-
公开(公告)号：US20240317677A1
公开(公告)日：2024-09-26
申请号：US18519989
申请日：2023-11-27
申请人： Skeyeon, Inc.
IPC分类号： C07C259/06 , A61P35/00 , B64G1/10 , B64G1/42 , B64G1/44 , B64G1/66 , G01S13/90 , G01S19/39 , H04B7/185 , H04B7/195
CPC分类号： C07C259/06 , A61P35/00 , B64G1/1021 , B64G1/425 , B64G1/443 , G01S19/39 , H04B7/18513 , H04B7/195 , B64G1/1028 , B64G1/1035 , B64G1/66 , G01S13/90
摘要： A satellite system operates at altitudes between 180 km and 350 km relying on vehicles including an engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are substantially lower than traditional satellites, reducing size, weight and cost of the vehicles and their constituent subsystems such as optical imagers, radars, and radio links. The system can include a large number of lower cost, mass, and altitude vehicles, enabling revisit times substantially shorter than previous satellite systems. The vehicles spend their orbit at low altitude, high atmospheric density conditions that have heretofore been virtually impossible to consider for stable orbits. Short revisit times at low altitudes enable near-real time imaging at high resolution and low cost. At such altitudes, the system has no impact on space junk issues of traditional LEO orbits, and is self-cleaning in that space junk or disabled craft will de-orbit.
-
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.
-
公开(公告)号：US20240239520A1
公开(公告)日：2024-07-18
申请号：US17944861
申请日：2022-09-14
发明人： Yehia F. Khalil
摘要： A system includes a nuclear reactor having a plurality of fuel rods of radioactive decay material distributed within and embedded within a heat exchange matrix. A plurality of coolant tubes is distributed within and embedded within the heat exchange matrix, interspersed with the plurality of fuel rods. The heat exchange matrix is configured to conduct heat from the fuel rods to the coolant tubes.
-
公开(公告)号：US20240125308A1
公开(公告)日：2024-04-18
申请号：US17772978
申请日：2021-10-14
申请人： ICEYE OY
CPC分类号： B64G1/42 , F03H1/0012 , F03H1/0025 , B64G1/413
摘要： A method of operating a spacecraft propulsion system comprises injecting electrons into the plasma surrounding the spacecraft prior to creating the stream of ions, and after commencing creation of the ion stream, continuing the injection of electrons in an amount sufficient to maintain the spacecraft at a positive potential. This method may be implemented in a single thruster. In spacecraft with multiple thrusters the same method may be implemented in each thruster.
Where the propulsion system comprises a plurality of thrusters, the method may comprise: operating at least one of the thrusters as a drive thruster, and operating at least one of the thrusters as an auxiliary or “reserve” thruster. The electron source of the at least one auxiliary thruster may be operated before creation of the ion stream to inject the electrons into the plasma surrounding the spacecraft.-
公开(公告)号：US11846248B1
公开(公告)日：2023-12-19
申请号：US17683014
申请日：2022-02-28
发明人： Frank Charles Zegler
CPC分类号： F02K9/58 , B64G1/402 , B64G1/421 , F02K9/42 , F02K9/44 , F02K9/50 , F02K9/60 , B64G1/401 , F02K9/425
摘要： A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.
-
公开(公告)号：US11772829B2
公开(公告)日：2023-10-03
申请号：US17254313
申请日：2018-06-27
发明人： Takashi Miyamoto , Naoki Yasuda , Shinichi Okada , Ryota Kusano
摘要： A power supply device (104-1) includes a substrate (20) on which an electric component (25) is mounted, a chassis (10) having a chassis surface (11) and a threaded part (10a), a chassis-side resin part (91) connected to a back surface (20a) and the chassis surface (11), a fixation screw (29), and an insulating member (60). The fixation screw (29) fixes both the electric component (25) and the substrate (20) to the chassis (10) by screw-coupling an end part (29c) of the fixation screw (29), exposed in a direction toward the chassis (10) from an open hole formed through the insulating member (60), to the threaded part (10a) of the chassis (10). In addition, the fixation screw (29) brings the electric component (25) and the chassis (10) into electrical noncontact with each other by being placed in an open hole of the insulating member (60).
-
公开(公告)号：US20230257135A1
公开(公告)日：2023-08-17
申请号：US17918901
申请日：2020-09-14
发明人： Liqiu Wei , Yongjie Ding , Hong Li , Liang Han , Daren Yu
CPC分类号： B64G1/406 , H05H1/4652 , B64G1/428
摘要： A micro-cathode arc propulsion system. By replacing an inductive circuit in a traditional micro-cathode arc propulsion system with a capacitor circuit, the stability of the operation of a micro-cathode arc thruster can be improved due to the stable discharging mode of the capacitor, and as the internal resistance of the capacitor is small during operation, the additional power consumption of the circuit is reduced, and the efficiency of the system is improved. In addition, as a pulse power supply is used to power in a pulse manner, the average power inputted into the micro-cathode arc thruster is greatly reduced.
-
公开(公告)号：US11724831B2
公开(公告)日：2023-08-15
申请号：US17314935
申请日：2021-05-07
申请人： Robert Bado
发明人： Robert Bado , Artem Madatov
摘要： An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.
-
公开(公告)号：US20230227155A1
公开(公告)日：2023-07-20
申请号：US17566811
申请日：2021-12-31
发明人： Ernestine Fu , Grey Parker , Prasanna Natarajan , Matt Korich , Jacob Viau , David Wilson , John Suh , David Byron , Mark Lister
CPC分类号： B64C37/02 , B64G1/16 , B64G1/425 , B64D2221/00
摘要： A combination two vehicle system is provided that includes a land-based vehicle configured for traversal over ground and an aerial vehicle configured for travel through air, where the aerial vehicle is configured to detachably couple with the land-based vehicle. The aerial vehicle includes stabilizing legs to provide stability for take-off or landing. A method of operating the vehicle system includes steps of: providing the land-based and the aerial vehicle having the stabilizing legs, and aerially transporting the vehicle system including the land-based vehicle and the aerial vehicle, where the stabilizing legs provide stability for take-off or landing. In addition, the land-based vehicle may transport a removable cargo pod, which the aerial vehicle may independently retrieve from the land-based vehicle.
-
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.
-
-
-
-
-
-
-
-
-
搜索结果
474 条记录 (耗时 0.023 秒)
