| Document |
Document Title |
|
WO/2023/222549A1 |
The invention relates to a de-icing system configured to be mounted on a surface (3A, 3B) of a mechanical part (1) to be de-iced, said system comprising at least: - a piezoelectric actuator (9), - a fastening device (11) configured to fa...
|
|
WO/2023/212788A1 |
The present patent application to a wing tip thruster rotation system describes a system for rotating wing tip thrusters (EDF or turbofan engines), belonging to the field of aircraft equipment, more precisely for use in aircraft of the c...
|
|
WO/2023/209289A1 |
The invention relates to a propeller blade or airfoil (10) for a turboprop engine, made from composite material and comprising a matrix-densified fibrous reinforcement, the propeller blade or airfoil comprising, in a spanwise direction (...
|
|
WO/2023/208829A1 |
A propulsion system (1A; 1B), more particularly for an aircraft (2), comprises: a number of rotors (12), which are disposed in at least four sectors (Q1-Q4), each of the rotors (12) being assigned to a pair (P) of rotors (12) which are d...
|
|
WO/2023/209288A1 |
A turbojet engine fan blade or vane (10) made of composite material comprises a fibrous reinforcement densified by a matrix, the fan blade or vane comprising, in the direction of its span (DL), a root (12) and an aerodynamic profile (11)...
|
|
WO/2023/209312A1 |
The invention relates to a propeller blade or airfoil (10) for a turboprop engine, made from composite material and comprising a matrix-densified fibrous reinforcement, the propeller blade or airfoil comprising, in a longitudinal directi...
|
|
WO/2023/209339A1 |
There is provided an acoustic black hole comprising: in a first axis, a variation from a first characteristic to a second characteristic, along a line; in a second axis different to the first axis, a variation from a first characteristic...
|
|
WO/2023/209338A1 |
There is provided an acoustic black hole comprising: in a first axis, a taper from a first thickness to a second thickness, along a line; in a second axis perpendicular to the first axis, and away from the line, one or more regions of di...
|
|
WO/2023/203475A1 |
The invention concerns an airfoil (40) comprising a front leading edge le, a rear trailing edge te, a mean line ml and a thickness t. The airfoil further comprises: a front portion (42) in which the thickness increases from the leading e...
|
|
WO/2023/199066A1 |
Examples provide an electric propulsion system; the system comprising a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, only a single one fan stage comprising a fan bearin...
|
|
WO/2023/198979A1 |
The invention relates to a turbine engine motor having an unducted fan, the motor comprising a plurality of guide vanes (10) made of composite materials. Each of the guide vanes is intended to be fixed only to an inner fixed structure (2...
|
|
WO/2023/198987A1 |
The invention relates to a module (3) having a longitudinal axis (X) and comprising a hydraulic actuator (46), and a pump (54) for supplying the hydraulic actuator (46) with fluid, the pump comprising axial pistons (54c) intended to be m...
|
|
WO/2023/199071A1 |
Examples provide electric propulsion systems; such a system comprising: a. a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, b. at least one fan stage comprising a fan bea...
|
|
WO/2023/196272A1 |
A coaxial rotor system includes a center mast non-rotatably disposed at and extending from a helicopter. A rotation axis extends along the center mast. An inner mast is disposed along the center mast and is rotatable about the rotation a...
|
|
WO/2023/175265A1 |
The present invention relates to an aircraft part comprising: a composite material structure comprising a fibrous reinforcement embedded in a matrix; a heating element (9) configured to heat the part, the heating element (9) being embedd...
|
|
WO/2023/170357A1 |
The invention relates to an aeronautical propulsion unit (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), wh...
|
|
WO/2023/170358A1 |
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each down...
|
|
WO/2023/159004A2 |
An apparatus for attenuating or counterbalancing external load fluctuations on a propeller driver machine is disclosed. In one embodiment a set of non-circular gears coupled to a rotor shaft or to the gearbox of the machine are further c...
|
|
WO/2023/152746A1 |
An aircraft, comprising: a fuselage; two wings mounted to the sides of the fuselage, extending laterally; a pusher propeller, statically mounted to the fuselage, wherein a rotational axis of the pusher propeller is parallel to a longitud...
|
|
WO/2023/149391A1 |
The present invention addresses the problem of providing a rotary wing that is excellent in light weight, rigidity, fatigue characteristics, and dimensional accuracy, and in particular, has excellent fatigue characteristics, that is, dur...
|
|
WO/2023/144157A1 |
An aircraft propeller drive system for an aircraft is disclosed. The aircraft has a propeller driven by an intermittent combustion internal combustion engine via the propeller drive system. The propeller drive system has: a torsion bar h...
|
|
WO/2023/142204A1 |
Provided in the present invention is a helicopter rotor manipulation device based on the pitch varying of a hydraulic torsion tube. The helicopter rotor manipulation device comprises a blade structure, a variable-pitch clamp system and a...
|
|
WO/2023/144843A1 |
This device is a closed liquid system inside two hollow metal arms that are connected in one direction. When rotating, by passing one arm at an angle perpendicular to the horizon surface upwards, the movement of the liquid from the secon...
|
|
WO/2023/146938A2 |
An aerial vehicle is disclosed including a rotor assembly having a downstream blade and a upstream blade. The downstream and upstream blades are configured to rotate about an axis of rotation. The downstream blade may be arranged extendi...
|
|
WO/2023/139332A1 |
The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a directi...
|
|
WO/2023/135375A1 |
The present invention relates to an application head (1) for automatically applying fibres, which application head comprises at least: - an application roller (3) that is designed to apply fibres to a mould (F), which application roller ...
|
|
WO/2023/123682A1 |
The present invention provides an aircraft having a double-row wheel counter-rotating pneumatic effect, comprising a wing plate, rotating assemblies, and a landing gear, wherein the wing plate is connected to a position directly above ea...
|
|
WO/2023/124378A1 |
A propeller and an aircraft. The propeller comprises a propeller blade (1) and a spoiler portion (2). At least part of the spoiler portion (2) protrudes out of a suction surface of the propeller blade (1), and the spoiler portion (2) ext...
|
|
WO/2023/118686A1 |
The invention relates to a turbine engine module, comprising: - a fan (3) intended to be rotated by a fan shaft (32) and comprising a plurality of variable-pitch blades (30); and - a pitch change system comprising a control means (52) co...
|
|
WO/2023/122717A1 |
A method of operating an aircraft including takeoff of an aircraft; transitioning the aircraft to a forward flight configuration by increasing an amount of forward propulsive force generated by a propeller assembly from equal to or less ...
|
|
WO/2023/118688A1 |
The invention relates to a device (94) for transferring fluid, for a turbine engine (1) having a longitudinal axis X, which device includes a stator part (96) intended to be connected to a stator apparatus (98, 99) of the turbine engine ...
|
|
WO/2023/118725A1 |
The invention relates to a hydraulic control circuit (57) of a dual-action orientation actuator (61) for the orientation of fan blades of a turbojet engine, comprising an oil reservoir (63), a variable-displacement axial piston pump (26)...
|
|
WO/2023/118689A1 |
The invention relates to a turbomachine module, having: - a fan comprising variable-pitch blades, - a speed reducer (34) connected to a fan shaft guided in rotation by two guide bearings, - a system for changing the pitch of the blades t...
|
|
WO/2023/122109A1 |
An aircraft has port side and starboard side propeller blades that each have a portion of the blade hidden or overlapping with the fuselage. This hidden or overlapping blade may extend into a slot of the fuselage. The advancing or retrea...
|
|
WO/2023/118724A1 |
The invention relates to a hydraulic control circuit (57) of a dual-action orientation actuator (61) for the orientation of fan blades of a turbojet engine, comprising an oil reservoir (63), a variable-displacement axial piston pump (26)...
|
|
WO/2023/111438A1 |
The invention relates to a hydraulic assembly (450) for an aircraft engine, the assembly comprising: - a pump (54) comprising a housing (54a) and a rotor (54b) arranged inside the housing (54a), the housing (54a) having at least one hydr...
|
|
WO/2023/114523A1 |
Method and tools for manufacturing core foam sections for a propeller is disclosed. In an embodiment, a method comprises wrapping a first adhesive film around pre-drilled rods; placing the rods into a first mold using placement features;...
|
|
WO/2023/111476A1 |
A method for managing the torque of an aircraft turbomachine comprising a fan (6) or a propeller of variable pitch connected to a turbine (5) by a shaft (7) and a reduction gear (8), and an electric generator (9) connected to the shaft (...
|
|
WO/2023/113651A1 |
The invention relates to nautical and aeronautical design, and more particularly to flow propellers for use in water or air, and can also be used as a generator for converting water and air flows into electrical energy. A flow propeller ...
|
|
WO/2023/108817A1 |
The present invention relates to the technical field of flight, and provides a propeller, a power assembly, and an aircraft, used for solving the technical problems of high noise and an increase in resistance caused by the fact that blad...
|
|
WO/2023/099832A1 |
The invention relates to a method (100) for manufacturing a blade, the method comprising preparing (102) a spar preform arranged in a first mold, the spar preform comprising a core and a root; a first injection step (104) of injecting a ...
|
|
WO/2023/102573A1 |
Disclosed are embodiments including an electric propulsion system for vehicles, for example aircraft (10), that can comprise a propulsion fan (26) and a plurality of electrical machines (22) connected at respective positions to an elonga...
|
|
WO/2023/099835A1 |
This control device for a propulsion system, which comprises means for computing a blade-pitch setpoint for at least one propeller of the propulsion system, the computing means using a predictive model of the performance of the propeller...
|
|
WO/2023/096622A1 |
The invention relates to an unmanned aerial vehicle (1) arranged to self-destruct near a target (H), comprising a body (10), foldable wings (20) that comprise the wing body (21 ) connected to the body (10) and flaps (22) partially movabl...
|
|
WO/2023/092183A1 |
Embodiments relate generally to systems and VTOL aerial vehicles. An example central server system comprises: at least one central server system processor; and central server system memory storing central server system program instructio...
|
|
WO/2023/089274A1 |
Module for mounting a turbomachine fan blade, comprising: - a blade force absorption device (24), - a blade carrier (22) capable of pivoting around a radial axis (A) and configured to be engaged axially inside the device (24), the carrie...
|
|
WO/2023/091481A1 |
A satellite having a longitudinally elongated body and being capable of operating in the thermosphere. The satellite can be powered by an electric rocket engine, and includes a remote sensing system configured to obtain images of Earth. ...
|
|
WO/2023/091389A1 |
Various implementations include a rotor control device including a shaft extending along a rotational axis, a hub, first and second pitch control components, and a swashplate. The hub has a hub axis and is hingedly coupled to the shaft s...
|
|
WO/2023/085198A1 |
The present invention provides a blade in which the specific rigidity of a flap part is further increased. This blade has a thick body part and a thin flap part integrally formed in the rear end of the body part. The flap part has a skin...
|
|
WO/2023/083813A1 |
The reversible hydraulic pump (12) for setting the propellor pitch (3) of a turboprop (2) comprises two cylinders (20, 21) connected by a transmission shaft (28). The first and second cylinders (20, 21) are connected to the transmission ...
|
