公开(公告)号：US11644057B2

公开(公告)日：2023-05-09

申请号：US16852852

申请日：2020-04-20

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： Scott G. Sabo

IPC: F16B21/16 ,  F16B21/02 ,  B64G1/22

CPC classification number: F16B21/165 ,  B64G1/222 ,  F16B21/02 ,  Y10T403/592

Abstract: A release mechanism for releasably securing a releasable structure to a stationary structure, where the mechanism employs release balls that can re-secure the releasable structure to the stationary structure. The release mechanism includes a base portion having three rails extending radially outward from a center of the base portion, and a rotatable portion rotatably mounted to the base portion, where the rotatable portion has a cam indentation. The release balls are positioned between the base portion and the rotatable portion so that one of the release balls is ridable on each of the rails and all of the release balls are positioned within the cam indentation. The cam indentation is configured so that as the rotatable portion is rotated relative to the base portion the cam indentation causes and allows the release balls to move along the rails in unison with each other to hold and release the releasable structure.

公开(公告)号：US11643930B2

公开(公告)日：2023-05-09

申请号：US17645671

申请日：2021-12-22

Applicant: Trans Astronautica Corporation

Inventor： Joel C. Sercel

IPC: E21C51/00 ,  B64G1/22 ,  F24S20/50 ,  F24S23/79 ,  F24S23/71 ,  B64G1/24 ,  B64G1/40 ,  B64G1/64 ,  B64G1/10 ,  F03H99/00 ,  B64G99/00 ,  F24S23/00 ,  F24S23/70 ,  B64G1/44

CPC classification number: E21C51/00 ,  B64G1/22 ,  B64G1/1078 ,  B64G1/242 ,  B64G1/40 ,  B64G1/402 ,  B64G1/446 ,  B64G1/646 ,  B64G99/00 ,  B64G2001/224 ,  F03H99/00 ,  F24S20/50 ,  F24S23/12 ,  F24S23/70 ,  F24S23/71 ,  F24S23/715 ,  F24S23/79 ,  Y02E10/40

Abstract: A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

公开(公告)号：US20230131485A1

公开(公告)日：2023-04-27

申请号：US17045338

申请日：2019-11-29

Applicant: SPACETY CO., LTD. (CHANGSHA)

Inventor： Xiaoming LI ,  Zhanhui WANG ,  Yu ZOU ,  Weijia REN

IPC: B64G1/24 ,  B64G1/22

Abstract: A deorbit-sail deployment device for forming a deorbit sail that drives a satellite to deorbit is disclosed. The deorbit-sail deployment device comprises a non-folding sail and a folding sail that are rotatably connected to each other to form the deorbit sail The folding sail comprises at least one first skeleton that folds the sail body in the folded state and supports the sail body in the unfolded state. The folding sail can be folded to a compact size before launch.

公开(公告)号：US11591116B2

公开(公告)日：2023-02-28

申请号：US17024064

申请日：2020-09-17

Applicant: THALES

Inventor： Yannick Baudasse ,  Stéphane Vezain

IPC: B64G1/22 ,  B65H16/06

Abstract: A deployable device includes a supporting structure, a mandrel able to move in rotation with respect to the supporting structure about a first axis Z, a membrane able to pass from a rolled-up configuration rolled up around the mandrel about the first axis Z to a deployed configuration deployed along a second axis X substantially perpendicular to the first axis Z. The device comprises two fittings secured to the mandrel at their centre, arranged one on either side of the membrane and comprising first stubs on their periphery, a casing extending between the two fittings, the casing comprising second stubs of a shape complementing the shape of the first stubs, the casing being able to pass from a rolled-up configuration at least partially enveloping the membrane in the rolled-up configuration to a deployed configuration at least partially superposed on the membrane in the deployed configuration.

公开(公告)号：US20230042339A1

公开(公告)日：2023-02-09

申请号：US17791344

申请日：2021-01-13

Applicant: Airbus Defence and Space Limited

Inventor： Elie Allouis ,  Alexander Hall ,  John Carroll

IPC: B64G1/64 ,  B64G4/00 ,  B64G1/22

Abstract: The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus comprises: a core platform (7); and a mobile platform (4) comprising an end effector configured to perform an assembly or manufacturing task. The mobile platform (4) is connected to the core platform (7) by a tether (6a). The core platform comprises a body and a coupling element (15a) connected to and extendable from the body (7) such that the coupling element (15a) may be spaced from the body of the core platform (7). The tether (6a) connects the mobile platform (4) to the body (7) via the coupling element (15a). The assembly apparatus further comprises an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.

公开(公告)号：US11572918B2

公开(公告)日：2023-02-07

申请号：US16166864

申请日：2018-10-22

Applicant: CSEM Centre Suisse d'Electronique et de Microtechnique SA - Recherche et Developpement

Inventor： Florent Cosandier ,  Philippe Schwab ,  Lionel Kiener

IPC: F16C11/12 ,  B64G1/22 ,  G12B5/00 ,  B64G1/66 ,  G04B17/04 ,  F16D3/00 ,  G01C19/22

Abstract: A pivot mechanism for guiding in rotation comprises a mobile element connected to a fixed element through flexible connections; with the flexible elements being configured to guide the mobile element according to a rotational movement in a plane, around a pivoting axis perpendicular to the plane; with each of the flexible connections comprising an intermediary junction provided with an expansion slot, the expansion slot being configured to expand during the rotation of the mobile element, so that the mobile element can pivot according to a second angular amplitude that is greater than a first angular amplitude achieved without said expansion slot; with the intermediary junctions being connected to one another by a coupling member; each of the coupling members being configured so as to prevent a movement out of the plane and a lateral movement in the plane of the mobile element. The pivot mechanism has a very high rotational amplitude.

公开(公告)号：US11518488B2

公开(公告)日：2022-12-06

申请号：US16579999

申请日：2019-09-24

Applicant: Airbus Operations GmbH

Inventor： Hermann Benthien ,  Axel Soeffker

IPC: F16L9/04 ,  B64C1/00 ,  B64G1/22 ,  B32B1/08 ,  B32B5/12 ,  B64C1/06 ,  F16L57/00

Abstract: A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

公开(公告)号：US20220371753A1

公开(公告)日：2022-11-24

申请号：US17735506

申请日：2022-05-03

Applicant: Trevor Brown

Inventor： Trevor Brown

IPC: B64G1/44 ,  H01L25/16 ,  H01Q3/34 ,  B64G1/22

Abstract: An apparatus comprises both a first side and a second side that is opposite the first side. The apparatus includes a plurality of photovoltaic cells disposed on the first side of the substrate and a plurality of microwave antennas disposed on both the first side of the substrate and the second side of the substrate. In addition, the apparatus comprises at least one photonic integrated circuit operably coupled to the substrate and to at least one of the plurality of photovoltaic cells to thereby receive electrical power therefrom. By one approach, the apparatus can further comprise at least one atomic clock supported by the substrate. By one approach, at least some of the aforementioned plurality of microwave antennas that are disposed on the first side of the substrate can comprise an optically transparent portion that serves as both a protective cover and a focusing lens.

公开(公告)号：US11485874B2

公开(公告)日：2022-11-01

申请号：US16454515

申请日：2019-06-27

Applicant: PRC-DeSoto International, Inc.

Inventor： Christopher A. Dacko ,  Michael A. Mayo ,  Gregory J. McCollum

IPC: C09D133/14 ,  C08F220/36 ,  C08L33/14 ,  C09D5/24 ,  C25D13/04 ,  C25D13/12 ,  C08F30/02 ,  C08F230/02 ,  C08L43/02 ,  C09D143/02 ,  B64F5/00 ,  B64G1/22 ,  C08F222/10 ,  C08F220/34

Abstract: The present invention is directed to an addition polymer comprising an addition polymer backbone; at least one moiety comprising a phosphorous acid group, the moiety being covalently bonded to the addition polymer backbone by a carbon-carbon bond; and at least one carbamate functional group. The present invention is also directed towards methods of making the addition polymer, aqueous resinous dispersions and electrodepositable coating compositions comprising the addition polymer, methods of coating a substrate and coated substrates.

公开(公告)号：US11465780B2

公开(公告)日：2022-10-11

申请号：US16970963

申请日：2019-02-13

Applicant: MAZAROM IMPEX S.R.L.

Inventor： Adrian Totu

IPC: B64G1/10 ,  B64G1/22 ,  B64G1/44 ,  B64G1/64

Abstract: Artificial satellite “Card-Sat” comprising a frame (1), an upper cover (2) and a lower cover (3), both covers (2, 3) being fixed to the frame (1), the frame (1), the upper cover (2) and the lower cover (3) defining a substantially paralelepipedic chamber (5), the satellite further comprising solar cells (6) fixed to the outer surface, in respect to the chamber (5), of the upper cover (2) and of the lower cover (3), and an avionics system (7), integrated on the inner surface, in respect to the chamber (5), of at least one of the upper cover (2) or the lower cover (3).