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WO/2021/222528A1 |
An aircraft nacelle has a first and second heat exchanger section to cool aircraft during different modes. Additionally, a fan and other components are configured to maximize efficiency and cooling capacity during a plurality of operatin...
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WO/2021/217545A1 |
Disclosed is an unmanned aerial vehicle, comprising a mechanism component. The mechanism component is used for bearing electronic devices of the unmanned aerial vehicle, the mechanism component is provided with a containing cavity (10) u...
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WO/2021/220154A1 |
An aircraft (1) with a motor bay (8) is described; a motor system (6) with a discharge duct (17); a heat exchanger (20) arranged outside said motor system (6); a first air intake (25); a first duct (26) along which the heat exchanger (20...
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WO/2021/205126A1 |
Removable closure member (50) configured to close a female portion (40) received in an external opening (16b) formed in the external surface (16) of a nacelle (10) for an aircraft engine, the female portion (40) comprising at least one a...
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WO/2021/183813A1 |
An injector head for an anti-icing system may comprise a body configured to receive a pressurized gas, wherein the body is configured to provide the pressurized gas through a bulkhead into an interior volume of a D-duct, a first nozzle c...
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WO/2021/165052A1 |
A shell and tube type heat exchanger comprising a shell and a tube arrangement within the shell. The tube arrangement comprises a flow tube. The flow tube furcates at a plurality of nodes along its length. The shell and tube type heat ex...
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WO/2021/152318A1 |
Disclosed is a flying vehicle propulsion system comprising a propulsor, a drive system and a heat exchanger. The drive system is arranged to drive the propulsor and the heat exchanger is arranged to thermally regulate at least part of th...
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WO/2021/138538A1 |
A method of reducing noise from a high-speed, including supersonic, jet, the method includes providing the high-speed or supersonic jet in a longitudinal flow direction; and inducing a rotation of a swirl layer of the high-speed or super...
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WO/2021/133206A1 |
The invention relates to aeronautical engineering, more particularly to cooling systems for engines of helicopter aerial vehicles, inter alia, for internal combustion engines of unmanned aerial vehicles. The system includes an engine coo...
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WO/2021/132038A1 |
A helicopter transmission cooling structure comprises: a transmission including a transmission mechanism that shifts a speed of rotational power input from a motor and outputs the shifted rotational power, and a housing that contains the...
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WO/2021/115660A1 |
The invention relates to a propulsion system (150) comprising a nacelle (202) with an air channel (208) along a longitudinal direction X, an electric motor (108), the output of which drives a propeller (110), and a fuel cell (250) compri...
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WO/2021/064374A9 |
A propulsion management system for an aircraft, an aircraft comprising such a propulsion management system and a method of decelerating an aircraft. The aircraft comprises an air propulsion system having one or more propellers. The propu...
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WO/2021/110618A1 |
The invention relates to a superconducting flux barrier electric motor, which comprises at least one armature (2) and at least one inductor (3), one of the armature or the inductor housing at least one rotor and at least one superconduct...
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WO/2021/106548A1 |
A multi-rotor helicopter comprises a fuselage serving as a main body, and a plurality of fan units that cause the fuselage to lift. Each of the fan units has a fan frame connected to a support arm integrated with the fuselage, and a firs...
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WO/2021/106549A1 |
This multi-rotor helicopter has a fuselage and a plurality of fan units. Each of the fan units is equipped with a circular fan frame, a rotating blade, and a drive-system cooling unit. Each drive-system cooling unit has: an accommodation...
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WO/2021/087482A1 |
A heating system is configured to produce heated fluid. The system includes a source of primary fluid, a diffusing structure comprising an outlet structure out of which the heated fluid flows, at least one conduit coupled to the source a...
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WO/2021/074513A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion forming an inlet section of...
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WO/2021/074515A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet secti...
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WO/2021/074643A1 |
The present invention relates to a fluid release system for a fuel cell, the system comprising: a conduit for communicating water from the fuel cell to one or more outlets; and, a water discharge arrangement arranged to selectively relea...
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WO/2021/074514A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, in particular a vertical take-off and landing (VTOL) aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (...
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WO/2021/074609A1 |
An air inlet for an aircraft nacelle comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface ...
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WO/2021/074535A1 |
The invention relates to an assembly for a turbomachine, comprising: - a nacelle comprising an inlet lip which defines an air inlet, and - a device for modifying the geometry of the air inlet, comprising: - a first spout, and - a second ...
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WO/2021/073956A1 |
The invention relates to a vehicle (1) comprising: - a fairing (2); - at least one propeller, characterized in that the fairing (2) defines a fluid chamber having a main opening that opens onto a lower face (22) of the fairing (2) so as ...
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WO/2021/074536A1 |
The invention relates to a method for repairing a turbomachine air intake lip comprising a damaged region of which the shape differs from the initial shape of the lip, characterized in that it comprises: - a step (41) of identifying the ...
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WO/2021/069834A1 |
The invention concerns an electric motor nacelle (1) for a vertical take-off and landing (VTOL) aircraft, comprising: - a fairing (10) in which an electric motor (20) is housed equipped with at least one propeller (22) extending outwards...
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WO/2021/064396A1 |
A thermal management system is provided for managing the temperature of one or more components in an aircraft nacelle. The thermal management system comprises an inlet opening into the nacelle, an outlet opening out of the nacelle, a gas...
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WO/2021/056194A1 |
An unmanned aerial vehicle (UAV) (10), comprising: a housing (100), a flight control motherboard (700), a battery (600), and an electronic speed control (ESC) module (401). The flight control motherboard (700), battery (600), and ESC mod...
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WO/2021/051243A1 |
A method for installing an air inlet duct protective cover of an aircraft engine, comprising the following steps: a. inflating a protective fabric cover; b. the protective cover supporting a certain prefabricated outer shape to achieve t...
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WO/2021/032918A1 |
Internal structure (22) for a nacelle (18) of a turbomachine (10), the structure being designed to surround at least one portion of a compartment capable of receiving a gas generator (14) of the turbomachine (10), the internal structure ...
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WO/2021/032534A1 |
Disclosed is an air intake (1) of an aircraft turbine engine nacelle comprising a lip (2), a downstream portion (3) and an internal partition (5) separating the lip (2) and the downstream portion (3), the lip (2) delimiting an annular re...
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WO/2021/019247A1 |
There is described herein a lattice framework for structural insulated panels (SIPs), wherein the SIPs each comprise a first facesheet and a second facesheet, the lattice framework comprising (a) a plurality of surface struts configured ...
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WO/2021/019288A1 |
A reinforced structural insulated panel (20) that comprises an expanded cork core (30), a pair of facesheets (24, 26) and a fibre reinforced polymer lattice framework (36). The core (30) is sandwiched between the facesheets (24, 26). The...
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WO/2021/009433A1 |
Aircraft propulsion unit comprising a fuselage (10) extending along a longitudinal axis (X) and incorporating an internal chamber, at least one ducted engine (20) attached to the fuselage (10) and comprising an air inlet section (20a), t...
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WO/2021/007761A1 |
A method for mounting a protective fabric cover at an air inlet of an aircraft engine, comprising the following steps: a. inflating a protective fabric cover; b. the protective fabric cover supporting a certain prefabricated outer shape ...
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WO/2021/004735A1 |
The invention relates to a soundproofing coating with a cellular structure consisting of several structures (11) connected in a transverse direction (D2), each formed by connecting a first longitudinal strip (4) with a second longitudina...
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WO/2021/003551A1 |
The engine is adapted to generate thrust or designed to generate torque includes a combustor, the combustor generates an exhaust gas flow to push the rotor blades of a rotor in a rotor housing, the exhaust gas flow rotates the rotor, sha...
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WO/2021/007216A1 |
Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan...
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WO/2020/257883A1 |
A muffler (40) devised particularly for use with an engine of the type used on unmanned aerial vehicles (UAVs), and a UAV (10) having an engine (30) fitted with the muffler (40). The muffler (40) comprises a body (51) having an interior ...
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WO/2020/251216A1 |
An unmanned aerial vehicle according to various embodiments of the present invention comprises: a main body; at least one connection frame connected to the main body; at least one propeller part connected to the connection frame; a drivi...
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WO/2020/245388A1 |
The invention relates to an aircraft (1), in particular an aircraft with support surfaces (11, 12), comprising a hull (10) for receiving at least one pilot and/or a payload, in particular air freight and/or at least one passenger, and at...
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WO/2020/245390A1 |
The invention relates to an aircraft and to a method for operating an aircraft (1), in particular an aircraft with support surfaces (11, 12), comprising a hull (10) for receiving at least one pilot and/or a payload, in particular air fre...
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WO/2020/245379A1 |
The invention relates to an aircraft (1) and to a method for operating an aircraft (1), in particular an aircraft with support surfaces (11, 12), a hull (10) for receiving at least one pilot and/or a payload, in particular air freight an...
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WO/2020/239470A1 |
The invention relates to an air intake lip (2a) of an aircraft turbomachine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip (2a) extending annularly about the X-axis and having an i...
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WO/2020/240110A1 |
The invention concerns a device (10) for attaching a lifting tool (100) to an aircraft element such as a nacelle thrust reverser door (200), the device comprising: a threaded screw (12) having a longitudinal axis (z) and comprising a dis...
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WO/2020/239870A1 |
Disclosed is an aircraft propulsion assembly (1) comprising a nacelle and a turbojet engine, the nacelle comprising an outer casing (5) comprising fan cowls (4) and the turbojet engine comprising at least one fan casing (6, 6'), the fan ...
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WO/2020/229081A1 |
The invention relates to a method for joining a power semiconductor component (1.1) to a heat pipe (2), wherein, during joining, the external pressure (p2) acting on the heat pipe (2) is changed proportionally to the internal pressure (p...
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WO/2020/227837A1 |
An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacell...
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WO/2020/229778A1 |
The present intention relates to a method for resetting the static pressure model (mod_Ps3(PCN25R)), called "Ps3 model", upstream of a combustion chamber in a turbine engine comprising a compressor (3), the Ps3 model being used to arbitr...
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WO/2020/225563A1 |
An acoustic panel for an aircraft comprising: a sound attenuating sheet comprising a plurality of cavities, a sound attenuating sheet having a first surface, a second surface opposite to the first surface and an end surface connecting th...
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WO/2020/217026A1 |
The invention relates to an air intake (3) for a nacelle (1) of an aircraft engine (6), the air intake (3) comprising a front lip (31) connecting a substantially cylindrical internal wall (32) and a substantially cylindrical external wal...
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