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公开(公告)号：US12129051B2
公开(公告)日：2024-10-29
申请号：US17689038
申请日：2022-03-08
发明人： Tyson Smith , John Akagi , Greg Droge
CPC分类号： B64G1/242 , G05B13/042 , B64G1/247
摘要： For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.
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公开(公告)号：US12116148B2
公开(公告)日：2024-10-15
申请号：US17731030
申请日：2022-04-27
申请人： Orbit Fab, Inc.
发明人： Daniel Faber
CPC分类号： B64G1/1078 , B64G1/2427 , B64G1/641 , B64G1/646
摘要： 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.
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公开(公告)号：US12110134B1
公开(公告)日：2024-10-08
申请号：US17739535
申请日：2022-05-09
发明人： Eric W. Monda , Bernard F. Kutter
CPC分类号： B64G1/646 , B64G1/2427
摘要： 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.
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公开(公告)号：US12103711B2
公开(公告)日：2024-10-01
申请号：US17603343
申请日：2019-05-31
发明人： Hisayuki Mukae
CPC分类号： B64G1/242 , B64G1/1085 , B64G1/244
摘要： In a satellite constellation forming system, each satellite in an orbit satellite group includes a propulsion device to change velocity of each satellite in the orbit satellite group. A satellite constellation forming unit causes propulsion devices of satellites in the orbit satellite group to operate in synchronization, for each orbital plane of the plurality of orbital planes. The satellite constellation forming unit causes each satellite in an orbit satellite group in a first orbital plane of the plurality of orbital planes to perform an acceleration and deceleration process of repeating operation of accelerating for a first time period and then decelerating for the first time period. The satellite constellation forming unit causes each satellite in an orbit satellite group in an orbital plane adjacent to the first orbital plane to start the acceleration and deceleration process after a delay of a second time period.
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公开(公告)号：US20240300674A1
公开(公告)日：2024-09-12
申请号：US18653388
申请日：2024-05-02
发明人： Eric Zavesky , James H. Pratt
CPC分类号： B64G1/242 , B64G1/1007 , G01S19/02 , H04B7/18519 , H04B7/18521 , H04B7/18547
摘要： Aspects of the subject disclosure may include, for example, a device that has a processing system including a processor; and a memory that stores executable instructions that, when executed by the processing system, facilitate performance of operations, including receiving a request for an observation of an overhead viewing area from an observer location; discovering an interference of a satellite with the observation of the overhead viewing area; determining possible solutions to the interference; selecting a solution of the possible solutions; receiving the observation from one or more satellites responding to the solution selected; and providing a response to the request including the observation received. Other embodiments are disclosed.
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公开(公告)号：US20240294274A1
公开(公告)日：2024-09-05
申请号：US18205526
申请日：2023-06-03
发明人： Arnon Spitzer
摘要： Satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite with a set of thruster arms each attached to an electric propulsion thruster performs acceleration, deceleration, and steering maneuvers through six degree of freedom positioning of the thrusters, the same set of thruster arms and thrusters performing station keeping of the docked servicer-client satellite system.
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公开(公告)号：US20240278940A1
公开(公告)日：2024-08-22
申请号：US17954144
申请日：2022-09-27
申请人： Jeffrey Bruce Morse
发明人： Jeffrey Bruce Morse
摘要： A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.
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公开(公告)号：US20240271913A1
公开(公告)日：2024-08-15
申请号：US18688864
申请日：2022-08-18
申请人： BAE Systems plc
CPC分类号： F41H5/06 , B64G1/1085 , B64G1/242 , B64G1/52 , G05D1/695 , G05D2109/40
摘要： There is provided a vehicle for protecting an entity against directed-energy weapons, comprising: a housing; and a shield for absorbing or reflecting a laser beam, the shield, in use, extending in a plane from the housing. There is also provided a system of vehicles and a method of coordinating a plurality of vehicles to protect an entity against directed-energy weapons.
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9.发明公开公开(公告)号：US20240253827A1
公开(公告)日：2024-08-01
申请号：US18152359
申请日：2023-01-10
申请人： Network Access Associates Limited ( aprivate company incorporated in England and Wales, with company
发明人： John GUINEY , Chris WINKELMANN , Peter PAPADOPOULOS , Kent MITTERER , Hank TSEU
IPC分类号： B64G3/00 , B64G1/24 , G06F3/0484 , G06Q10/0631
CPC分类号： B64G3/00 , B64G1/24 , G06F3/0484 , G06Q10/06316
摘要： Systems and methods of the present disclosure may use a satellite operations center (SOC) to receive satellite commanding workflows associated with satellites in a fleet of satellites, where each satellite commanding workflow includes tasks configured to trigger at least one fleet operations ground segment element to generate at least one satellite command to cause at least one change in at least one of the satellite payload or the satellite bus. The SOC may determine contact windows associated with the satellites. The SOC may determine a command order of the satellite commanding workflows based on the contact windows and append each satellite commanding workflow to a satellite command queue according to the command order. The SOC may automatically instruct, upon each contact window commencing, satellite communication infrastructure to transmit the satellite command(s) of each successive satellite commanding workflow in the satellite command queue according to the command order.
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公开(公告)号：US12017807B2
公开(公告)日：2024-06-25
申请号：US17405784
申请日：2021-08-18
申请人： Jasem Jamal Alhubail
发明人： Jasem Jamal Alhubail
摘要： A spacecraft capable of re-entry into atmosphere includes an airframe, including a body and one or more wings, and one or more propulsion devices, for example, rocket engines, reaction control thrusters, and jet engines. One or more louver systems are incorporated into the airframe to assist in controlling the aerodynamic profile of the spacecraft. The louver system includes a number of fins rotatable about and axis. An actuator system may rotate the fins in unison or independently of the other fins. A controller may receive information from sensors incorporated into the airframe and send instructions to the actuator system to rotate the fins in response to the sensor information in order to achieve a calculated aerodynamic profile. The spacecraft may also include retractable landing legs. One or more of the wings may be actuated wings.
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