24
Abstract: For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.
-
公开(公告)号：US20220348360A1
公开(公告)日：2022-11-03
申请号：US17691614
申请日：2022-03-10
Inventor： Tyson Smith , Zachary Lewis , Kurt Olsen , Marc Anthony Bulcher , Stephen Whitmore
Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.
-
公开(公告)号：US20230286673A1
公开(公告)日：2023-09-14
申请号：US17689038
申请日：2022-03-08
Inventor： Tyson Smith , John Akagi , Greg Droge
CPC classification number: B64G1/242 , G05B13/042 , B64G2001/247
Abstract: For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.
-
公开(公告)号：US11724829B2
公开(公告)日：2023-08-15
申请号：US17691614
申请日：2022-03-10
Inventor： Tyson Smith , Zachary Lewis , Kurt Olsen , Marc Anthony Bulcher , Stephen Whitmore
Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.
-
Patent Agency Ranking
公开(公告)号：US20220315252A1
公开(公告)日：2022-10-06
申请号：US17391843
申请日：2021-08-02
Inventor： Tyson Smith , Zachary Lewis , Kurt Olsen , Marc Anthony Bulcher , Stephen Whitmore
Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer.
-
公开(公告)号：US12129051B2
公开(公告)日：2024-10-29
申请号：US17689038
申请日：2022-03-08
Inventor： Tyson Smith , John Akagi , Greg Droge
CPC classification number: B64G1/242 , G05B13/042 , B64G1/247
Abstract: For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.
-
公开(公告)号：US20230286674A1
公开(公告)日：2023-09-14
申请号：US17891968
申请日：2022-08-19
Inventor： Tyson Smith , John Akagi , Greg Droge
IPC: B64G1/24
CPC classification number: B64G1/242
Abstract: For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.
-
公开(公告)号：US11407531B2
公开(公告)日：2022-08-09
申请号：US16945473
申请日：2020-07-31
Inventor： Tyson Smith , Zachary Lewis , Kurt Olsen , Marc Anthony Bulcher , Stephen Whitmore
Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.
-
公开(公告)号：US20210101702A1
公开(公告)日：2021-04-08
申请号：US16945473
申请日：2020-07-31
Inventor： Tyson Smith , Zachary Lewis , Kurt Olsen , Anthony Marc Bulcher , Stephen Whitmore
IPC: B64G1/40
Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.018 seconds)
