公开(公告)号：US20240344163A1

公开(公告)日：2024-10-17

申请号：US18753762

申请日：2024-06-25

申请人： Relativity Space, Inc.

发明人： Jordan Noone ,  Timothy A. Ellis ,  John Rising

IPC分类号： C21D9/00 ,  B23K15/00 ,  B23K15/02 ,  B23K26/342 ,  B23K26/70 ,  B28B1/00 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64G1/00 ,  B64G1/22 ,  C21D1/30 ,  C21D1/60 ,  C21D1/613 ,  C21D7/06

CPC分类号： C21D9/0068 ,  B23K15/0026 ,  B23K15/0086 ,  B23K15/02 ,  B23K26/342 ,  B23K26/702 ,  B28B1/001 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64G1/002 ,  B64G1/22 ,  C21D1/30 ,  C21D1/60 ,  C21D1/613 ,  C21D7/06

摘要： Systems and methods for additive layer manufacturing of metallic components, such as rocket engines and propellant supply systems, are provided. Methods include melting the surface of a work piece to form a weld pool; adding wire to the weld pool and moving a heat source relative to the work piece to progressively form a new layer of metallic material on the work piece; cooling the formed layer; stress relieving (e.g., peening) the cooled layer; applying a secondary operations either sequentially or simultaneously; and repeating the above steps as required to form components layer by layer. Systems and methods of supplying a first propellant to the rocket engine of a launch vehicle are also provided, where the first propellant is supplied through a heat exchanger for generating mechanical energy to pump the first propellant into the rocket engine, and electrical energy to pump a second propellant into the rocket engine.

公开(公告)号：US20240246702A1

公开(公告)日：2024-07-25

申请号：US18418105

申请日：2024-01-19

申请人： Stardust Holdings, LLC d/b/a/ XTERRA Space

发明人： Alex Amelia Kuehn ,  Tyler Gerald Holden

IPC分类号： B64G1/66 ,  B64G1/00 ,  B64G1/10 ,  B64G1/22

CPC分类号： B64G1/66 ,  B64G1/005 ,  B64G1/10 ,  B64G1/223

摘要： This disclosure relates generally to a modular CubeSat dispenser with novel features that enable universal compatibility within a single CubeSat dispenser system. The apparatus of the invention is particularly useful for 10 CubeSat dispensers and other standardized deployment devices.

公开(公告)号：US12027911B2

公开(公告)日：2024-07-02

申请号：US17695763

申请日：2022-03-15

申请人： The Aerospace Corporation

发明人： Colin J. Mann ,  Don Walker

IPC分类号： H02J7/35 ,  B64G1/10 ,  B64G1/42 ,  B64G1/44 ,  H01L31/02 ,  H01L31/0475 ,  H01M10/42 ,  H01M10/615 ,  B64G1/22

CPC分类号： H02J7/35 ,  B64G1/10 ,  B64G1/425 ,  B64G1/428 ,  B64G1/443 ,  H01L31/02008 ,  H01L31/0475 ,  H01M10/425 ,  H01M10/615 ,  B64G1/223 ,  H01M2010/4271 ,  H01M2220/20

摘要： Embodiments of the present invention include modular solar power cells, arrays, and power management systems for use in satellite systems and constellations. In one embodiment, a solar cell module can include: a module substrate including a high-emissivity side and a mounting side; a power management circuit mounted to the mounting side of the module substrate; a battery arranged adjacent to the power management circuit; a solar cell substrate arranged adjacent the battery and including an embedded battery heater; and a solar cell mounted directly to the solar cell substrate and connected to the battery.

公开(公告)号：US20240199240A1

公开(公告)日：2024-06-20

申请号：US18415398

申请日：2024-01-17

申请人： Space Exploration Technologies Corp.

发明人： Andrew C. Thompson ,  Patrick Sodt ,  Thomas Tarlton ,  Robert S. Tarlton ,  Solomon Westerman ,  Michael Dergance

IPC分类号： B64G1/64 ,  B64G1/22 ,  B64G1/24 ,  B64G1/40

CPC分类号： B64G1/645 ,  B64G1/2427 ,  B64G1/641 ,  B64G1/223 ,  B64G1/226 ,  B64G1/40 ,  B64G1/643

摘要： A method of deploying a plurality of spacecraft includes coupling the plurality of spacecraft in a stack to a payload adaptor, the stack extending along a longitudinal axis; launching the payload adaptor into an orbit; and decoupling an entirety of the stack from the payload adaptor after the payload adaptor reaches the orbit.

公开(公告)号：US20240056019A1

公开(公告)日：2024-02-15

申请号：US17754201

申请日：2021-12-16

申请人： LIG NEX1 Co., LTD. ,  Industry-Academic Cooperation Foundation, Chosun University

发明人： Sung Woo PARK ,  Soo Jin KANG ,  Jong Pil KIM ,  Hyun Ung OH

IPC分类号： H02S30/20 ,  H02S10/40 ,  F16F15/02 ,  B64G1/10 ,  B64G1/22 ,  B64G1/44

CPC分类号： H02S30/20 ,  H02S10/40 ,  F16F15/02 ,  B64G1/10 ,  B64G1/2222 ,  B64G1/443

摘要： An exemplary embodiment of the present invention provides a deployable solar panel mounted on a movable body configured to be movable, the deployable solar panel including: a solar panel mounted on an outer portion of the movable body and configured to convert light energy into electrical energy; and a yoke having a reinforcing part stacked on at least one surface of a base to connect the movable body and the solar panel and configured to attenuate vibration transmitted to the solar panel.

公开(公告)号：US11884424B2

公开(公告)日：2024-01-30

申请号：US16966722

申请日：2018-12-27

申请人： NEC CORPORATION

发明人： Taichi Hirose ,  Naoyuki Kaneko

IPC分类号： H02S20/30 ,  H02S30/20 ,  B64G1/22 ,  H02S30/00

CPC分类号： B64G1/222 ,  H02S20/30 ,  H02S30/00 ,  H02S30/20

摘要： A panel deployment apparatus includes a guide provided on a first hinge axis of a main hinge; a guide provided on a second hinge axis of a side hinge; and a deployment stop arm that stops deployment of a second side panel by sequential engagement with the guide and the guide, the deployment stop arm being fixed to the second side panel, wherein the second main panel is deployed in a state of the deployment stop arm being engaged with the guide and, when the deployment stop arm is disengaged from the guide and then engaged with the guide, the first side panel is deployed in a state of the deployment stop arm being engaged with the guide and, when the deployment stop arm is disengaged from the guide, the second side panel is deployed.

公开(公告)号：US11878820B1

公开(公告)日：2024-01-23

申请号：US16870974

申请日：2020-05-10

申请人： Space Exploration Technologies Corp.

发明人： Andrew C. Thompson ,  Patrick Sodt ,  Thomas Tarlton ,  Robert S. Tarlton ,  Solomon Westerman ,  Michael Dergance

IPC分类号： B64G1/64 ,  B64G1/24 ,  B64G1/40 ,  B64G1/22

CPC分类号： B64G1/645 ,  B64G1/2427 ,  B64G1/641 ,  B64G1/223 ,  B64G1/226 ,  B64G1/40 ,  B64G1/643

摘要： A method of releasing spacecraft from a rocket includes arranging spacecraft in a stack on a rocket, launching the rocket until it attains orbital velocity, imposing a flat spin on the rocket, and releasing the entire stack from the rocket during the flat spin. In one aspect, the method includes applying a compressive load along a length of the stack, launching the rocket until it attains orbital velocity, imposing a flat spin on the rocket, and releasing the compressive load to allow the entire stack to separate from the rocket during the flat spin.

公开(公告)号：US11874061B2

公开(公告)日：2024-01-16

申请号：US17936199

申请日：2022-09-28

申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION

发明人： Howard S. Eller

IPC分类号： B64G1/22 ,  B64G4/00 ,  F27B14/10 ,  F27B14/06 ,  F27B14/14 ,  B33Y30/00 ,  B33Y70/00 ,  B33Y80/00 ,  B22F3/00 ,  B22F5/00 ,  B22F12/00 ,  B22F12/44 ,  B29L31/30

CPC分类号： F27B14/10 ,  B22F3/003 ,  B22F5/00 ,  B22F12/226 ,  B22F12/44 ,  B64G1/22 ,  B64G4/00 ,  F27B14/06 ,  F27B14/14 ,  B22F2202/09 ,  B29L2031/3097 ,  B33Y30/00

摘要： A system and method for manufacturing a space-based component in space. The method includes collecting and capturing space debris directly from and suspended in space, heating the collected space debris using solar radiation in a manner that separately and independently melts different constituent elements and compounds in the space debris, collecting the different constituent elements and compounds as they are being separately melted, storing the elements and compounds in a molten, solid or vapor form, and fabricating the space-based component using the stored elements and compounds.

公开(公告)号：US11858665B1

公开(公告)日：2024-01-02

申请号：US16817286

申请日：2020-03-12

申请人： Maxar Space LLC

发明人： Jillian Gorsuch ,  Gregory Dudder

IPC分类号： B64G1/22

CPC分类号： B64G1/222 ,  Y10T403/342 ,  Y10T403/459

摘要： An apparatus includes an integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring. In a spacecraft application, a spacecraft appendage may be coupled with a deployment mechanism, the deployment mechanism including at least one integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring.

公开(公告)号：US20230406543A1

公开(公告)日：2023-12-21

申请号：US18350925

申请日：2023-07-12

申请人： M.M.A. DESIGN, LLC

发明人： Lyn Eric Ruhl ,  Mitchell Todd Wiens

IPC分类号： B64G1/22 ,  B64G1/64

CPC分类号： B64G1/222 ,  B64G1/64 ,  B64G1/443

摘要： An example system for extraterrestrial deployment of a flexible membrane surface includes a flexible membrane having a periphery and an interior. The flexible membrane is rolled about a roll axis into a cylindrical geometric shape in an undeployed state. A payload base has extendable radial booms, wherein the distal end of each extendable radial boom is attached to the periphery of the flexible membrane and the interior of the flexible membrane is free of attachment to the extendable radial booms. The payload base and the extendable radial booms are positioned to one side of the flexible membrane along the roll axis. The extendable radial booms are configured to extend orthogonally to the roll axis from the payload base to unroll the flexible membrane about the roll axis to form the flexible membrane surface in a deployed state, wherein the roll axis is substantially orthogonal to the flexible membrane surface.