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公开(公告)号：US12228382B2
公开(公告)日：2025-02-18
申请号：US17727924
申请日：2022-04-25
Applicant: The Boeing Company
Inventor： John K. Foster , Ryan Binkholder , Thaddeus Jakubowski, Jr.
Abstract: A propulsionless munition configured to be launched from a hypersonic aerial includes a munition body that is free of any propulsion system for producing thrust. The munition body includes a forward section including a radome assembly and an aft section including a control system. The radome assembly includes a nose radome and a frangible radome cover disposed over the nose radome for shielding the nose radome from high temperatures resulting from aerodynamic heating at hypersonic speeds. The frangible radome cover is detachable from the nose radome upon detection by the control system of a predetermined threshold comprising at least one of a predetermined speed, a predetermined altitude, and a predetermined temperature.
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公开(公告)号：US20250010981A1
公开(公告)日：2025-01-09
申请号：US18894867
申请日：2024-09-24
Applicant: Troy Reabe
Inventor： Troy Reabe
Abstract: The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.
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公开(公告)号：US12187431B2
公开(公告)日：2025-01-07
申请号：US17713600
申请日：2022-04-05
Applicant: The Boeing Company
Inventor： Cory Gordon Keller , James V. Eveker
Abstract: A container suspension and release system provides at least one ejector assembly having a carry position and a deployed position. The ejector assembly includes an actuator configured to extend ejector assembly from the carry position to the deployed position, and a retention assembly. The retention assembly employs a bracket attached to the actuator and a fixed sway brace extending from the bracket. A left retention arm is pivotally attached to the bracket and a right retention arm is pivotally attached to the bracket, with the left and right retention arms configured to rotate in opposite directions. A rotation activation mechanism is provided to rotate the left and right retention arms in the deployed position. An energy source connected to the actuator to provides energy to actuate the at least one ejector assembly.
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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
Applicant: Modern Technology Solutions, Inc.
Inventor： Marinus Bernard Bosma
IPC: 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 classification number: B64D39/06 , B64C39/024 , B64D1/06 , B64D1/16 , B64D1/22 , B64D5/00 , B67D7/04 , B67D7/40 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
Abstract: 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
Applicant: THOR INDUSTRIES LTD
Inventor： Lee THORNHILL , Alistair WRAGG , Fergus DUNCAN
CPC classification number: B64D1/06 , F42B25/00 , F42C5/00 , B64U2101/18
Abstract: 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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Patent Agency Ranking
公开(公告)号：US20230391469A1
公开(公告)日：2023-12-07
申请号：US18297826
申请日：2023-04-10
Applicant: Modern Technology Solutions, Inc.
Inventor： Marinus Bernard BOSMA
CPC classification number: B64D39/06 , B67D7/04 , B67D7/40 , B64C39/024 , B64D5/00 , B64D1/06 , B64D1/22 , B64D1/16 , B64U30/10
Abstract: 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
Applicant: Modern Technology Solutions, Inc.
Inventor： Marinus Bernard Bosma
IPC: 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 classification number: B64D39/06 , B64C39/024 , B64D1/06 , B64D1/16 , B64D1/22 , B64D5/00 , B67D7/04 , B67D7/40 , B64U30/10 , B64U50/12 , B64U50/34 , B64U80/82
Abstract: 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
Applicant: Modern Technology Solutions, Inc.
Inventor： Marinus Bernard Bosma
Abstract: 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
Applicant: AEREA S.p.A.
Inventor： Luca Andrea Pernechele , Dario Guffanti
Abstract: 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
Applicant: HANWHA CORPORATION
Inventor： Se Hun Kim , Hye Sung Kim , Woon Soon Lee , Yee Jung Kim , Yong Teo Jeong
Abstract: 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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