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公开(公告)号：US12065271B2
公开(公告)日：2024-08-20
申请号：US17574486
申请日：2022-01-12
摘要： Embodiments of the present disclosure are directed to techniques for transitioning a spacecraft from a power-saving state to a power-consuming state at a time after launch of the spacecraft on a launch vehicle. Because the spacecraft can detect conditions for transitioning to the power-consuming state, commands received via an umbilical connection to the launch vehicle, or detecting the presence or absence of such a connection, is unnecessary, thereby removing several technical barriers to eliminating such umbilical connections altogether.
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公开(公告)号：US12037141B1
公开(公告)日：2024-07-16
申请号：US18544463
申请日：2023-12-19
发明人： Xu Guo , Zhi Sun , Wenyu Hao , Tichang Jiao , Shurui Ye
IPC分类号： B64G1/00
CPC分类号： B64G1/002
摘要： A main frame structure having box-section bearing beams of a launch vehicle engine includes a body. The body includes upper bearing table tops, lower bearing table tops, a cross gasket, a connecting ring and the box-section bearing beams. The box-section bearing beam includes an upper surface, a lower surface and two side beam walls, and has a cavity structure. Penetrating transverse ribs penetrating the two side beam walls are arranged on the box-section bearing beams, and one ends of the box-section bearing beams are circumferentially distributed at an outer side of the connecting ring. The lower bearing table tops are arranged at the outer side of the connecting ring, the lower bearing table tops are connected to the cross gasket, and the other ends of the upper surfaces and the lower surfaces are connected by means of arc chamfers and are connected to the upper bearing table tops.
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公开(公告)号：US12031507B2
公开(公告)日：2024-07-09
申请号：US17754787
申请日：2020-08-27
发明人： Andrew Lapsa , Thomas Feldman
CPC分类号： F02K9/97 , B64G1/006 , F02K9/64 , F02K9/972 , F05D2240/1281
摘要： An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface. An engine includes a high pressure chamber and the augmented aerospike nozzle. A vehicle for supersonic flight includes the engine with the augmented aerospike nozzle.
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公开(公告)号：US12017804B2
公开(公告)日：2024-06-25
申请号：US17362228
申请日：2021-06-29
摘要： A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.
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公开(公告)号：US12006068B2
公开(公告)日：2024-06-11
申请号：US17580727
申请日：2022-01-21
发明人： Weiming Ma , Yuxing Zhang , Mingyuan Zhang , Xiangming Zhang , Weichao Li , Xinlin Long , Chen Deng
CPC分类号： B64G1/002 , H02N11/006 , B60L50/13 , F02K9/74
摘要： 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.
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6.发明公开公开(公告)号：US20240158102A1
公开(公告)日：2024-05-16
申请号：US18283000
申请日：2022-03-11
申请人： SEBASTIAN KLAUS
发明人： SEBASTIAN KLAUS
CPC分类号： B64G1/006 , B64G1/2225 , B64G1/623
摘要： An atmosphere reentry and landing device for a safe reentry of a rocket stage into the atmosphere and for a safe splashdown thereof. The device includes a ballute which is folded in a first state and unfolded in a second state, a shrouding mechanism which carries out a shrouding of the rocket stage with the ballute, a filling mechanism, and a control unit which controls the shrouding mechanism and the filling mechanism. The ballute is disposed on the rocket stage so that an aerodynamics thereof is not compromised in the first state. The ballute substantially shrouds the rocket stage in the second state. During reentry into the atmosphere, the filling mechanism fills the ballute in the second state with air or a gas from a boundary layer which is created between a plasma formed in front of a surface of the device and the surface of the device.
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公开(公告)号：US20240116654A1
公开(公告)日：2024-04-11
申请号：US18272383
申请日：2021-09-30
发明人： Michael Lindsay , Takashi Iwai
CPC分类号： B64G1/1081 , B64G1/002 , B64G1/2427 , B64G1/62 , B64G1/645 , B64G1/66
摘要： According to an aspect of the present invention, there is provided a method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. According to another aspect of the present invention, there is provided system for rendezvous with an orbiting object comprising: a first spacecraft raft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.
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公开(公告)号：US20240116653A1
公开(公告)日：2024-04-11
申请号：US17992588
申请日：2022-11-22
摘要： Example coil guns and methods of using coil guns are described herein. An example coil gun includes a first pancake module; a second pancake module, where the first pancake module and the second pancake module are each formed of a winding with an inner superconducting material layer and an outer ordinary conductor layer, where the first pancake module and the second pancake module are physically and/or inductively coupled to propagate a quench of a superconducting state of the first pancake module to the second pancake module.
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公开(公告)号：US11932425B2
公开(公告)日：2024-03-19
申请号：US16902865
申请日：2020-06-16
申请人： Xtenti, LLC
发明人： Daniel Lim , Jason Armstrong , Robert Spicer
摘要： 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.
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公开(公告)号：US11932424B2
公开(公告)日：2024-03-19
申请号：US16988615
申请日：2020-08-08
申请人： Roman Nawojczyk
发明人： Roman Nawojczyk
摘要： System for multiple use of space rockets equipped with spreadable arms and sliding engines covers, and for said space rockets a vertical landing method on two movable gantries situated on a specific sea ship or on a solid ground. Said space rockets comprise steering flaps and a dividable sectional load cover. The specific sea ship comprises specific joined hulls, two horizontally movable decks and tunnels with ballasting wagons. The specific sea ship has installed a landing station for the space rockets. The landing station comprises hangers, grasping wagons and two movable ship gantries. The hangers comprise rotating wedges. The gantries comprise damping wagons. The system comprises also two movable ground gantries and a specific movable ground crane all situated on a solid ground that together create a multi-task station for the space rockets hanging up, reloading, launching, and landing. The system allows that the space rockets can liftoff from two movable gantries while vertically hang on their spreadable arms.
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