Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 1,469

Document Document Title
WO/2020/180377A1
A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the...  
WO/2020/180366A1
A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected to receive rotational input power from each of the heat en...  
WO/2020/180375A1
A power plant a for an aircraft having a hybrid-electric propulsion system including a nacelle body including therein an electric motor directly connected to a gearbox for driving a propeller, wherein the gearbox is connected directly to...  
WO/2020/138076A1
An outer plate cooling system is provided with: an outer shell having an outer plate, an inner plate placed inside the outer plate, and a heat insulating layer placed between the outer plate and the inner plate; a cooling chamber which i...  
WO/2020/138075A1
This outer panel cooling system comprises: an outer shell having an outer panel and an inner panel; a heat source chamber provided on the inner side of the inner panel; a cooling path provided between the outer panel and the inner panel,...  
WO/2020/136415A2  
WO/2020/122077A1
[Problem] To provide a motor cooling structure capable of improving cooling efficiency when cooling a motor that has reached a high temperature. [Solution] In the motor cooling structure equipped with a motor disposed on a board and a pr...  
WO/2020/115960A1
[Problem] To provide a pressure variation absorbing structure in which it is possible to prevent degradation in pressure variation absorbing performance caused by an air current on a surface and to prevent deviation of a resonance freque...  
WO/2020/113110A1
An aerodynamic flow control system in proximity to the nacelle inlet to provide "virtual" shaping of the nacelle's flow surface. The aerodynamic flow control is adjustable so that it can be continuously and adaptively optimized for a ran...  
WO/2020/109482A1
The invention relates to a method for customized production of replacement structure parts (40) from a blank (29) for replacing damaged structure components which are provided with a multiplicity of holes for attachment to a receiving st...  
WO/2020/091629A1
A twin supersonic convergent air inlet is a supersonic air inlet consisting of two joined, mirror identical parallel supersonic convergent scoop mixed compression air inlets for two engines, said air inlets being fastened to one another ...  
WO/2020/090879A1
[Problem] To provide a drone that operates using a fuel cell as a power source and can remain highly safe even during autonomous flight. [Solution] The present invention comprises: a flight control unit 21 that generates thrust by operat...  
WO/2020/084527A1
A vehicle (1) provided with an engine (2), at least one air intake (4) through which the engine (2) takes in the external air needed to operate, and an air filter (9) arranged downstream of the air intake (4). The air filter (9) presents...  
WO/2020/075091A1
A vehicle (1) provided with an engine (2), at least one air intake (4) through which the engine (2) takes in the external air needed to operate, and an air filter (9), which is arranged downstream of the air intake (4). The air filter (9...  
WO/2020/072365A1
The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus (1400) that includes a probe (1410) affixed to an aircraft engine frame and having a shaft (1420) having a barb (1...  
WO/2020/052910A1
A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) confi...  
WO/2020/043993A1
The invention relates to a handling assembly (31) of a propulsion assembly, comprising a nacelle and an aircraft turbofan, characterized in that it comprises: - a handling envelope (35) covering at least half of the circumference of an o...  
WO/2020/031013A1
A heat exchanger (10) for a transmission unit of an aircraft (1) is described that comprises: a first module (23) defining a first feed path (P) for a first fluid to be cooled; a second module (33) defining a second feed path (T) for a s...  
WO/2020/016520A1
The invention concerns a method for manufacturing a composite panel, in particular in a turbomachine, characterised in that it comprises the following steps: a) producing a first wall, a second wall, a third wall and a fourth wall from c...  
WO/2020/008147A1
The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having...  
WO/2020/005387A1
An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted bo...  
WO/2020/001273A1
The present utility model relates to a heat dissipation structure and an unmanned aerial vehicle. The heat dissipation structure comprises: a housing; a heat dissipation fan provided inside the housing; and a first air inlet and a second...  
WO/2019/243119A1
The invention relates to a rear propulsion system (4) for an aircraft configured to ingest a boundary layer of said aircraft, the rear propulsion system (4) extending longitudinally along an X-axis, the rear propulsion system (4) compris...  
WO/2019/243117A1
The invention relates to a rear propulsion system (4) for an aircraft configured to ingest a boundary layer of said aircraft, the rear propulsion system (4) extending longitudinally along an X-axis, the rear propulsion system (4) compris...  
WO/2019/229337A1
The outlet (2) of a heat exchange circuit extending under a wall (1), such as a nacelle cowling of an aircraft engine, is divided into openings (7) in the form of parallel slots which are elongated in the longitudinal direction (X) and s...  
WO/2019/232060A1
A vehicle includes a main body and at least one wing coupled to the main body. A source of compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster having ...  
WO/2019/224499A1
The invention relates to an acoustic attenuation panel (1) for an aircraft jet engine nacelle, and to a method for manufacturing this panel. The panel (1) comprises a central cellular core interposed between an acoustic front skin (3) co...  
WO/2019/220038A1
The invention relates to an aircraft power architecture comprising a power transmission gearbox (12), located in a first compartment (30), a gas turbine (14), located in a second compartment (32) comprising a gas generator (18) and a fre...  
WO/2019/202515A1
A general mounting method for ducted fan propulsors is disclosed. This mounting method uses extremely slender stators that connect the duct ring to the propulsor which is mounted in the middle and drives the rotor, fan or propeller. The ...  
WO/2019/197224A1
A starting/generating system for an aircraft turbine engine, the starting/generating system comprising at least one brushless drive motor/generator (1), at least one control module (6) and at least one power module (7), the power module ...  
WO/2019/192750A1
An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel suppl...  
WO/2019/195189A1
A Helmholtz resonator having a plurality of resonator chamber modules formed into an array. The array is configured to dampen sound. A module of the plurality of resonator chamber modules includes a first chamber and a second chamber. Th...  
WO/2019/171000A1
The invention relates to an active device for attenuating acoustic emissions (8) from a turbojet of an aircraft, characterised in that the device comprises conduits (20) for the circulation of a pressurised air flow supplying rotating el...  
WO/2019/172808A1
´╗┐The invention relates to jet propulsors widely used, for example, in various transport vehicles and is intended for equipping transport vehicles moving in a three-dimensional liquid (for example, in water body) or gas (for example, in...  
WO/2019/166040A1
Disclosed is a method for reducing contrails during operation of an aircraft (100, 100') having a heat engine (10). The method comprises: bringing about condensation of the moisture contained in the exhaust gas (A) of the heat engine by ...  
WO/2019/158451A1
An acoustic damper (100) for a gas duct system (20), comprises a housing (1) comprising a first wall (2) and a second wall (3) opposite to and spaced from the first wall (2) so as to at least partly define a housing volume there between....  
WO/2019/158884A1
The invention relates to a nacelle for a turbomachine, the nacelle comprising an inner wall that is annular about a longitudinal axis of the nacelle, the annular inner wall being designed to surround at least part of the turbomachine, th...  
WO/2019/155175A1
The invention concerns a de-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle, characterised in that it comprises an embossed acoustic structure (32) that delimits a plurality of acoustic cells (34), ...  
WO/2019/146271A1
This superconductive cable according to one aspect of the present disclosure is for transmitting electric power among a plurality of electric power devices mounted on an aircraft. The superconductive cable is provided with: a heat insula...  
WO/2019/146270A1
A superconductive cable system according to one aspect of the present disclosure is for transmitting electric power among a plurality of electric power devices mounted on an aircraft. This superconductive cable system is provided with: a...  
WO/2019/135058A1
The invention relates to a structure (131) for the nacelle of an aircraft propulsion unit, comprising a first skin and stiffeners (3) arranged to hold acoustic treatment modules (4) against the first skin. Each acoustic treatment module ...  
WO/2019/115959A1
The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic t...  
WO/2019/110939A1
The invention relates to a method for manufacturing an abradable coating, which consists of depositing, on a substrate surface (12), a filament of a thermosetting material, while ensuring both a relative movement between the substrate an...  
WO/2019/110940A1
The invention relates to an acoustic coating in an ordered array of interconnected microchannels, for receiving, on a receiving surface, an incident acoustic wave in a direction Ac normal to said surface, said method consisting in: depos...  
WO/2019/110958A1
A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in wh...  
WO/2019/106304A1
The aircraft nacelle has a front portion comprising an inner wall (1) and an outer wall (2) joined by an annular front frame (3) to delimit a gas passage duct (V), the front frame being formed by a plurality of adjacent sheet metal frame...  
WO/2019/094726A1
An accelerated and/or redirected flow arrangement, optimally serving as a wildlife and/or debris excluder (WDE), is used in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough, e.g....  
WO/2019/094765A1
A system and method of an airflow control system for a vehicle is described herein. The airflow control system (100) includes an airflow housing (120) defining an airflow passageway (125) extending between a bypass opening (122) and an i...  
WO/2019/074860A1
A hydraulic propulsion system is disclosed which includes an input interface configured to receive mechanical power from a power source, a pressure source comprising one or more fixed or variable displacement pumps coupled to the input i...  
WO/2019/072980A1
The invention is concerned with a noise attenuation element arranged in use for connection to an air directing structure such as a wing flap. The element has a non-uniform lattice density across at least a portion of the body of the elem...  

Matches 1 - 50 out of 1,469