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公开(公告)号：US12103701B2
公开(公告)日：2024-10-01
申请号：US18295215
申请日：2023-04-03
IPC分类号： B64D1/06 , B64C39/02 , B64D1/16 , B64D1/22 , B64D5/00 , B64D39/06 , B67D7/04 , B67D7/40 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
CPC分类号： B64D39/06 , B64C39/024 , B64D1/06 , B64D1/16 , B64D1/22 , B64D5/00 , B67D7/04 , B67D7/40 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
摘要： A stabilizing system for a cable has a cable deployed and suspended from a helicopter, a cargo support attached at a deployed end of the cable, an end effector attached to the cable, the end effector comprising thrusters directed in a plurality of directions orthogonal to a vertical axis of the cable, first control circuitry in the helicopter, and second control circuitry in the end effector. Thrust of individual thrusters is controlled through the first and second control circuitry maintaining the axis of the cable vertical, damping swinging of the cable.
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公开(公告)号：US20240010335A1
公开(公告)日：2024-01-11
申请号：US18307266
申请日：2023-04-26
申请人： THOR INDUSTRIES LTD
发明人： Lee THORNHILL , Alistair WRAGG , Fergus DUNCAN
CPC分类号： B64D1/06 , F42B25/00 , F42C5/00 , B64U2101/18
摘要： Disclosed herein is a payload delivery device. The payload delivery device is configured for delivering an explosive component. The payload delivery device comprises a first module having an interior cavity for containing an explosive component. The payload delivery device further comprises at least one attachment module connected to the central module via a connection means. The at least one attachment module having an interior cavity for containing an additional component.
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公开(公告)号：US20230391469A1
公开(公告)日：2023-12-07
申请号：US18297826
申请日：2023-04-10
CPC分类号： B64D39/06 , B67D7/04 , B67D7/40 , B64C39/024 , B64D5/00 , B64D1/06 , B64D1/22 , B64D1/16 , B64U30/10
摘要： A satellite refueling system has a refueling satellite carrying fuel, a fuel hose connected to the fuel carried by the refueling satellite, with a maneuverable end effector at a deployed end of the fuel hose, the end effector comprising a fuel supply nozzle connected to the fuel hose, a plurality of thrusters on the end effector providing thrust in a plurality of directions, an imaging device on the end effector capturing images in an immediate environment of the end effector, and computerized circuitry operating individual ones of the plurality of thrusters in response to the images captured by the imaging device. The refueling satellite deploys the fuel hose, and the computerized circuitry operates the thrusters to maneuver the end effector, bringing the fuel supply nozzle to a location to deliver fuel.
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公开(公告)号：US11745894B2
公开(公告)日：2023-09-05
申请号：US18175472
申请日：2023-02-27
IPC分类号： B64D39/06 , B67D7/04 , B67D7/40 , B64C39/02 , B64D5/00 , B64D1/06 , B64D1/22 , B64D1/16 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
CPC分类号： B64D39/06 , B64C39/024 , B64D1/06 , B64D1/16 , B64D1/22 , B64D5/00 , B67D7/04 , B67D7/40 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
摘要： A refueling system has a vehicle having a fuel tank connected to a deployable fuel hose, an end effector having controlled flight, the fuel hose connected at an end away from the first vehicle, through the end effector to a fuel connector under the end effector, a second vehicle having a fuel tank coupled through a pumping apparatus to a fueling port on an acquisition apparatus adapted to acquire the end effector and connect the fueling port and the fuel connector of the end effector, and control circuitry enabling controlled flight of the end effector, wherein the end effector is controlled to be acquired by the acquisition apparatus to couple the fuel connector with the fueling port and fuel is provided from the fuel tank of one of the vehicles to the fuel tank of the other of the vehicles through the pumping apparatus.
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公开(公告)号：US11623760B2
公开(公告)日：2023-04-11
申请号：US17092800
申请日：2020-11-09
摘要： A satellite refueling system has a refueling satellite carrying fuel, a fuel hose connected to the fuel carried by the refueling satellite, with a maneuverable end effector at a deployed end of the fuel hose, the end effector comprising a fuel supply nozzle connected to the fuel hose, a plurality of thrusters on the end effector providing thrust in a plurality of directions, an imaging device on the end effector capturing images in an immediate environment of the end effector, and computerized circuitry operating individual ones of the plurality of thrusters in response to the images captured by the imaging device. The refueling satellite deploys the fuel hose, and the computerized circuitry operates the thrusters to maneuver the end effector, bringing the fuel supply nozzle to a location to deliver fuel.
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公开(公告)号：US11560228B2
公开(公告)日：2023-01-24
申请号：US16599572
申请日：2019-10-11
申请人： AEREA S.p.A.
摘要： A restrain and release mechanism for an externally airborne load, includes at least one stiff support for suspending the load and an elastically deformable adaptive member designed to maintain the load at pressure contact against the support. The adaptive member is a three-dimensional monolithic metallic body obtained using an additive manufacturing method and having a flexural orthotropic behaviour.
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公开(公告)号：US20210253250A1
公开(公告)日：2021-08-19
申请号：US17101208
申请日：2020-11-23
申请人： HANWHA CORPORATION
发明人： Se Hun Kim , Hye Sung Kim , Woon Soon Lee , Yee Jung Kim , Yong Teo Jeong
摘要： Proposed are a shell launcher for a drone and a method of launching shells for a drone. According to the shell launcher for a drone and the method of launching shells for a drone, by launching shells such as EFPs using a drone, it is possible to use a drone as various weapon systems.
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公开(公告)号：US10730625B1
公开(公告)日：2020-08-04
申请号：US16272593
申请日：2019-02-11
申请人： Raytheon Company
发明人： Joshua J. Kirk
摘要： A system includes a payload ejector configured to contact a payload carried by a flight vehicle and to push the payload away from the flight vehicle. The payload ejector includes a piston configured to extend from the payload ejector and a shock attenuator coupled to the piston, where the shock attenuator is configured to push the payload away from the flight vehicle. The shock attenuator includes a shock attenuator housing and a plunger that is movable within the shock attenuator housing and that extends from the shock attenuator housing. The plunger is configured to be pushed at least partially into the shock attenuator housing in order to damp a shock pulse applied to the payload. The shock attenuator housing may have an interior space, and the shock attenuator may further include a spring, compliant material, or fluid within the interior space.
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公开(公告)号：US20200010195A1
公开(公告)日：2020-01-09
申请号：US16470429
申请日：2017-12-27
发明人： Yoav Herzig , Daniel Marom
摘要： An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.
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公开(公告)号：US10259560B2
公开(公告)日：2019-04-16
申请号：US15270053
申请日：2016-09-20
摘要： A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.
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