公开(公告)号：US20220348360A1

公开(公告)日：2022-11-03

申请号：US17691614

申请日：2022-03-10

Applicant: Utah State University Space Dynamics Laboratory

Inventor： Tyson Smith ,  Zachary Lewis ,  Kurt Olsen ,  Marc Anthony Bulcher ,  Stephen Whitmore

IPC: B64G1/40 ,  F02K9/72

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：US11724829B2

公开(公告)日：2023-08-15

申请号：US17691614

申请日：2022-03-10

Applicant: Utah State University Space Dynamics Laboratory

Inventor： Tyson Smith ,  Zachary Lewis ,  Kurt Olsen ,  Marc Anthony Bulcher ,  Stephen Whitmore

IPC: B64G1/40 ,  F02K9/72

CPC classification number: B64G1/404 ,  F02K9/72

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：US20220315252A1

公开(公告)日：2022-10-06

申请号：US17391843

申请日：2021-08-02

Applicant: Utah State University Space Dynamics Laboratory

Inventor： Tyson Smith ,  Zachary Lewis ,  Kurt Olsen ,  Marc Anthony Bulcher ,  Stephen Whitmore

IPC: B64G1/40 ,  B64G1/10 ,  F02K9/95 ,  F02K9/34

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：US11407531B2

公开(公告)日：2022-08-09

申请号：US16945473

申请日：2020-07-31

Applicant: Utah State University Space Dynamics Laboratory

Inventor： Tyson Smith ,  Zachary Lewis ,  Kurt Olsen ,  Marc Anthony Bulcher ,  Stephen Whitmore

IPC: B64G1/40 ,  F02K9/72

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

Applicant: Utah State University Space Dynamics Laboratory

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.