公开(公告)号：US20240270404A1

公开(公告)日：2024-08-15

申请号：US18440997

申请日：2024-02-14

Applicant: Continuum Dynamics, Inc.

Inventor： Glen R. Whitehouse ,  Todd R. Quackenbush

IPC: B64D27/31 ,  B64C11/20 ,  F01D15/10

CPC classification number: B64D41/007 ,  G06F30/15 ,  G06F30/28 ,  B64F5/00 ,  F03D1/0633 ,  F03D9/322 ,  F05D2220/76 ,  F05D2260/81

Abstract: A method of modeling a turbine mounted behind an aircraft wing for providing a specified proportion of a propulsive force in the aircraft flight direction to an amount of power generated by the turbine when driven by the airflow trailing the wings. The turbine converts a portion of the otherwise wasted energy in the rotational vortices trailing the aircraft wings into thrust that reduces aircraft drag while also providing electricity to power electrical systems on the aircraft. The method is also capable of modeling a turbine construction that will use the energy in the wake solely to generate electricity without increasing drag on the aircraft or solely to reduce drag without generating electricity. In one embodiment, the method saves computation time by using a recursive routine to define a preliminary turbine configuration based on an idealized vortex model and then matches it to the flow trailing an actual aircraft wing.

公开(公告)号：US20240132201A1

公开(公告)日：2024-04-25

申请号：US18348239

申请日：2023-07-05

Applicant: Thomas Norman Hesse

Inventor： Thomas Norman Hesse

IPC: B64C11/20 ,  B64C11/30 ,  F01D7/00 ,  G01C21/16

CPC classification number: B64C11/20 ,  B64C11/30 ,  F01D7/00 ,  G01C21/16 ,  F05D2260/70

Abstract: A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.

公开(公告)号：US11873096B1

公开(公告)日：2024-01-16

申请号：US17667648

申请日：2022-02-09

Applicant: Cornerstone Research Group, Inc.

Inventor： S. Alan Spring ,  Cory Kays ,  Joshua Nieman ,  Bryan Pelley

IPC: B64C9/24 ,  B64C11/02 ,  B64C11/20

CPC classification number: B64C9/24 ,  B64C11/02 ,  B64C11/20

Abstract: An aircraft wing and propulsion system includes a leading-edge device positioned at the leading edge of an aircraft wing and one or more propulsors affixed to the main body of the aircraft wing. The leading-edge device includes a moveable slat affixed to the aircraft wing with an extension mechanism such that the moveable slat is translatable between a closed position abutting a main body of the aircraft wing and an open position extended from the main body of the aircraft wing to form a gap. An associated method of operating the same during takeoff and landing includes extending the moveable slat to expose the propulsors on the aircraft wing and operating the propulsors during take-off or landing of the aircraft to provide increased power and lift for the aircraft.

公开(公告)号：US11863040B2

公开(公告)日：2024-01-02

申请号：US17057465

申请日：2019-05-21

Applicant: Research Foundation for the State University of New York

Inventor： Adrian Ieta

IPC: H02K44/06 ,  F21Y115/10 ,  B64C23/00 ,  H01T23/00 ,  B64C11/20 ,  H02K99/00 ,  B63H7/02 ,  F04D13/06

CPC classification number: H02K44/06 ,  B63H7/02 ,  B64C11/20 ,  H02K99/20 ,  B64C23/005 ,  F04D13/06 ,  F21Y2115/10 ,  H01T23/00

Abstract: An electrohydrodynamic rotary system and related method that include at least one rotary device comprising a hub portion, an axis of rotation, and at least one blade extending radially from the hub portion. The system includes at least one electrically conductive rotary electrode emitter coupled to the at least one blade proximate to the back edge, and at least one electrically conductive counter electrode positioned proximate to the at least one rotary device in a spaced relationship. The system further includes an electrical system that applies an electric potential difference between the at least one electrically conductive rotary electrode emitter and the at least one electrically conductive counter electrode that generates corona discharges from the at least one rotary electrode that form flows of ionic wind that rotate the at least one rotary device about the axis of rotation in a first direction.

公开(公告)号：US20230113569A1

公开(公告)日：2023-04-13

申请号：US17963271

申请日：2022-10-11

Applicant: Jesse Antoine Marcel

Inventor： Jesse Antoine Marcel

IPC: B64C11/20 ,  B64C29/00 ,  F01D13/00 ,  H02K16/02 ,  H02K11/30 ,  H02K1/16

Abstract: An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

公开(公告)号：US11524765B2

公开(公告)日：2022-12-13

申请号：US16761179

申请日：2018-11-02

Applicant: Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V.

Inventor： Malo Rosemeier ,  Alexandros Antoniou

IPC: G01M5/00 ,  F03D17/00 ,  G01N3/08 ,  B64C11/20 ,  B64C11/04 ,  B64C11/30 ,  G01N3/04

Abstract: The invention relates to a test stand comprising a support (19, 25) which is moveably connected to a wall (18, 18′, 18″), a base, a frame (26) of the test stand or another part of the test stand and can be moved on a predetermined path; an actuator (22) which is connected to the support and by means of which the support (19, 25) that can be moved on the predetermined path, two clamping devices (13) respectively comprising a ball joint, wherein one of the two clamping devices (13) is seemed to the support (19, 25) and the other of the two clamping devices (13) is arranged in an axis (10) with the first of the two clamping devices (13), such that a test body (1) is clamped between the two clamping devices (13) on outer surfaces of the test body and can be maintained by the clamping devices (13), and a test force exerted by a test body by moving the support (19, 25) through the first of the two clamping devices (13) acts essentially along the axis (10). The test body is fixed by means of an elastic element (23) in order to limit a rotation of the test body about the axis (10).

公开(公告)号：US20220251958A1

公开(公告)日：2022-08-11

申请号：US17729159

申请日：2022-04-26

Applicant: Ratier-Figeac SAS

Inventor： Pascal AMAT

IPC: F01D5/14 ,  B64C11/20 ,  B64C11/26 ,  B23P15/04 ,  B65H51/00 ,  F01D5/28

Abstract: A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yam extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

公开(公告)号：US20220135195A1

公开(公告)日：2022-05-05

申请号：US17577587

申请日：2022-01-18

Applicant: Sharrow Engineering LLC

Inventor： Gregory Charles Sharrow

IPC: B63H1/26 ,  F04D29/38 ,  B64C11/18 ,  B64C11/00 ,  F01D5/14 ,  F02K3/06 ,  F03D1/06 ,  B64C11/20 ,  B64C11/16

Abstract: A propeller having a plurality of blades extending radially outward from a hub, the blades forming a loop. Each loop having an intake portion, an exhaust portion and a tip portion extending radially outward from the hub and a gap between the intake root and the exhaust root. The tip portion of each of the blades is 30%-75% of the blade, the tip portion beginning at a first deviation from zero of the roll value and extending to 90 degrees, wherein roll value is zero in a plane parallel to the hub axis, and wherein the blades have a vertical angle between −45 degrees and 45 degrees throughout.

公开(公告)号：US11286782B2

公开(公告)日：2022-03-29

申请号：US16213653

申请日：2018-12-07

Applicant: General Electric Company

Inventor： Gregory Carl Gemeinhardt ,  Douglas Duane Ward ,  David William Crall ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F01D5/28 ,  B23P15/04 ,  B64C11/20 ,  B29D99/00

Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.

公开(公告)号：US20210253482A1

公开(公告)日：2021-08-19

申请号：US17096694

申请日：2020-11-12

Applicant: Northrop Grumman Systems Corporation.

Inventor： Benjamin W.C. Garcia ,  David R. Nelson

IPC: C04B35/571 ,  B64C1/00 ,  C04B35/80 ,  B64C3/26 ,  B64C1/12 ,  C04B35/82 ,  B64C1/06 ,  B64C11/20 ,  C04B35/628 ,  F02K9/08 ,  F01D5/28 ,  F02K9/34 ,  C04B35/515

Abstract: A preceramic resin formulation comprising a polycarbosilane preceramic polymer, an organically modified silicon dioxide preceramic polymer, and, optionally, at least one filler. The preceramic resin formulation is formulated to exhibit a viscosity of from about 1,000 cP at about 25° C. to about 5,000 cP at a temperature of about 25° C. The at least one filler comprises first particles having an average mean diameter of less than about 1.0 μm and second particles having an average mean diameter of from about 1.5 μm to about 5 μm. Impregnated fibers comprising the preceramic resin formulation are also disclosed, as is a composite material comprising a reaction product of the polycarbosilane preceramic polymer, organically modified silicon dioxide preceramic polymer, and the at least one filler. Methods of forming a ceramic matrix composite are also disclosed.