公开(公告)号：US12129030B2

公开(公告)日：2024-10-29

申请号：US16771473

申请日：2018-12-14

申请人： Incaendium Initiative Corporation

发明人： Michael S. Thomas

IPC分类号： B64D1/16 ,  A62C3/02 ,  A62C37/00 ,  B64C1/00 ,  B64C1/38 ,  B64C1/40 ,  B64C9/00 ,  B64C15/14 ,  B64C19/02 ,  B64C39/02 ,  B64U20/60 ,  B64U50/18 ,  B64U50/34 ,  G01S19/42 ,  G05D1/00 ,  G05D1/10 ,  B64U101/47

CPC分类号： B64D1/16 ,  A62C3/0228 ,  A62C37/00 ,  B64C1/38 ,  B64C1/40 ,  B64C9/00 ,  B64C15/14 ,  B64C19/02 ,  B64U20/60 ,  B64U50/18 ,  B64U50/34 ,  G05D1/101 ,  B64C2001/0072 ,  B64C2009/005 ,  B64C2201/145 ,  B64U2101/47 ,  G01S19/42

摘要： A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

公开(公告)号：US20240353250A1

公开(公告)日：2024-10-24

申请号：US18683606

申请日：2022-07-27

申请人： SAFRAN HELICOPTER ENGINES

发明人： Antoine Pascal MOUTAUX ,  Olivier ROBERT

IPC分类号： G01F23/16 ,  B64D1/16 ,  G01F22/02 ,  G01F23/18

CPC分类号： G01F23/162 ,  G01F22/02 ,  G01F23/185 ,  B64D1/16

摘要： The invention relates to a sensor (1) for determining a liquid level (NE) for an aircraft tank (100), the determining sensor (1) comprising a closure device (2) for closing a port (101) of the tank (100) and a measuring device (3), removably mounted on the closure device (2), comprising a liquid line (20) configured to convey liquid from the port (100) of the tank (100), and a member (21) for automatically sealing the liquid line (20) if the measuring device (3) is not mounted on the closure device (2), the measuring device (3) comprising at least one pressure measuring member (30) configured to measure a pressure difference between the liquid pressure (P1) in the liquid line (20) and a reference pressure (P2) in order to deduce the liquid level (NE) thereof.

公开(公告)号：US12117830B2

公开(公告)日：2024-10-15

申请号：US18208987

申请日：2023-06-13

申请人： AEROVIRONMENT, INC.

发明人： Macdonald John Peebles ,  Andrew Martin ,  Charles Lawrence Baker ,  Daisy Wang ,  Kevin Jay Aguilar ,  Matthew Allen Hanna ,  Brian Young ,  Eric Sornborger ,  Eric James Aagaard

IPC分类号： G05D1/00 ,  B64C39/02 ,  B64D1/04 ,  B64D1/16 ,  B64D47/08 ,  F41G3/02 ,  F41G3/04 ,  F41G3/14 ,  F41G3/16 ,  F41G7/00 ,  F41G7/20 ,  F41G7/22 ,  F41G9/00 ,  G01C11/06 ,  G01C23/00 ,  G08G5/00

CPC分类号： G05D1/0027 ,  B64C39/024 ,  B64D1/04 ,  B64D1/16 ,  B64D47/08 ,  F41G3/02 ,  F41G3/04 ,  F41G3/145 ,  F41G3/165 ,  F41G7/007 ,  F41G7/20 ,  F41G7/2233 ,  F41G9/00 ,  G01C11/06 ,  G01C23/00 ,  G08G5/0047 ,  G08G5/0013 ,  G08G5/0026 ,  G08G5/0034 ,  G08G5/0069

摘要： A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.

公开(公告)号：US12097971B2

公开(公告)日：2024-09-24

申请号：US18297826

申请日：2023-04-10

申请人： Modern Technology Solutions, Inc.

发明人： Marinus Bernard Bosma

IPC分类号： B64D39/06 ,  B64C39/02 ,  B64D1/06 ,  B64D1/16 ,  B64D1/22 ,  B64D5/00 ,  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 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.

公开(公告)号：US20240288872A1

公开(公告)日：2024-08-29

申请号：US18531887

申请日：2023-12-07

申请人： JAR Scientific, LLC

发明人： Justin Starr ,  Ashish Basuray ,  Roman Kazantsev

IPC分类号： G05D1/00 ,  B60L58/12 ,  B64C39/02 ,  B64D1/16 ,  B64D9/00 ,  B64D47/08 ,  B64F1/36 ,  B64U10/13 ,  B64U50/19 ,  B64U101/30 ,  G01S19/45 ,  G05D1/249 ,  G05D1/692 ,  G05D1/698 ,  G06F18/25 ,  G06V10/764 ,  G06V10/82 ,  G06V20/10 ,  G06V20/13 ,  G06V20/17 ,  G06V20/52 ,  G06V40/10 ,  G08G5/00 ,  G08G5/02 ,  G08G5/04

CPC分类号： G05D1/104 ,  B60L58/12 ,  B64C39/024 ,  B64D1/16 ,  B64D9/00 ,  B64D47/08 ,  B64F1/362 ,  G01S19/45 ,  G05D1/249 ,  G05D1/692 ,  G05D1/698 ,  G06F18/25 ,  G06V10/764 ,  G06V10/82 ,  G06V20/10 ,  G06V20/13 ,  G06V20/17 ,  G06V20/176 ,  G06V20/52 ,  G08G5/0043 ,  G08G5/02 ,  G08G5/045 ,  B60L2200/10 ,  B64U10/13 ,  B64U50/19 ,  B64U2101/30 ,  B64U2201/10 ,  G06V40/10 ,  G06V2201/08

摘要： An embodiment provides unmanned aerial vehicles (UAVs) for infrastructure surveillance and monitoring. One example includes monitoring power grid components such as high voltage power lines. The UAVs may coordinate, for example using swarm behavior, and be controlled via a platform system. Other embodiments are described and claimed.

公开(公告)号：US12043387B2

公开(公告)日：2024-07-23

申请号：US18149078

申请日：2022-12-31

申请人： Autoflight (Kunshan) Co., Ltd.

发明人： Yu Tian

IPC分类号： B64D1/16 ,  B64U10/25 ,  B64U60/10 ,  B64U101/45 ,  B64U101/47

CPC分类号： B64D1/16 ,  B64U10/25 ,  B64U60/10 ,  B64U2101/45 ,  B64U2101/47

摘要： An unmanned aerial vehicle having a fuselage, a water collection and emission equipment, wings, linear reinforcements, a landing gear and a vertical fin. The water collection and emission equipment has buoyancy units, a sealed cabin, a water pump and a water collection and emission pipe. The sealed cabin is detachably connected to the fuselage, and a compartment is arranged in the sealed cabin. The water pump is arranged in the compartment and the side wall of the sealed cabin has at least one concave part which is concave towards the direction of the inner cavity used for slowing down the swaying of water.

公开(公告)号：US12017773B2

公开(公告)日：2024-06-25

申请号：US17684493

申请日：2022-03-02

申请人： Victor D. Trotter

发明人： Victor D. Trotter

IPC分类号： A62C3/00 ,  A62C3/02 ,  B64D1/16 ,  F16K1/20 ,  F16K31/04

CPC分类号： B64D1/16 ,  A62C3/0235 ,  F16K1/2007 ,  F16K1/2021 ,  F16K31/047

摘要： A dump gate system for a fluid hopper in a firefighting aircraft. A gate sealably engages a gate opening in the hopper at a closed position. The gate is hingedly connected about the gate opening, and a drive shaft is supported within the hopper. A crank arm is fixed to the drive shaft and is further coupled to the gate by a connecting link. The crank arm and the connecting link define an over-center geometry while the gate is at the closed position, such that weight of the fluid on the gate induces torque on the drive shaft in a gate-closing direction. A linear electric motor is selectively coupled to rotate the drive shaft in a gate-opening direction to thereby enable control of the fluid flow from the hopper according to an angular position of the drive shaft.

公开(公告)号：US20240152137A1

公开(公告)日：2024-05-09

申请号：US18208987

申请日：2023-06-13

申请人： AEROVIRONMENT, INC.

发明人： Macdonald John Peebles ,  Andrew Martin ,  Charles Lawrence Baker ,  Daisy Wang ,  Kevin Jay Aguilar ,  Matthew Allen Hanna ,  Brian Young ,  Eric Sornborger ,  Eric James Aagaard

IPC分类号： G05D1/00 ,  B64C39/02 ,  B64D1/04 ,  B64D1/16 ,  B64D47/08 ,  F41G3/02 ,  F41G3/04 ,  F41G3/14 ,  F41G3/16 ,  F41G7/00 ,  F41G7/20 ,  F41G7/22 ,  F41G9/00 ,  G01C11/06 ,  G01C23/00 ,  G08G5/00

CPC分类号： G05D1/0027 ,  B64C39/024 ,  B64D1/04 ,  B64D1/16 ,  B64D47/08 ,  F41G3/02 ,  F41G3/04 ,  F41G3/145 ,  F41G3/165 ,  F41G7/007 ,  F41G7/20 ,  F41G7/2233 ,  F41G9/00 ,  G01C11/06 ,  G01C23/00 ,  G08G5/0047 ,  G08G5/0013 ,  G08G5/0026 ,  G08G5/0034 ,  G08G5/0069

摘要： A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.

公开(公告)号：US20240066337A1

公开(公告)日：2024-02-29

申请号：US18452192

申请日：2023-08-18

申请人： Airbus SAS

发明人： Jean-Loup THIERS ,  Samuel BURGUNDER

IPC分类号： A62C3/02 ,  B64D1/16

CPC分类号： A62C3/0242 ,  B64D1/16

摘要： A control device of a fluid storing and jettisoning system with which a host aircraft is equipped, comprising a fluid reservoir and at least one tube, is connected to valves for allowing or preventing the jettisoning of water and controls the flow rate of fluid jettisoned and the jettisoning duration depending on at least one parametrized criterion.

公开(公告)号：US20230391447A1

公开(公告)日：2023-12-07

申请号：US18236592

申请日：2023-08-22

申请人： Troy Reabe

发明人： Troy Reabe

IPC分类号： B64C19/02 ,  B64D1/16 ,  F16H51/00 ,  G05G5/00 ,  F16H21/06 ,  F16H21/44 ,  G05G1/04

CPC分类号： B64C19/02 ,  B64D1/16 ,  F16H51/00 ,  G05G5/005 ,  F16H21/06 ,  F16H21/44 ,  G05G1/04 ,  G05G2505/00

摘要： 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.