公开(公告)号：US20240253763A1

公开(公告)日：2024-08-01

申请号：US18101914

申请日：2023-01-26

Applicant: JETZERO, INC.

Inventor： John Vassberg ,  Blaine Rawdon

IPC: B64C1/16 ,  B64C39/10 ,  B64D27/26 ,  B64D29/04 ,  B64F5/10

CPC classification number: B64C1/16 ,  B64C39/10 ,  B64D27/40 ,  B64D29/04 ,  B64F5/10

Abstract: A system for providing favorable environment for propulsion system of a blended wing body aircraft, wherein the system comprises a blended wing body, wherein the blended wing body comprises a main body, wherein the main body comprises a main body shaping comprising an upper aft surface configured to provide a favorable environment for a propulsion system of the blended wing body aircraft, and the propulsion system mounted to the upper aft surface of the main body, wherein the propulsion system comprises one or more prime movers, and a nacelle covering the one or more prime movers.

公开(公告)号：US11728540B2

公开(公告)日：2023-08-15

申请号：US17172366

申请日：2021-02-10

Applicant: Bell Textron Inc.

Inventor： William A. Amante ,  Steven Loveland ,  Jessica A. Revere

IPC: H01M10/6556 ,  H01M50/244 ,  H01M10/6554 ,  H01M10/625 ,  H01M10/613 ,  H01M50/249 ,  B64D29/04 ,  B64D33/08

CPC classification number: H01M50/249 ,  B64D29/04 ,  B64D33/08 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6554 ,  H01M10/6556 ,  H01M50/244 ,  H01M2220/20

Abstract: A battery assembly for an aircraft includes a cold plate having an upper planar member, a lower planar member, and at least one fluid channel positioned between the upper and lower planar members and configured to receive a cooling fluid. The battery assembly also includes an upper battery mounted to the upper planar member for transferring heat from the upper battery to the cooling fluid through the upper planar member. The battery assembly further includes a lower battery mounted to the lower planar member for transferring heat from the lower battery to the cooling fluid through the lower planar member.

公开(公告)号：US11565813B2

公开(公告)日：2023-01-31

申请号：US16589405

申请日：2019-10-01

Applicant: UNIVERSITY OF SOUTH CAROLINA

Inventor： Ron Fulbright

IPC: B64C39/02 ,  B64D1/16 ,  B64D47/08 ,  B64D29/04 ,  B60L50/60 ,  B60L53/80 ,  B64D47/00 ,  A62C3/02

Abstract: Presently disclosed subject matter integrates a method of using thousands of semi-autonomous unmanned aerial vehicles, herein called drones, to deliver vastly superior amounts of fire retardant over substantially larger and variably-shaped drop patterns. Each drone is able to swap its own batteries with freshly charged batteries and each drone is able to refill its container with water or fire retardant. Once launched, a swarm of drones can perform repeated trips from the water/retardant source to the fire without human involvement other than the high-level tasking of where to drop the retardant. Once a general drop destination and drop pattern shape is designated, the swarm can transport retardant to that location, form itself into the desired drop shape, and deploy retardant. The drone body is designed to be modular so different components can be attached with ease and no special training or knowledge required.

公开(公告)号：US11485506B2

公开(公告)日：2022-11-01

申请号：US15745691

申请日：2016-07-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Jérôme Jean Tantot

IPC: B64D27/20 ,  F04D29/68 ,  F01D17/16 ,  F04D29/54 ,  F01D9/06 ,  F02K3/062 ,  F04D29/56 ,  B64D29/04 ,  B64D33/02 ,  F02K3/072

Abstract: An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow.

公开(公告)号：US11420759B2

公开(公告)日：2022-08-23

申请号：US17044178

申请日：2019-03-25

Applicant: JAPAN AEROSPACE EXPLORATION AGENCY

Inventor： Atsushi Ueno ,  Tatsunori Yuhara ,  Masashi Kanamori

IPC: F02K1/34 ,  B64C5/02 ,  B64C30/00 ,  B64D27/20 ,  B64D29/04

Abstract: [Object] To provide a supersonic aircraft and a method of reducing sonic booms, by which sonic booms due to engine exhaust can be reduced.
[Solving Means] A supersonic aircraft includes: a pair of engine nacelles 12R, 12L mounted on a fuselage 11 of an airframe 10; fins 13R, 13L as a pair of shielding plates that inhibits engine exhaust 15 discharged from jet engines (not shown) accommodated in the engine nacelles 12R, 12L from wrapping downward around the airframe 10; and a pair of horizontal tails 14R, 14L disposed behind the engine nacelles 12R, 12L. The fins 13R, 13L are disposed on the horizontal tails 14R, 14L so as to sandwich the engine exhaust 15, respectively.

公开(公告)号：US11338901B2

公开(公告)日：2022-05-24

申请号：US16396006

申请日：2019-04-26

Applicant: Rolls-Royce Corporation

Inventor： James Loebig

IPC: B64C1/16 ,  B64C1/00 ,  B64D29/04 ,  B64D27/14 ,  B64D35/02 ,  F01D15/10 ,  B64D31/00

Abstract: An aircraft is disclosed having a boundary layer ingestion propulsor. The aircraft comprises an elongated fuselage extending between a nose section and a tail section. The fuselage has an upswept underside in the tail section. The boundary layer ingestion propulsor is positioned in the tail section. The propulsor comprises a fan radially encased by a nacelle circumscribing the fuselage. The nacelle defines a leading edge line extending from a top dead center to a bottom dead center of the nacelle intersecting an axis of rotation of the fan at an angle no greater than seventy degrees.

公开(公告)号：US11310872B2

公开(公告)日：2022-04-19

申请号：US16401020

申请日：2019-05-01

Applicant: ITT Manufacturing Enterprises LLC

Inventor： A. David Sandiford

IPC: H05B3/18 ,  H05B3/00 ,  B29C70/68 ,  B29C70/84 ,  B29C70/88 ,  B64D15/12 ,  B64D29/00 ,  B64D41/00 ,  H05B3/26 ,  H05B3/28 ,  B29C69/00 ,  B29D99/00 ,  B29C44/18 ,  B64D29/04 ,  B64D33/02 ,  B29L31/30 ,  B29L31/00 ,  C23C14/20 ,  B29K105/04 ,  B29L31/08 ,  B29K105/20 ,  B29K703/04 ,  B29L31/34

Abstract: Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device.

公开(公告)号：US11299284B2

公开(公告)日：2022-04-12

申请号：US16893894

申请日：2020-06-05

Applicant: Zhenkun Wang

Inventor： Zhenkun Wang

IPC: B64D29/04 ,  B64D27/20 ,  B64D33/02 ,  B64C21/04

Abstract: This instant invention provides an airplane design mainly to eject rearward the high-speed exhaust gas from the engine of the airplane to flow through the upper surface of the wing, such that the forward propulsion forcing can be obtained via rearward ejecting the high-speed exhaust gas to push the air rearward, and also larger uplift forcing induced by a larger velocity difference vertically across the wing can be obtained to ascend the airplane at the same time. This velocity difference is generated because the air over the wing is accelerated by the ejected high-speed exhaust gas, but the air below the wing stays the same velocity, such that a bigger velocity difference is directly produced vertically across the wing, and thus more uplift forcing can be provided to ascend the airplane.

公开(公告)号：US20210339879A1

公开(公告)日：2021-11-04

申请号：US17366749

申请日：2021-07-02

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Andrew Breeze-Stringfellow ,  Darek Tomasz Zatorski ,  Dominic Barone

IPC: B64D27/24 ,  B64D29/04 ,  B64C3/10 ,  B64C29/00 ,  B64D27/08 ,  B64C3/32 ,  B64D35/02 ,  B64C3/38 ,  B64D33/04 ,  B64D31/06

Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.

公开(公告)号：US11084595B2

公开(公告)日：2021-08-10

申请号：US16042487

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Kurt David Murrow

IPC: B64D27/24 ,  B64C29/00 ,  B64D29/04 ,  B64C3/10 ,  B64D27/08 ,  B64C3/32 ,  B64D35/02 ,  B64C3/38 ,  B64D33/04 ,  B64D31/06 ,  B64D27/02 ,  B64D27/26 ,  H02K7/18

Abstract: An aircraft defining a vertical direction and a transverse direction. The aircraft may include a fuselage, a wing extending from the fuselage, and a hybrid-electric propulsion system. The hybrid-electric propulsion system may include a power source, a plurality of vertical thrust electric fans arranged along the wing and driven by the power source, and a forward thrust propulsor. The power source may include a combustion engine and an electric generator. The combustion engine may also define a flowpath for exhausting combustion gases. The forward thrust propulsor may be selectively or permanently mechanically coupled to the combustion engine. The forward thrust propulsor may include a propulsor fan having a plurality of fan blades arranged outside of the flowpath of the combustion engine for exhausting combustion gases.