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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...
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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...
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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 ...
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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....
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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...
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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), ...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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....
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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...
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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...
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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...
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WO/2019/069302A1 |
An aerodynamic arrangement and method for providing a required air pressure coefficient at an area of location of an air port of an internal cooling system of a flying platform is described. The air port is selected from an air inlet por...
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WO/2019/063682A1 |
The invention relates to a method for propelling an aircraft. In order to obtain electric energy, fuel is combusted and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine, and the fuel...
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WO/2019/058109A1 |
In a method of manufacturing an electrothermal heater mat (3), there is provided a preform (7) which comprises a laminated stack of dielectric layers (51-56) which are made of thermoplastic material and include a central layer or group o...
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WO/2019/048772A1 |
The invention relates to a method for manufacturing a cellular core (34) for an acoustic panel (30), the cellular core (34) comprising at least one plurality of acoustic cells (36) and a plurality of de-icing channels (48) that extend lo...
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WO/2018/236626A1 |
Techniques are disclosed for cooling an unmanned aerial vehicle (UAV). In some examples, a heat sink is coupled to a portion of the UAV that is to be cooled. One or more heat pipes are coupled to the shim, and extend to one or more propu...
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WO/2018/234710A1 |
The disclosure relates to the field of acoustic treatment for aircraft turbojet engine nacelles. More specifically, it concerns an acoustic treatment device (6) in the form of an annular ring comprising several sections (61-66), each sec...
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WO/2018/232340A1 |
An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusin...
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WO/2018/223748A1 |
Disclosed is a duct fan, comprising: a duct (1) having a central axis, an air inlet and an air outlet being respectively located at an upper end and a lower end of the duct (1); a propeller hub shaft arranged on the central axis of the d...
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WO/2018/226268A1 |
A flight vehicle has an engine that includes air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes a bulged region that has at least one dimension, perpendicul...
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WO/2018/226269A1 |
A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an ...
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WO/2018/225706A1 |
A sound-absorbing panel to be used affixed to a jet engine of an aircraft, provided with: a resin core layer 20 having a first surface, a second surface disposed on the side opposite from the first surface, and multiple partitions extend...
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WO/2018/222844A1 |
A vertical take-off and landing (VTOL) rotary aircraft or helicopter (10) has eight propellers (42) in a quad propeller arm (34) configuration where each propeller arm (34) has two counter-rotating propellers (42). Folding propeller arms...
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WO/2018/169454A3 |
The invention relates to the field of aviation engines and aeroplane braking devices. A deflecting cascade of a thrust reverser of an engine nacelle includes monolithic sections. Each section is made of a polymer composite material an...
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WO/2018/195122A1 |
This disclosure relates to various seals for sealing around exhaust pipes, such as the exhaust pipe of an aircraft auxiliary power unit. The seal can include a collar portion bounding an opening that is configured to receive the exhaust ...
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WO/2018/178948A1 |
An air intake unit (3) for an engine of an aircraft (1); the intake unit (3) has: a tubular housing (4); a first inlet opening (7) which is obtained through an outer wall (6) of the tubular housing (4) and through which external air can ...
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WO/2018/174943A1 |
An air inlet for a flight vehicle engine includes at least one fin, at least partially upstream of a throat of the engine. The fin protrudes into a flow channel, extending beyond a boundary layer into the main airstream in the inlet. The...
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WO/2018/169454A2 |
The invention relates to aeronautical engineering, and specifically to the construction of aviation engines and aeroplane braking devices, and can be used in a cascade-type thrust reverser rotating cascade made of polymer composite ma...
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WO/2018/165498A1 |
An unmanned aerial vehicle includes at least one rotor motor configured to drive at least one propeller to rotate; and a micro hybrid generator system configured to provide power to the at least one rotor motor. The micro hybrid generato...
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WO/2018/152784A1 |
An airframe (10) and an unmanned aerial vehicle (100). The airframe (10) comprises a housing (12) and fans (14). An air vent (121) is separately provided on both ends of the housing (12) to be communicated with the internal space of the ...
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WO/2018/154256A1 |
The invention relates to an afterbody for a pylon supporting an aircraft turbojet engine, provided so as to form an aerodynamic surface covering the base of said pylon, said afterbody being elongate in the longitudinal direction, compris...
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WO/2018/118383A1 |
An innovative passive cooling solution with sealed UAV enclosure system allows heat from a semiconductor chip to be dissipated to the ambient environment through evaporation/condensation phase-change cooling and air cooling a heat sink s...
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WO/2018/075413A1 |
Described embodiments provide a rotor mounting boom assembly for a personal aircraft. The rotor mounting boom assembly includes a rotor mounting boom releasably attachable to a wing of the personal aircraft, one or more vertical lift rot...
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WO/2018/068979A1 |
The invention relates to a drive system (9) for a vehicle, in particular an airplane (1), comprising the following components: - an internal combustion engine (15) for converting chemical energy stored in a liquid fuel (12) into mechanic...
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WO/2017/041018A9 |
A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore condu...
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WO/2018/067310A1 |
An air intake assembly for an aircraft includes an auxiliary power unit intake that is defined by a skin of the aircraft. The auxiliary power unit intake is in fluid communication with an auxiliary power unit. The air intake assembly als...
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WO/2018/067329A1 |
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume (522) having a first average velocity from an engine (500), and expelling a bypass exhaust plume (532) having a second average velocity from t...
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WO/2018/049720A1 |
Disclosed are an aircraft arm assembly of an aircraft and an aircraft, the aircraft arm assembly (10) of the aircraft comprising an aircraft arm housing (12) and an air guide mechanism (14), wherein the aircraft arm housing (12) is inter...
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WO/2018/038909A1 |
An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a...
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WO/2018/035206A1 |
A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the elec...
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WO/2017/209820A3 |
A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream.. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are...
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WO/2018/020112A1 |
The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said a...
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WO/2018/015659A1 |
The invention relates to a nacelle (10) of a turbine engine (14) having a substantially tubular structure and defining a secondary channel (28), the nacelle (10) comprising a shroud (22) forming a trailing edge on a downstream end of the...
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