公开(公告)号：US10910198B2

公开(公告)日：2021-02-02

申请号：US16773908

申请日：2020-01-27

Applicant: MOMENTUS INC.

Inventor： Jason Hummelt ,  Joel Sercel ,  Philip Mainwaring ,  James Small ,  Matthew Parman

IPC: F03H1/00 ,  B64G1/40 ,  H01J37/32

Abstract: A thruster system for use in a spacecraft includes a microwave source, a resonant cavity coupled to the microwave source, wherein the microwave source is configured to generate a standing wave field in the resonant cavity, a nozzle provided at one end of the resonant cavity; and at least one injector configured to inject propellant into the resonant cavity so as to create a rotating circumferential flow. The standing wave field raises a temperature of the injected propellant to provide thrust by way of a hot gas exiting the resonant cavity via the nozzle.

公开(公告)号：US11352150B2

公开(公告)日：2022-06-07

申请号：US16773920

申请日：2020-01-27

Applicant: MOMENTUS INC.

Inventor： Matthew Parman ,  Joel Sercel ,  Mikhail Kokorich ,  James Small ,  Nicholas Simon ,  Nathan Orr ,  Samuel Avery ,  Scott Stanley

IPC: B64G1/40 ,  B64G1/54

Abstract: A spacecraft structure for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

公开(公告)号：US20200294772A1

公开(公告)日：2020-09-17

申请号：US16773908

申请日：2020-01-27

Applicant: MOMENTUS INC.

Inventor： Jason Hummelt ,  Joel Sercel ,  Philip Mainwaring ,  James Small ,  Matthew Parman

IPC: H01J37/32 ,  B64G1/40 ,  F03H1/00

Abstract: A thruster system for use in a spacecraft includes a microwave source, a resonant cavity coupled to the microwave source, wherein the microwave source is configured to generate a standing wave field in the resonant cavity, a nozzle provided at one end of the resonant cavity; and at least one injector configured to inject propellant into the resonant cavity so as to create a rotating circumferential flow. The standing wave field raises a temperature of the injected propellant to provide thrust by way of a hot gas exiting the resonant cavity via the nozzle.

公开(公告)号：US20200290755A1

公开(公告)日：2020-09-17

申请号：US16773920

申请日：2020-01-27

Applicant: MOMENTUS INC.

Inventor： Matthew Parman ,  Joel Sercel ,  Mikhail Kokorich ,  James Small ,  Nicholas Simon ,  Nathan Orr ,  Samuel Avery ,  Scott Stanley

IPC: B64G1/40 ,  B64G1/54

Abstract: A method in a spacecraft for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

公开(公告)号：US20210183624A1

公开(公告)日：2021-06-17

申请号：US17163537

申请日：2021-01-31

Applicant: MOMENTUS INC.

Inventor： Jason Hummelt ,  Joel Sercel ,  Philip Mainwaring ,  James Small ,  Matthew Parman

IPC: H01J37/32 ,  F03H1/00 ,  B64G1/40

Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.