公开(公告)号：US12116148B2

公开(公告)日：2024-10-15

申请号：US17731030

申请日：2022-04-27

Applicant: Orbit Fab, Inc.

Inventor： Daniel Faber

IPC: B64G1/10 ,  B64G1/24 ,  B64G1/64

CPC classification number: B64G1/1078 ,  B64G1/2427 ,  B64G1/641 ,  B64G1/646

Abstract: Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

公开(公告)号：US12030674B2

公开(公告)日：2024-07-09

申请号：US17194277

申请日：2021-03-07

Applicant: Altius Space Machines Inc.

Inventor： Geoffrey Thomas Licciardello ,  Jonathan Andrew Goff ,  Calvin James Murphy

IPC: B64G1/64

CPC classification number: B64G1/641

Abstract: A fluid transfer interface is provided. The fluid transfer interface includes one or more of first and second interface portions. The first interface portion includes a first portion of a fluid connector and one or more ferromagnetic surfaces. The second interface portion includes an extendable second portion of the fluid connector and one or more electropermanent magnets, laterally disposed around the second portion of the fluid connector, configured to be magnetized or demagnetized in unison. The one or more electropermanent magnets are further configured to provide attraction force to the one or more ferromagnetic surfaces when magnetized and couple the first interface portion to the second interface portion and provide no attraction force to the one or more ferromagnetic surfaces when demagnetized and allow the first interface portion to be decoupled from the second interface portion.

公开(公告)号：US11981458B2

公开(公告)日：2024-05-14

申请号：US17631193

申请日：2019-11-07

Applicant: EXOLAUNCH GmbH

Inventor： Peter Schwarz ,  Johannes Gruber ,  Peter Wimmer

IPC: B64G1/64

CPC classification number: B64G1/641 ,  B64G1/645

Abstract: The invention relates to a separation system that dispenses a satellite from a launch vehicle along a dispensing axis, with a first ring for mounting to the launch vehicle and a second ring for mounting to the satellite and a deployment means exerting a separating force on the first and the second ring.

公开(公告)号：US20240132234A1

公开(公告)日：2024-04-25

申请号：US18547501

申请日：2021-02-25

Applicant: AIRBUS DEFENCE AND SPACE S.A.

Inventor： Fernando José CESPEDOSA CASTÁN ,  José Luis MORA PLAZA

IPC: B64G1/64

CPC classification number: B64G1/641 ,  B64G1/645

Abstract: A retaining and releasing device for spaceships retains and releases a body to/from a support structure. A releasing bolt keeps the releasable body and the support structure connected in a position for locking the retaining and releasing device. A locking device for locking the releasing bolt in the support structure has a case and a segmented ring. The case is movable axially relative to the releasing bolt and includes an end with a through-slot. A releasing system includes an actuator, a rod having the same orientation as the releasing bolt, with a locking pin, cooperating with the slot, and a compression spring. The actuator locks the rod in a position for locking the retaining and releasing device. The compression spring is in contact with the case of the locking device and disposed around the rod to rotate the rod. The device includes a system for removing the releasing bolt.

公开(公告)号：US11955715B2

公开(公告)日：2024-04-09

申请号：US17742022

申请日：2022-05-11

Applicant: Blue Digs LLC

Inventor： Chris Cosner ,  Ying Feria ,  Raenaurd Turpin ,  Andre Houle ,  Richard Aston ,  Brett Cope ,  Ricardo Leon

IPC: H01Q21/00 ,  B64G1/64 ,  H01Q1/28 ,  H01Q5/42 ,  H01Q5/50 ,  H01Q1/08 ,  H04B7/185

CPC classification number: H01Q21/0018 ,  B64G1/641 ,  H01Q1/288 ,  H01Q5/42 ,  H01Q5/50 ,  B64G1/643 ,  H01Q1/08 ,  H04B7/18513 ,  H04B7/18515

Abstract: A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

公开(公告)号：US11932425B2

公开(公告)日：2024-03-19

申请号：US16902865

申请日：2020-06-16

Applicant: Xtenti, LLC

Inventor： Daniel Lim ,  Jason Armstrong ,  Robert Spicer

IPC: B64G1/64 ,  B64G1/00 ,  B64G1/22

CPC classification number: B64G1/641 ,  B64G1/002 ,  B64G1/223 ,  B64G1/643

Abstract: The disclosure provides a configurable-mass rideshare dispenser for a rideshare adapter employable with a LV. In one example, the configurable-mass rideshare dispenser includes: (1) a modular chassis having a plurality of walls, wherein each of the plurality of walls includes multiple internal mounts operable to mount at multiple candidate locations a rideshare payload, its associated attachment/deployment mechanisms, signal processing circuitry, and at least one additional mass object, and (2) at least one door coupled to at least one of the plurality of walls, wherein the signal processing circuitry is operable to provide deployment sequencing that operates the at least one door.

公开(公告)号：US11878819B2

公开(公告)日：2024-01-23

申请号：US17553628

申请日：2021-12-16

Applicant: The Boeing Company

Inventor： Richard W. Aston ,  Emily Colleen Woods ,  Rachel Elizabeth Zilz ,  Michael John Langmack ,  Nicole Marie Hastings

IPC: B64G1/58 ,  B64G1/00 ,  B64G1/64

CPC classification number: B64G1/58 ,  B64G1/002 ,  B64G1/641

Abstract: A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

公开(公告)号：US20230382566A1

公开(公告)日：2023-11-30

申请号：US18165567

申请日：2023-02-07

Applicant: NanoRacks, LLC

Inventor： Michael David JOHNSON ,  Mark David ROWLEY ,  Michael Desmond LEWIS ,  J. Brockton HOWE

IPC: B64G1/64 ,  B64G1/52

CPC classification number: B64G1/641 ,  B64G1/52 ,  B64G1/646 ,  B64G1/14

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

公开(公告)号：US20230348116A1

公开(公告)日：2023-11-02

申请号：US18218545

申请日：2023-07-05

Applicant: OMNITEQ, LLC

Inventor： Michael David Johnson

IPC: B64G1/64

CPC classification number: B64G1/641 ,  B64G1/645 ,  B64G2001/643

Abstract: The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

公开(公告)号：US11701735B2

公开(公告)日：2023-07-18

申请号：US17568393

申请日：2022-01-04

Applicant: Nanchang Hangkong University

Inventor： Yuhua Chen ,  Jinyang Hu ,  Timing Zhang ,  Jilin Xie ,  Limeng Yin ,  Shanlin Wang ,  Yongde Huang ,  Mingwei Wei ,  Wentao Zhang

IPC: H05B6/10 ,  H05B6/62 ,  B23K13/02 ,  B64G1/64 ,  B23K101/00

CPC classification number: B23K13/02 ,  B64G1/641 ,  B23K2101/006

Abstract: An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.