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Matches 1 - 50 out of 1,508

Document Document Title
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 ...  
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
WO/2020/180368A3
An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.  
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...  
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...  
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...  
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...  
WO/2020/188200A3
The invention relates to a nacelle (10A) for an aircraft bypass turbomachine (100), comprising: •an annular envelope (11) extending about a longitudinal axis (104), • a thrust reverser (13) comprising: • an annular movable cowl (14...  
WO/2020/180376A3
An aircraft includes a fuselage defining a longitudinal axis between a forward end and a aft end. At least one airfoil is laterally extending from the fuselage defining an airfoil axis. An electrical system has an electric storage. The e...  
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...  
WO/2020/216713A1
The present application relates to an air intake (2) for a turbojet engine nacelle comprising an annular structure (21, 22) and a rear bulkhead (23), the annular structure (21, 22) comprising at least one portion (21A) of an outer shroud...  
WO/2020/217027A1
The invention relates to an air intake for an aircraft engine nacelle, the air intake comprising a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, a front mounting flange conf...  
WO/2020/217025A1
The invention relates to an air intake (3) for a nacelle (1) for 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 wa...  
WO/2020/216712A1
The invention relates to an air intake (1) of a turbojet engine nacelle comprising an annular structure (110) including an outer fairing (100) defining an aerodynamic outer surface and an inner fairing (102) defining an aerodynamic inner...  
WO/2020/212225A1
A process for using an air input (2) of a turboreactor nacelle (1) of an aircraft, comprising an air input lip (23) which comprises at least one fixed portion and at least one portion (3, 3', 4, 4', 5, 5', 6, 6', 7) which can be moved be...  
WO/2020/212224A1
An aircraft turbojet engine (1) extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake (2) which comprises at least one deflection member (3, 4, 5) movably mounted ...  
WO/2020/212226A1
An aircraft turbojet engine (1) comprising a fan (11) configured to provide a reverse thrust and a nacelle comprising an air intake (2), the air intake (2) comprising at least one circulation duct (3) in the annular cavity (20) opening, ...  
WO/2020/212228A1
Disclosed is a method for using an aircraft turbojet engine (1) comprising an air inlet (2) comprising a plurality of rectifier vanes (3), each rectifier vane (3) being mounted such that it can move between a retracted position to assist...  
WO/2020/201652A1
The invention concerns a method for monitoring at least one aircraft engine, said method comprising an acquisition (100) depending on first and second sets of measurements of respectively endogenous and exogenous variables. The method al...  
WO/2020/201033A1
The invention concerns a method for manufacturing a structural surface heat exchanger of preset or left-hand final shape (10) for an aircraft, comprising the steps of forming (E1), shaping (E2; E3) and assembling (E4), by welding or braz...  
WO/2020/201658A1
The invention relates to an air inlet duct (60) for a nacelle (26) of an aircraft propulsion assembly (10), this duct (60) comprising an annular body (50) and an annular air inlet lip (40) comprising two coaxial annular walls (41, 42), i...  
WO/2020/187345A1
The invention relates to an aircraft (3) having at least one wing (32) on which an aircraft propulsion device is arranged which has at least one heat engine (I), in particular a gas turbine (10), and an exhaust gas passage (21) for guidi...  
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...  

Matches 1 - 50 out of 1,508