公开(公告)号：US12078154B1

公开(公告)日：2024-09-03

申请号：US16153297

申请日：2018-10-05

Applicant: Board of Trustees of The University of Alabama, for and on behalf of The University of Alabama in Huntsville

Inventor： Kunning Gabriel Xu ,  Ryan Patrick Gott

IPC: F03H1/00 ,  B64G1/40 ,  H01J1/02

CPC classification number: F03H1/0087 ,  B64G1/405 ,  F03H1/0018 ,  H01J1/025

Abstract: The present disclosure generally pertains to devices and methods for generating thrust in vehicles, for instance in space applications. A heaterless, insertless hollow cathode utilizes AC and pulsed DC electric fields to ionize the propellant gas and generate a plasma plume. The cathode uses an argon microplasma generated in a quartz tube with a tungsten filament and brass ion collector. Free electrons are then drawn from the plasma plume and supplied to a thruster engine.

公开(公告)号：US11905936B2

公开(公告)日：2024-02-20

申请号：US17264893

申请日：2019-05-17

Applicant: ENPULSION GmbH

Inventor： Nembo Buldrini ,  Bernhard Seifert ,  Alexander Reissner

IPC: F03H1/00 ,  B64G1/40

CPC classification number: F03H1/005 ,  B64G1/402 ,  B64G1/405 ,  F03H1/0037

Abstract: The disclosed subject matter relates to an ion thruster for thrust vectored propulsion of a spacecraft, comprising a reservoir for a propellant, an emitter having a base and, on one side of the base, at least one outlet for emitting ions of the propellant, wherein the base is connected to the reservoir for providing flow of propellant from the reservoir to said at least one outlet, and an extractor facing said one side of the emitter for extracting and accelerating the ions from the emitter, wherein the extractor is split into sectors about an axis which orthogonally runs through said one side of the emitter, wherein said sectors are electrically insulated from one another.

公开(公告)号：US11708182B2

公开(公告)日：2023-07-25

申请号：US17007890

申请日：2020-08-31

Applicant: Massachusetts Institute of Technology

Inventor： Melissa Alyson Smith ,  Donna-Ruth Yost ,  Daniel Freeman ,  Noah Siegel ,  Paulo C. Lozano

IPC: B64G1/40 ,  F03H1/00 ,  H01J49/16

CPC classification number: B64G1/405 ,  F03H1/0012 ,  H01J49/165

Abstract: Electrospray devices and methods of fabricating electrospray devices are described.

公开(公告)号：US20230207175A1

公开(公告)日：2023-06-29

申请号：US18115723

申请日：2023-02-28

Applicant: Smokey Hawk Solitons, LLC

Inventor： Thomas Hunt Hawkins ,  David Hawkins

IPC: H01F7/20 ,  B64G1/40 ,  H01F7/02

CPC classification number: H01F7/202 ,  B64G1/405 ,  H01F7/0273

Abstract: This application describes creating, modifying, and bending electromagnetic solitons at large scales for the various applications. An electromagnetic soliton generator system controls the magnetic soliton such that the orientation, rotation rate, pitch angle, and magnetic field strength of the solitons are modified to provide the described standing waves and generate a magnetic flux differential.

公开(公告)号：US11649809B2

公开(公告)日：2023-05-16

申请号：US17119039

申请日：2020-12-11

Applicant: Airbus Defence and Space GmbH

Inventor： Franz Georg Hey ,  Nils Gerrit Kottke ,  Günter Kornfeld

IPC: F03H1/00 ,  H05H1/54 ,  B64G1/40

CPC classification number: F03H1/0043 ,  H05H1/54 ,  B64G1/405

Abstract: A neutralizer suitable for use in an ion engine comprises a halogen gas source and an electrode tube comprising an inlet opening connected to the halogen gas source for supplying a halogen gas provided by the halogen gas source into the electrode tube, a discharge space for generating a plasma from the halogen gas supplied into the electrode tube, and an outlet opening for discharging the plasma generated in the discharge space and free electrons from the electrode tube. An electron emitter is arranged in the discharge space of the electrode tube, which is at least partially made of tungsten, a tungsten alloy or a tungsten composite material containing at least one of iridium, rhenium, ruthenium, rhodium and osmium.

公开(公告)号：US20190248515A1

公开(公告)日：2019-08-15

申请号：US16324539

申请日：2017-08-08

Applicant: ispace, inc.

Inventor： Takeshi HAKAMADA ,  Takahiro NAKAMURA ,  Toshiki TANAKA ,  Daisuke FURUTOMO ,  John WALKER ,  Mohamed RAGAB ,  Daishi MATSUKURA ,  Abdelkader HAOUCHINE ,  Damien HAIKAL ,  Chit Hong YAM ,  Julian Jakub GRAMATYKA

IPC: B64G1/00 ,  B64G1/40

CPC classification number: B64G1/007 ,  B64G1/14 ,  B64G1/242 ,  B64G1/40 ,  B64G1/402 ,  B64G1/405 ,  B64G1/443

Abstract: A first step of propelling a transport ship from a low earth orbit or a geostationary transfer orbit to a targeted orbit or a destination with electric propulsion is provided.

公开(公告)号：US20180290768A1

公开(公告)日：2018-10-11

申请号：US15764667

申请日：2016-09-29

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Frédéric FAYE ,  Eric BEAUFUME ,  Jacques COTTIER

IPC: B64G1/10 ,  B64G1/64 ,  B64G1/40 ,  G02B23/02 ,  G02B23/16

CPC classification number: B64G1/1021 ,  B64G1/10 ,  B64G1/402 ,  B64G1/405 ,  B64G1/641 ,  B64G2001/1028 ,  G02B23/02 ,  G02B23/16

Abstract: Disclosed is a satellite which includes: at least one optical photography instrument including a main lens having an optical axis and the optical instrument having a field of view; at least one launcher interface system, intended for being removably secured to a satellite interface system of a launcher of the satellite; a linking device between the launcher interface and the optical instrument extending substantially parallel to the optical axis of the main lens between an upper end and a lower end; the launcher interface system is connected to the linking device by the lower end and the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launcher interface system being outside the field of view of the instrument.

公开(公告)号：US20180273215A1

公开(公告)日：2018-09-27

申请号：US15470592

申请日：2017-03-27

Applicant: Space Systems/Loral, LLC

Inventor： Cameron Ground ,  Gordon Wu ,  Derek Chan

IPC: B64G1/50 ,  B64G1/26 ,  B64G1/40 ,  B64G1/58 ,  F24F13/02

CPC classification number: B64G1/506 ,  B64G1/26 ,  B64G1/40 ,  B64G1/405 ,  B64G1/503 ,  B64G1/58 ,  F24F13/02

Abstract: A spacecraft includes a spacecraft main body, including payload equipment disposed on an inner panel surface of at least one radiator panel, the at least one radiator panel having an exterior-facing outer panel surface. The spacecraft includes at least one electric thruster disposed proximate to an aft facing panel of the spacecraft main body. The at least one electric thruster is thermally coupled with the at least one radiator panel by way of a thermally conductive path.

公开(公告)号：US20180201395A1

公开(公告)日：2018-07-19

申请号：US14800436

申请日：2015-07-15

Applicant: California Institute of Technology

Inventor： Cecile Jung-Kubiak ,  Colleen M. Marrese-Reading ,  Victor E. White ,  Daniel W. Wilson ,  Matthew R. Dickie ,  Karl Y. Yee ,  Richard E. Muller ,  James E. Polk ,  John R. Anderson ,  Nima Rouhi ,  Frank Greer

IPC: B64G1/40

CPC classification number: B64G1/405

Abstract: Micro-emitter arrays and methods of microfabricating such emitter arrays are provided. The microfabricated emitter arrays incorporate a plurality of emitters with heights greater than 280 microns with uniformity of +/−10 microns arranged on a supporting silicon substrate, each emitter comprising an elongated body extending from the top surface of the substrate and incorporating at least one emitter tip on the distal end of the elongated body thereof. The emitters may be disposed on the substrate in an ordered array in an X by Y grid pattern, wherein X and Y can be any number greater than zero. The micro-emitter arrays may utilize a LMIS propellant source including, for example, gallium, indium, bismuth, or tin. The substrate may incorporate at least one through-via providing a fluid pathway for the LMIS propellant to flow from a propellant reservoir beneath the substrate to the top substrate surface whereupon the micro-emitter array is disposed.

公开(公告)号：US09980361B2

公开(公告)日：2018-05-22

申请号：US15625898

申请日：2017-06-16

Applicant: The United States of America, as represented by the Secretary of the Navy

Inventor： Michael S. McDonald

IPC: F03H1/00 ,  H05H1/24 ,  B64G1/40

CPC classification number: H05H1/24 ,  B64G1/405 ,  F03H1/0006 ,  F03H1/0075 ,  H01J37/32596 ,  H05H1/20

Abstract: Embodiments relate to a hallow cathode with integral layers of radiation shielding. The hollow cathode includes an inner cathode tube that forms a gas feed to direct gas toward a downstream end, where the directed gas forms plasma. A heater element is positioned at the downstream end of the inner cathode tube, the heater element to heat the plasma. The hollow cathode further includes an outer cathode tube with a keeper electrode to sustain a bias voltage across a gap at a downstream end of the outer cathode tube for igniting the plasma. The integral layers of radiation shielding are connected by offset radial supports and are incorporated as a single element with either the inner or outer cathode tube, where the integral layers are nested with torturous conductive paths to reduce radiation and conduction losses from the downstream end of the inner cathode tube.