公开(公告)号：US11377237B1

公开(公告)日：2022-07-05

申请号：US16400383

申请日：2019-05-01

Applicant: United Launch Alliance, L.L.C.

Inventor： Eric W. Monda ,  Bernard F. Kutter

IPC: B64G1/64 ,  B64G1/00

Abstract: A method of achieving orbital rendezvous with a target satellite includes launching a spacecraft with a launch vehicle at an optimal time; steering the launch vehicle out-of-plane based on the orbital elements of the target satellite's orbit; and entering a predetermined rendezvous envelope of the target satellite before the target satellite completes one complete orbit from the target satellite's position at the optimal time.

公开(公告)号：US20220172393A1

公开(公告)日：2022-06-02

申请号：US17601264

申请日：2020-03-31

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Alexandre FALCOZ

IPC: G06T7/73 ,  G06T7/64 ,  G06V10/25 ,  G06V10/44 ,  G06V10/50 ,  B64G1/64

Abstract: A method for locating a target (C) relative to a vehicle (V), the target including at least one three-dimensional external component (Cs) presenting a quadratic surface, the method being implemented by a computer and including capturing an image of the target comprising an area of interest in which the external component of the target is visible in the form of an elliptical contour, for each of a plurality of pixels of the area of interest in the image, calculating an intensity gradient of the image around the pixel, and determining, based on the intensity gradient, the parameters of a line presenting a direction normal to the gradient at the pixel, selecting, among the set of determined lines, a set of lines that are tangents to the elliptical contour, and estimating the parameters of the elliptical contour on the image based on the parameters of the tangents to the elliptical contour.

公开(公告)号：US20220144456A1

公开(公告)日：2022-05-12

申请号：US17580727

申请日：2022-01-21

Applicant: Naval University of Engineering

Inventor： Weiming MA ,  Yuxing ZHANG ,  Mingyuan ZHANG ,  Xiangming ZHANG ,  Weichao LI ,  Xinlin LONG ,  Chen DENG

IPC: B64G1/00 ,  B64G1/64

Abstract: A space launch system and method through electromagnetic pushing. The space launch system comprises an energy storage subsystem, an energy conversion subsystem, a linear motor subsystem, and a control maintenance subsystem. The space launch system converts the electric energy into an electromagnetic force. Through the electromagnetic force, a rocket is pushed to be accelerated to a certain speed along an electromagnetic launching track to realize the launching of the rocket.

公开(公告)号：US20220106063A1

公开(公告)日：2022-04-07

申请号：US17493553

申请日：2021-10-04

Applicant: OMNITEQ, LLC

Inventor： Michael David Johnson

IPC: B64G1/64

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：US20220089301A1

公开(公告)日：2022-03-24

申请号：US17598959

申请日：2020-03-27

Applicant: Airbus Defence and Space Limited

Inventor： Juliet Gregory ,  James Sadler ,  William Bentall ,  Frederique Dupont De Denechin ,  Henri Bavestrello ,  Marc Manz ,  James Sheppard-Alden

IPC: B64G1/40 ,  B64G1/64 ,  F16L37/107

Abstract: The present disclosure relates to a coupling assembly for fluidly connecting first and second spacecraft. The first space-craft comprises a drive mechanism and the second spacecraft comprising a valve for filling and/or draining the second spacecraft. The coupling assembly comprises first and second connectors and a lock. The first connector comprises an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism such that the drive mechanism is operable to exert a torque on the coupling member to rotate the coupling member. The second connector comprises a stop portion and a bore for transferring fluid, the second connector configured to screw on to the valve until the stop portion engages the valve. In use, the lock is initially in a locked state wherein the coupling member is rotationally fixed relative to the second connector such that operation of the drive mechanism rotates the coupling member and the second connector together such that the second connector is screwed on to the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to engage and open the valve whilst the lock is in the locked state. The lock is configured such that, once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member that is greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve. The present disclosure also relates to a kit of parts for a coupling and to a method of fluidly connecting first and second spacecraft using a coupling.

公开(公告)号：US11280194B2

公开(公告)日：2022-03-22

申请号：US15560916

申请日：2016-04-22

Applicant: Trans Astronautica Corporation

Inventor： Joel Sercel

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

Abstract: An optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

公开(公告)号：US11273932B2

公开(公告)日：2022-03-15

申请号：US16127111

申请日：2018-09-10

Applicant: Space Arena, Inc.

Inventor： Daniel Faber

IPC: B64G1/24 ,  B64C39/02 ,  H01L23/60 ,  B64G1/64 ,  A63B71/02

Abstract: Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

公开(公告)号：US11254453B2

公开(公告)日：2022-02-22

申请号：US16748617

申请日：2020-01-21

Applicant: Space Systems/Loral, LLC

Inventor： Andrew E. Turner

IPC: B64G1/64 ,  B64G1/00 ,  B64G1/22 ,  B64G1/10

Abstract: Techniques for deploying a plurality of smallsats from a common launch vehicle are disclosed where a structural arrangement provides a load path between an upper stage of the launch and the plurality of spacecraft. Each spacecraft is mechanically coupled with the launch vehicle upper stage only by the structural arrangement. The structural arrangement includes at least one trunk member that is approximately aligned with the longitudinal axis of the launch vehicle upper stage, a plurality of branch members, each branch member being attached to the trunk member and having at least a first end portion that is substantially outboard from the longitudinal axis; and a plurality of mechanical linkages, each linkage coupled at a first end with a first respective spacecraft and coupled at a second end with one of the plurality of branch members, the trunk member or a second respective spacecraft.

公开(公告)号：US20220033111A1

公开(公告)日：2022-02-03

申请号：US16943203

申请日：2020-07-30

Applicant: The Aerospace Corporation

Inventor： Richard P. WELLE

IPC: B64G1/64 ,  B64G1/10

Abstract: An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

公开(公告)号：US11214388B2

公开(公告)日：2022-01-04

申请号：US16243225

申请日：2019-01-09

Applicant: Raytheon Company

Inventor： Christopher M. Cosner ,  Michael S. Baldwin

IPC: B64G1/64

Abstract: A self-contained payload module and method of deployment of a payload includes a housing that is configured to engage a propulsive payload adapter hub, at least one deployable payload that is arranged in an interior cavity of the housing and deployable using the propulsive payload adaptor hub, a payload electronics system arranged in the interior cavity, a thermal control system in communication with the at least one payload and arranged in the housing, and at least one antenna that is arranged on the housing and configured for wideband communication.