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公开(公告)号：US11565628B2
公开(公告)日：2023-01-31
申请号：US16370660
申请日：2019-03-29
申请人： Blue Origin, LLC
摘要： A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.
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公开(公告)号：US11548663B2
公开(公告)日：2023-01-10
申请号：US16332857
申请日：2016-12-29
发明人： Shunichi Kawamura
摘要： A cable (130) includes an electrical wire band (134). A parallel electrical wire (133) is formed by arranging a pair of a first electrical wire (131) and a second electrical wire (132) without being twisted together. The electrical wire band is formed by arranging a plurality of parallel electrical wires in a lateral row. In addition, between two adjacent parallel electrical wires, a second electrical wire of one parallel electrical wire is arranged adjacently to a first electrical wire of the other parallel electrical wire. Further, the electrical wire band is wound and accommodated in a spiral spring shape in a cable wrap mechanism (100).
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公开(公告)号：US20220332439A1
公开(公告)日：2022-10-20
申请号：US17627652
申请日：2020-09-16
摘要： The invention relates to an aerial transport device by means of connections with supply lines and cables for the transport of electricity, liquids and goods, at the limit of the atmospheres of the planets, in areas with low gravitational attraction, so that the flight can take place in the formation. The aerial transport device by means of flight devices (A, A1n, B, Bn, A4) that are in motion and connected between them, characterized in that the system can supply (P1) and simultaneously transport physical objects, liquids, and energy (P) to and from the outer space of dense atmospheres (D) and to reach the maximum limit of the environment density suitable for space flight devices (A3) with aerodynamic load as well as for horizontal air transport (A4, A2, P, An, A3). The invention is technical device for transporting in space with flying devices and move in formation flight of at least three forming connections.
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公开(公告)号：US11420777B1
公开(公告)日：2022-08-23
申请号：US16746699
申请日：2020-01-17
摘要： A rover can include a spherical shall and an avionics hub. The spherical shell defines a spherical volume and having an inner surface and an outer surface. The avionics hub is disposed within the spherical volume. The avionics hub includes an avionics shell, a data acquisition unit, and a plurality of motortrain assemblies. The avionics shell is disposed with the spherical volume of the spherical shell. The data acquisition unit is disposed within the avionics shell. Each motortrain assembly includes a motorized wheel extending at least partially through the avionics shell and in contact with the inner surface of the spherical shell, the plurality of motortrain assemblies configured to rotate the spherical shell relative to the avionics shell to move the rover.
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公开(公告)号：US20220204188A1
公开(公告)日：2022-06-30
申请号：US17499634
申请日：2021-10-12
发明人： Benjamin LONGMIER , David HASH
摘要： A satellite includes a housing, a circuit board containing circuitry, a battery electrically connected to the circuit board, a tank, an expandable balloon disposed in the tank, a heater, a valve providing liquid communication between the tank and the heater when in an open position and providing no liquid communication between the tank and the heater when in a closed position, and a nozzle having an orifice in liquid communication with the heater. Operating the satellite includes partially filling the expandable balloon with a gas, loading liquid fuel into the tank, launching the satellite into space, opening the valve to cause the liquid fuel from the tank to pass into the heater under pressure provided by the gas in the expandable balloon, activating the heater to heat and vaporize the liquid fuel into a fuel vapor, and expelling the fuel vaper out of the nozzle.
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公开(公告)号：US20220194634A1
公开(公告)日：2022-06-23
申请号：US17442442
申请日：2019-06-03
发明人： Erich H. Soendker
摘要： A reconfigurable power processing unit for a spacecraft including a plurality of power modules. Each of the power modules includes a first power source and a second power source. The first power source and the second power source are configured to be in series in a first state and in parallel in a second state. A plurality of contactors connect each power module to at least one of another power module in the plurality of power modules and a power processing output and are configured to control the state of the power modules.
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公开(公告)号：US11362228B2
公开(公告)日：2022-06-14
申请号：US14728985
申请日：2015-06-02
发明人： Harry A. Atwater , Sergio Pellegrino , Seyed Ali Hajimiri , Jeffrey P. Bosco , Dennis Callahan , Emily C. Warmann
IPC分类号： H01L31/054 , H01L31/052 , H02S40/22 , H02S40/42 , H02S50/00 , H02S30/20 , B64G1/42 , B64G1/44 , B64G1/22 , H02S20/30 , H01L31/0224 , H01L31/0304 , H01L31/0687 , H01L31/0693
摘要： A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Each solar power station includes a plurality of satellite modules. The plurality of satellite modules each include a plurality of modular power generation tiles including a photovoltaic solar radiation collector, a power transmitter and associated control electronics. Numerous embodiments relate to efficient power generation tiles. In one embodiment, an efficient power generation tile includes: at least one photovoltaic material; and at least one concentrator that redirects incident solar radiation towards a photovoltaic material such that the photovoltaic material experiences a greater solar flux relative to the case where the photovoltaic material experiences unaltered solar radiation.
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公开(公告)号：US11302979B2
公开(公告)日：2022-04-12
申请号：US16272363
申请日：2019-02-11
发明人： Kristian Zimmermann
IPC分类号： H01M50/20 , H01M10/6554 , H01M10/613 , B64D27/24 , B64G1/42 , H01M10/625 , H01M10/6556 , H01M10/6553 , H01M50/502 , H01M50/213 , H01M50/249 , H01M50/231
摘要： A battery arrangement for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes at least one battery; and two supporting, multi-layered structural laminates, between which the at least one battery is held on both sides via battery holders, wherein each multi-layered structural laminate has a cooling plate layer and a current collector layer, wherein the at least one battery is coupled electrically to the current collector layer.
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公开(公告)号：US20220017242A1
公开(公告)日：2022-01-20
申请号：US17290699
申请日：2019-11-05
摘要： A stage for a space launch vehicle is provided. The space launch vehicle has a main body including a first end and a second end, and defines a central longitudinal axis between the first end and the second end. The stage comprises a stage rocket engine arranged at or near the first end of the stage to propel the launch vehicle vertically upwards at take-off. The stage furthermore comprises a plurality of fans for providing lift during a landing procedure of the stage, wherein the fans have a rotational axis arranged substantially perpendicular to the central longitudinal axis. Also provided are space launch vehicles and methods for transporting a payload into space.
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公开(公告)号：US11217839B2
公开(公告)日：2022-01-04
申请号：US16272010
申请日：2019-02-11
发明人： Kristian Zimmermann , Petr Schejbal
IPC分类号： H01M10/6555 , H01M10/613 , B64D27/24 , B64G1/42 , H01M10/625 , H01M10/6551 , H01M10/6554 , H01M10/6556 , H01M50/20 , H01M50/502
摘要： A battery arrangement for structurally integrating batteries in a vehicle, in particular an aircraft or spacecraft, includes at least one battery, two supporting cooling plates between which the at least one battery is held on both sides via battery holders, and connecting rods which connect the two cooling plates to one another.
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