Rendezvous Or Docking Patents (Class 244/172.4)
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Patent number: 12255178Abstract: An electronic device includes a first integrated circuit (IC) die and a second IC die. The first IC die includes a first set of contact pads arranged in a first geometrical pattern on a first surface of the first IC die, the second IC die includes a second set of the contact pads that are arranged, on a second surface of the second IC die, in a second geometrical pattern that is a mirror image of the first geometrical pattern. The second surface of the second IC die is facing the first surface of the first IC die, and the contact pads of the first and second sets are aligned with one another and mounted on one another.Type: GrantFiled: January 26, 2022Date of Patent: March 18, 2025Assignee: Mellanox Technologies, LtdInventor: Ido Bourstein
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Patent number: 12246857Abstract: An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.Type: GrantFiled: March 29, 2022Date of Patent: March 11, 2025Assignee: Maxar Space LLCInventors: Michael Freestone, Sean Dougherty
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Patent number: 12242277Abstract: Embodiments of the present disclosure relate to a guiding system for a robot. The guiding system includes a millimeter-wave positioning system and a transmitter. The millimeter-wave positioning system is configured to determine a position of the robot relative to a base station for charging the robot. The transmitter is configured to emit a radar guiding signal for guiding the robot to the base station and to steer the radar guiding signal towards the position of the robot.Type: GrantFiled: August 16, 2021Date of Patent: March 4, 2025Assignee: Infineon Technologies AGInventors: Heinrich Guenther Heiss, Raffaele Soloperto
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Patent number: 12195204Abstract: Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.Type: GrantFiled: July 13, 2022Date of Patent: January 14, 2025Assignee: Orbit Fab, Inc.Inventors: Alexander Deuitch, Srinivasan A. Suresh, Logan Fettes, James Cho
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Patent number: 12145750Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.Type: GrantFiled: June 14, 2023Date of Patent: November 19, 2024Assignee: L'Garde, Inc.Inventor: Nathaniel C. Barnes
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Patent number: 12122540Abstract: Provided is a space vehicle that includes: a main body; a movable portion configured to reciprocate in an axial direction with respect to the main body; and a magnetic force generation unit attached to a distal end of the movable portion, and attracts, by a magnetic force, a platelike body attached to an object in outer space. The magnetic force generation unit includes: a magnet support member attached to a distal end of the movable portion via a buffer elastic body; and a plurality of permanent magnets laid on a surface of the magnet support member to form an attraction region. When a drive unit moves the movable portion away from the main body, the attraction region protrudes from the main body while maintaining a fixed orientation crossing the axial direction, and is changeable in position and/or orientation by the buffer elastic body when an external force is applied.Type: GrantFiled: October 6, 2021Date of Patent: October 22, 2024Assignee: ASTROSCALE JAPAN INC.Inventors: Takashi Iwai, Kenji Sagara, Sho Fujita
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Patent number: 12097978Abstract: A service satellite having a body, a controller and a docking unit including a telescopic arm, mounted on a 6-DOF parallel manipulator, and two additional gripping arms. The telescopic arm, deployed from the 6-DOF manipulator, is equipped with a pair of rapid closure digits. The telescopic arm facilitates capturing the launch adaptor ring of a client spacecraft, even during tumbling. The 6-DOF parallel manipulator has force sensors and can accommodate post capturing relative motion through active compliance control and controlled de-tumbling, for avoiding generation of high forces in the telescopic arm. After relative rate annihilation, the telescopic arm retracts and the client ring is secured to the 6-DOF manipulator with the help of a pair of clamps. After the ring is secured, two additional gripping arms secure a rigid connection with the launcher ring so that the docking connection comprises three equally spaced connections.Type: GrantFiled: March 25, 2021Date of Patent: September 24, 2024Assignee: Hellenic Technologies of Robotics SAInventor: Vassilios Papantoniou
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Patent number: 12091199Abstract: The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool.Type: GrantFiled: March 7, 2023Date of Patent: September 17, 2024Assignee: MACDONALD, DETTWILER AND ASSOCIATES INC.Inventors: Andrew Paul Turner, Tej Sachdev, Andrew Scott Ogilvie, Natalie Panek, Steve Fisher, Michael Honeybrown, Drew Alexander Grandy, Victor Nifo
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Patent number: 12086873Abstract: A system for docking a vehicle to a building, wherein the vehicle functions as a space of the building when the vehicle is connected thereto, and wherein the building includes at least one station inside or outside thereof such that the vehicle can dock at the at least one station, includes a server configured to check whether the at least one station is available to allow a user to select a station for a vehicle, to select the station randomly when the user does not select the station, and when the vehicle is docked at the selected station, to connect the vehicle to the selected station in wired or wireless manner to manage use of the selected station.Type: GrantFiled: September 29, 2020Date of Patent: September 10, 2024Assignees: HYUNDAI MOTOR COMPANY, KIA MOTORS CORPORATIONInventors: Sang Heon Lee, Jin Ho Hwang, Dong Eun Cha
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Patent number: 12071262Abstract: The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool.Type: GrantFiled: December 21, 2020Date of Patent: August 27, 2024Assignee: MACDONALD, DETTWILER AND ASSOCIATES INC.Inventors: Andrew Paul Turner, Tej Sachdev, Andrew Scott Ogilvie, Natalie Panek, Steve Fisher, Michael Honeybrown, Drew Alexander Grandy, Victor Nifo
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Patent number: 12037143Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.Type: GrantFiled: December 12, 2022Date of Patent: July 16, 2024Assignee: BLUE ORIGIN, LLCInventor: Michael D. Johnson
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Patent number: 12024311Abstract: A boom cover for covering a refueling boom, particularly a flying boom, of a refueling aircraft. The boom has a closure which has a shield sized to cover the open end of the refueling boom, to prevent intrusion of debris, animals, etc. The closure has a hoop for circumscribing the boom and drawing the shield taut for remaining on the boom and flaccid for attachment to and removal from the boom. The closure may be attached to and removed from the boom by a longitudinally rotatable handle which is manipulated by a ground operator. Optionally the handle may be removable from the closure for use on subsequent aircraft or storage.Type: GrantFiled: August 15, 2022Date of Patent: July 2, 2024Assignee: United States of America as represented by the Secretary of the Air ForceInventor: Jacob Helzer
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Patent number: 12017802Abstract: A method for collecting orbital debris comprises detecting a piece of orbital debris approaching a front end of a debris collecting apparatus. An electromagnet is activated and acts to slow or stop rotation of the orbital debris and to attract the orbital debris to the collecting zone. The orbital debris is secured and the orbit of the debris collecting apparatus is changed to a decaying orbit in order to move the debris collecting apparatus out of LEO and closer to Earth. The debris collecting apparatus remains in the decaying orbit until a predetermined altitude is reached at which point the orbital debris is released from the collecting zone to continue along the decaying orbit such that it enters Earth's atmosphere. The debris collecting apparatus is then moved out of the decaying orbit and returned to a stable LEO.Type: GrantFiled: March 22, 2021Date of Patent: June 25, 2024Inventor: Frank David Fulfs Marin
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Patent number: 11987393Abstract: A launch lock system includes a first portion rigidly coupled to the second portion in a first state and the first portion movable in all directions relative to the second portion in a second state. The launch lock system includes a fastener subassembly coupled to the second portion, and the fastener subassembly is movable relative to the second portion from a first position to a second position. The launch lock system includes at least one pivot arm subassembly having a pivot arm movable between a first position and a second position. The pivot arm is coupled to the first portion in the first position. In the first state, the pivot arm is in the first position and cooperates with the fastener subassembly in the first position, and in the second state, the pivot arm is uncoupled from the first portion and the fastener subassembly.Type: GrantFiled: July 16, 2020Date of Patent: May 21, 2024Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Timothy Barber, Ken E. Young, Timothy Hindle
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Patent number: 11939087Abstract: An autonomous compliance controlled generic mooring station includes a pair of mooring systems connected to each other. The pair of mooring systems includes a pair of mooring interfaces, allowing the pair of mooring systems to change between a mooring state and a release state. One of the pair of mooring interfaces includes an electropermanent magnet and the other one of the pair of mooring interfaces includes a ferromagnetic plate. The electropermanent magnet and the ferromagnetic plate are configured to connect the pair of mooring systems together.Type: GrantFiled: March 14, 2022Date of Patent: March 26, 2024Assignee: THE AEROSPACE CORPORATIONInventor: Donald Wayne Denham
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Patent number: 11926441Abstract: An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.Type: GrantFiled: December 20, 2021Date of Patent: March 12, 2024Assignee: KOREA AEROSPACE RESEARCH INSTITUTInventors: Sung Hyuck Im, Jun Seong Lee, Kee Joo Lee, Jae Sung Park
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Patent number: 11845639Abstract: A stability frame for the installation of a wind turbine on an offshore substructure, wherein the wind turbine comprises a tower configured to be anchored to a rigging assembly below the barycenter of the wind turbine, has a main body configured to be mounted about the upper part of the tower; and a plurality of guides, which extend outwardly from the main body and are configured for constraining parts of the rigging assembly so as to laterally support the wind turbine by the rigging assembly.Type: GrantFiled: June 19, 2018Date of Patent: December 19, 2023Assignee: SAIPEM S.P.A.Inventors: Vincent George McCarthy, Christopher Sexton
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Patent number: 11827386Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.Type: GrantFiled: March 20, 2021Date of Patent: November 28, 2023Assignee: Northrop Grumman Systems CorporationInventors: Matthew Alan Michel, Michael Alfred Tosto, Kevin David Tebbe, Daisaku Inoyama, John Francis Papayanopoulos
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Patent number: 11738891Abstract: A refinery spacecraft comprises a hub section defining a longitudinal axis, an excavator segment to convey material into the hub section, first, second and third rotary ring segments rotatable about the hub section with adjustable speed and direction, each rotary ring segments comprising three modules configured to carry out refining or storage processes and wherein two of the three modules in each rotary ring segment have adjustable angular positions relative to the longitudinal axis. Methods of collecting and refining substances from an asteroid, derelict orbiting spacecraft or other space junk, can comprise attaching a refining spacecraft to an asteroid, extracting material from the asteroid, transferring material into a refining hub, transferring material to refining rings orbiting the refining hub, and controlling orbiting of the refining rings about the hub to establish and maintain angular momentum of the refining spacecraft at a stable condition.Type: GrantFiled: December 30, 2020Date of Patent: August 29, 2023Assignee: United States of America as Represented by the Administrator of NASAInventor: Gregory Allen Dorais
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Patent number: 11713141Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.Type: GrantFiled: September 7, 2021Date of Patent: August 1, 2023Assignee: L'Garde, Inc.Inventor: Nathaniel C. Barnes
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Patent number: 11702230Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a non-sealing berthing system includes a tunnel having an interface surface that mates with a docking system of a target spacecraft. The berthing system further includes sliding hooks disposed circumferentially on the interface surface of the tunnel, preload members disposed circumferentially at the interface surface of the tunnel and configured to extend and retract from the interface surface in an axial direction, guide petals spaced around an inner peripheral surface of the tunnel, and soft capture petals spaced around the inner peripheral surface of the tunnel. The soft capture petals include capture latches configured to engage mechanical latch strikers on the docking system of the target spacecraft.Type: GrantFiled: May 17, 2019Date of Patent: July 18, 2023Assignee: The Boeing CompanyInventors: Raju Dharmaraj, Thomas L. Hoffman
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Patent number: 11702229Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a berthing system includes a tunnel having an interface surface that defines a hard capture mating plane for mating with a docking system of a target spacecraft. The berthing system further includes hooks disposed circumferentially on the interface surface, one or more pressure seals disposed on the interface surface, spring-loaded guide petals spaced around an inner peripheral surface of the tunnel that are configured to independently slide in the axial direction, and capture latches spaced around the inner peripheral surface that are configured to engage mechanical latch strikers on the docking system.Type: GrantFiled: May 17, 2019Date of Patent: July 18, 2023Assignee: The Boeing CompanyInventors: Raju Dharmaraj, Thomas L. Hoffman
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Patent number: 11661218Abstract: An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.Type: GrantFiled: August 8, 2017Date of Patent: May 30, 2023Assignee: ISPACE, INC.Inventors: Takeshi Hakamada, Takahiro Nakamura, John Walker, Toshiro Shimizu, Toshiki Tanaka, Daisuke Furutomo, Yu Kudo, Kiyona Miyamoto, Daishi Matsukura, Mohamed Ragab, Abdelkader Haouchine, Damien Haikal, Chit Hong Yam, Julian Jakub Gramatyka
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Patent number: 11643226Abstract: Provided herein are various enhancements to spacecraft or other vehicles, including spacecraft docking mechanisms and vehicle mating systems. In one example, a vehicle mating mechanism includes a latch assembly of a vehicle having soft capture elements and hard capture elements. The soft capture elements accept a bar element of a mating vehicle and retain the bar element to within an envelope that provides a soft capture with the mating vehicle. The hard capture elements move within the envelope to engage the bar element and draw the bar element toward the vehicle to provide a hard capture with the mating vehicle. The vehicle mating mechanism can also include a cup-cone interface element of the vehicle that mates with a cup-cone interface element of the mating vehicle during the hard capture to establish an alignment between the vehicle and the mating vehicle.Type: GrantFiled: September 1, 2020Date of Patent: May 9, 2023Assignee: Lockheed Martin CorporationInventors: Jonathan Michael Markcity, Christopher Leighton Brown
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Patent number: 11572200Abstract: A first spacecraft comprises a drive mechanism. A second spacecraft comprises a valve for filling/draining the second spacecraft. The coupling assembly comprises a first connector comprising an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism. A second connector comprises a stop portion and a bore for transferring fluid. Operation of the drive mechanism rotates the coupling member and the second connector together to screw the second connector onto the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to open the valve whilst the lock is in the locked state. Once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member 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.Type: GrantFiled: March 27, 2020Date of Patent: February 7, 2023Assignee: AIRBUS DEFENCE AND SPACE LIMITEDInventors: Juliet Gregory, James Sadler, William Bentall, Frederique Dupont De Denechin, Henri Bavestrello, Marc Manz, James Sheppard-Alden
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Patent number: 11564531Abstract: A device for automatically hand-swaying beverage cups is disclosed, comprising a robotic arm and a cover, wherein the robotic arm has a plurality of movable arms and a plurality of joints that pivotally connect each of the movable arms to each other, and at the extreme end of such movable arms there install a pair of symmetrical clamping components and a clamping controller, and also includes a host computer electrically connected to each of the movable arms, each of the joints and the clamping controller, respectively; in addition, the cover respectively has a conical surface on the outside, an inner hole is openly configured on the bottom surface of the cover, and each of the clamping components can collectively clamp the cover and the cup thus facilitating the hand-swaying operations of the cup with the robotic arm.Type: GrantFiled: March 11, 2020Date of Patent: January 31, 2023Assignee: O-VIEW TECHNOLOGY CO., LTD.Inventor: Chia-l Pan
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Patent number: 11560243Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.Type: GrantFiled: February 22, 2019Date of Patent: January 24, 2023Assignee: Blue Origin, LLCInventor: Michael D. Johnson
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Patent number: 11554885Abstract: A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.Type: GrantFiled: June 7, 2021Date of Patent: January 17, 2023Inventor: David L. Green
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Patent number: 11537135Abstract: A moving robot includes: a main body; a traveling unit configured to rotate and move the main body; a sensing unit configured to sense position information of a specific point of a front portion of a docking device; and a controller configured to, based on sensing result of the sensing unit, determine i) whether a first condition, which is preset to be satisfied when the docking device is disposed in a front of the moving robot, is satisfied, and ii) whether a second condition, which is preset to be satisfied when the moving robot is disposed in a front of the moving robot, is satisfied, to control an operation of the traveling unit so as to satisfy the first condition and the second condition, and to move to the front so as to attempt to dock in a state where the first condition and the second condition are satisfied.Type: GrantFiled: January 16, 2019Date of Patent: December 27, 2022Assignee: LG ELECTRONICS INC.Inventors: Sungbeom Cho, Jaeheon Chung, Seaunglok Ham, Jinwoo Han
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Patent number: 11459116Abstract: An example system includes a processor and a non-transitory computer-readable medium having stored therein instructions that are executable to cause the system to perform various functions. The functions include: (i) acquiring an image of a first aerial vehicle, the image depicting an object of a second aerial vehicle prior to contact between the object and a surface of the first aerial vehicle; (ii) providing the image as input to a data-driven analyzer that is trained in a supervised setting with example images for determining a predetermined point of contact between the object and the surface of the first aerial vehicle; (iii) determining, based on an output of the data-driven analyzer corresponding to the input, an estimated point of contact between the object and the surface of the first aerial vehicle; and (iv) providing the estimated point of contact to a display system.Type: GrantFiled: June 24, 2020Date of Patent: October 4, 2022Assignee: The Boeing CompanyInventors: Trent M. Kyono, Steven F. Griffin, Jacob A. Lucas, James L. Clayton, Justin C. Hatcher
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Patent number: 11377237Abstract: 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.Type: GrantFiled: May 1, 2019Date of Patent: July 5, 2022Assignee: UNITED LAUNCH ALLIANCE, L.L.C.Inventors: Eric W. Monda, Bernard F. Kutter
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Patent number: 11338911Abstract: Example magnetic recovery systems and magnetic docking mechanisms for fixed-wing UAVs are disclosed herein. An example capture mechanism for an unmanned aerial vehicle (UAV) includes a first member attached to a capture vehicle, the first member having a first portion having a first shape and a magnetic portion; and a second member attached to the UAV, the second member having a second portion having a second shape, wherein the first member and the second member mutually self-align responsive to incidental contact of the first shape and the second shape, and the magnetic portion is to capture the second member.Type: GrantFiled: September 18, 2018Date of Patent: May 24, 2022Assignee: Insitu, Inc.Inventor: John R. Wong
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Patent number: 11142349Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.Type: GrantFiled: February 15, 2019Date of Patent: October 12, 2021Assignee: L'Garde, Inc.Inventor: Nathaniel C. Barnes
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Patent number: 11104459Abstract: Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.Type: GrantFiled: December 1, 2017Date of Patent: August 31, 2021Assignee: Northrop Grumman Systems CorporationInventors: Peter O. Sorensen, Matthew Alan Michel, William A. Llorens, David M. Murphy, Jeffrey Braden, Michael Edward McEachen, Michael Foster
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Patent number: 11053031Abstract: A spacecraft docking system and method thereof are provided. The system comprises an active docking device and a passive docking device. The active docking device comprises an active docking ring and a docking frame. The active docking device further comprises three sets of buffer mechanisms, each set of the buffer mechanisms comprises a main buffer, two screw nut assemblies, and a self-difference buffer. An upper end and a lower end of the screw nut assembly are movably connected to the active docking ring and the docking frame, respectively. The two screw nut assemblies in each set are simultaneously driven and stretched by the main buffer, being also connected to each other through the self-difference buffer, and able to be relatively adjusted and stretched through the self-difference buffer.Type: GrantFiled: June 13, 2017Date of Patent: July 6, 2021Assignee: AEROSPACE SYSTEM ENGINEERING SHANGHAIInventors: Zhi Liu, Chongfeng Zhang, Zongxiang Jin, Junwei Shi, Zhe Xie, Xueping Hu
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Patent number: 10981281Abstract: The present disclosure relates to a low mass system for releasably securing a robotic arm to a spacecraft and also securing various payloads to the robotic arm and to each other, permitting the robotic arm to be both moved from one location to another suitably equipped location on a spacecraft to another and to allow the free end of the robotic arm to be secured to any payload also similarly equipped such that this payload may be manipulated by the robotic arm.Type: GrantFiled: December 1, 2017Date of Patent: April 20, 2021Assignee: MACDONALD, DETTWILER AND ASSOCIATES INC.Inventors: Gavin Hay, Michael Robert Honeybrown, Peter Krimbalis, Justin Charbonneau
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Patent number: 10960992Abstract: According to the present invention, the device, which is provided with a male element secured to one of the parts and a female element secured to the other of said parts, comprises a plurality of resilient fastening strips forming a flared receptacle for said male element inside said female element. This receptacle is slidably movable so as to capture, pull and hold said male element inside said female element.Type: GrantFiled: October 5, 2016Date of Patent: March 30, 2021Assignee: ArianeGroup SASInventor: Sylvain Grosroyat
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Patent number: 10882643Abstract: A capturing plate is attached to an on-orbit device, and the capturing plate is attached to a part of the on-orbit device where a capturing device bonds to the on-orbit device in space with a bonding component, including adhesive, of the capturing device. A method for capturing the on-orbit device includes moving the capturing device including the bonding component to the on-orbit device and letting the bonding component of the capturing device adhere to the on-orbit device.Type: GrantFiled: May 26, 2017Date of Patent: January 5, 2021Assignee: Astroscale Japan Inc.Inventor: Mitsunobu Okada
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Patent number: 10882644Abstract: Techniques for performing spacecraft rendezvous and/or docking include operating a first orbiting spacecraft, the first spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement and performing one or both of a rendezvous operation and a docking operation with the first spacecraft and a second orbiting spacecraft, the second spacecraft including one or more actuators. The performing one or both of the rendezvous operation and the docking operation includes determining a pose and pose rate of the second spacecraft relative to the first spacecraft using observations made by the sensor arrangement and determining a desired approach trajectory for the second spacecraft.Type: GrantFiled: October 10, 2017Date of Patent: January 5, 2021Assignee: Space Systems/Loral, LLCInventors: Robert Erik Schwarz, John Douglas Lymer
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Patent number: 10816321Abstract: Provided herein are a measurement device and an operation method thereof. The measurement device senses a distance variation between the measurement device and an object using a built-in proximity sensor and accordingly determines whether to turn on or turn off a track sensing module and an optical ranging module such that the measurement device provides intelligent selection to achieve energy saving without being interfered with by other sensors being turned on.Type: GrantFiled: November 11, 2016Date of Patent: October 27, 2020Assignee: PIXART IMAGING INC.Inventors: Ting-Yang Chang, Shih-Wei Kuo, Yen-Min Chang
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Patent number: 10738444Abstract: A faucet including a faucet head, a body and a magnetic coupling releasably coupling the faucet head to the faucet body.Type: GrantFiled: March 21, 2019Date of Patent: August 11, 2020Assignee: Delta Faucet CompanyInventor: Alfred Charles Nelson
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Patent number: 10696425Abstract: A system for imparting linear momentum transfer may include a catching mechanism of a target space vehicle and a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle. The tether may be fixedly or detachably connected to a Kinetic Energy Storage and Transfer (KEST) vehicle that maneuvers and potentially retrieves the tether. Alternatively, the tether may be separate from the KEST vehicle and may be retrieved by a suitable retrieving mechanism, such as a robotic arm.Type: GrantFiled: May 10, 2017Date of Patent: June 30, 2020Assignee: The Aerospace CorporationInventor: Robert Alan Hickman
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Patent number: 10676189Abstract: An aircraft-to-aircraft retrieval system can be used to capture a remote aircraft for retrieval into and service by a transport aircraft during a flight mission. An aircraft capture device can be towed from the transport aircraft and brought into proximity with the remote aircraft during flight. A probe of the remote aircraft can be received within a receptacle of the aircraft capture device, and locking cables or locking arms of the aircraft capture device can be secured onto a portion of the probe. The aircraft capture device can be provided with an activation switch for detecting contact with the probe located in the receptacle and for transmitting an indication of the contact to initiate engagement of the probe. The aircraft capture device can be locked to the probe while it is reeled to the transport aircraft for retrieval of the remote aircraft.Type: GrantFiled: February 1, 2017Date of Patent: June 9, 2020Assignee: LOCKHEED MARTIN CORPORATIONInventor: William Benton Lytle
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Patent number: 10569911Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.Type: GrantFiled: September 13, 2016Date of Patent: February 25, 2020Assignee: NanoRacks, LLCInventors: Michael David Johnson, Mark David Rowley, Michael Desmond Lewis, J. Brockton Howe
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Patent number: 10513352Abstract: A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.Type: GrantFiled: August 4, 2015Date of Patent: December 24, 2019Assignee: AIRBUS DEFENCE AND SPACE SASInventors: Dominique Poncet, Cyril Tourneur, René Cheynet De Beaupre
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Patent number: 10513354Abstract: There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.Type: GrantFiled: July 12, 2019Date of Patent: December 24, 2019Assignee: MACDONALD, DETTWILER AND ASSOCIATES INC.Inventors: Tej Singh Sachdev, John Douglas Lymer, Richard Andrew Bryan, Branko Francetic, Paul Robert Peacock, Peter Panagiotis Krimbalis
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Patent number: 10469527Abstract: Disclosed are systems and methods for protection of a technological system (TS) from cyber attacks. An exemplary method comprises: obtaining a real state of the TS; initializing a cybernetic control system (CCS) by synchronizing the CCS with the TS; comparing, by the CCS, the real state of the TS with an ideal state of the TS; based on the comparison, identifying a deviation of the real state of the TS from the ideal state of the TS; when the deviation is identified, checking an integrity of at least functional interconnections of the states of one or more elements of the TS; determining whether the ideal state of the TS is a modeling error based on one or more confirmed sustained functional interconnections between elements of the TS; and identifying anomalies in the TS based on one or more disturbed functional interconnections between elements of the TS.Type: GrantFiled: September 2, 2016Date of Patent: November 5, 2019Assignee: AO Kaspersky LabInventors: Sergey V. Gordeychik, Andrey B. Lavrentyev, Andrey P. Doukhvalov
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Patent number: 10464696Abstract: A space device includes: an adhesion part to adhere to a target existing in the space; and a propulsion part to obtain propulsion power. The space device that adheres to the target at the adhesion part moves together with the target by the propulsion part, thereby conveying the target to a predetermined target position.Type: GrantFiled: March 18, 2015Date of Patent: November 5, 2019Assignee: ASTROSCALE JAPAN INC.Inventor: Mitsunobu Okada
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Patent number: 10427808Abstract: There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset center of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to center of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset center-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.Type: GrantFiled: May 19, 2015Date of Patent: October 1, 2019Assignee: MacDonald, Dettwiler and Associates Inc.Inventors: Tej Singh Sachdev, John Douglas Lymer, Richard Andrew Bryan, Branko Francetic, Paul Robert Peacock, Peter Panagiotis Krimbalis
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Patent number: 10145993Abstract: Described are retroreflective marker devices, which encode information that can be read by optical sensors, such as LiDAR devices, and that do not detract from human safety. Also described are kits for retrofitting existing markers.Type: GrantFiled: January 4, 2018Date of Patent: December 4, 2018Assignee: LIGHTHOUSE & BEACON, INC.Inventors: Sura Hadi, William Davis, Michael John Bosworth Roberts, Michalyn Andrews