| Document |
Document Title |
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
WO/2018/002855A1 |
Apparatus and method for conditioning engine-heated air onboard an aircraft including a heat exchanger (140) at least partially disposed in a pylon structure (118) for supporting an engine (134) of the aircraft. The pylon heat exchanger ...
|
|
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...
|
|
WO/2017/172840A1 |
This document describes a system and method through which unmanned aerial vehicles (UAVs) can be docked, with a device that can secure the UAVs, and information can be transmitted to and from such UAVs. The UAVs are secured through the u...
|
|
WO/2017/165379A1 |
Some embodiments provide a system to design an unmanned aircraft system (UAS) based on an intended task, comprising: UAS component database and a design control circuit configured to: obtain a first set of multiple task parameters corres...
|
|
WO/2017/149196A1 |
A floatplane (100) comprising a fuselage (102), at least one primary wing (104) attached to the fuselage (102), a float arrangement comprising a number of floats (106), and propulsion means (500) for driving the floatplane (100), charact...
|
|
WO/2017/134459A1 |
The present invention aims to provide a modular jet trainer aircraft (1) which can be reconfigured to provide a plurality of different handling aircraft which will be particularly beneficial in the training of pilots. For example, the pr...
|
|
WO/2017/132805A1 |
The present invention relates to a unmanned aerial vehicle electronic speed controller (ESC) heat dissipation device. The device comprises an arm (1), an ESC (2) being provided internally at one end of the arm (1), a rotor being provided...
|
|
WO/2017/127931A1 |
An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is con...
|
|
WO/2017/124783A1 |
A motor (100), a power device using the motor, and an unmanned aerial vehicle (500) using the power device. The motor (100) comprises a stator (30) and a rotor (50) rotatably sleeved around the stator (30). The motor (100) further compri...
|
|
WO/2017/103389A1 |
The invention relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle, comprising devices for actuating and controlling the reverser, including hydraulic locks and cylinders, the corresponding hydrauli...
|
|
WO/2017/093710A1 |
Noise attenuating devices and methods, precursors and abrasive blasting masks for manufacturing noise attenuating devices are disclosed. An exemplary method disclosed herein comprises bonding a facing sheet (12) of the noise attenuating ...
|
|
WO/2017/089730A1 |
The invention relates to a turbomachine (24) of "open rotor" or turboprop type, comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake duct (32) surrounding the central hub (30) and opening int...
|
|
WO/2017/078805A1 |
An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the g...
|
|
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...
|
|
WO/2017/041018A1 |
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...
|
|
WO/2017/024391A1 |
An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine...
|
|
WO/2017/024392A1 |
An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulat...
|
|
WO/2017/024389A1 |
An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having...
|
|
WO/2017/024390A1 |
An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid ...
|
|
WO/2017/024394A1 |
An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fa...
|
|
WO/2017/017368A1 |
The invention relates to a porous body (9) made from a ceramic-matrix composite material and intended for an acoustic attenuation panel, comprising: a plurality of interwoven ceramic fibres (13), a metal oxide matrix (15), and a pluralit...
|
|
WO/2017/013363A1 |
The present invention relates to an aircraft comprising a fuselage (1) and a thruster downstream of the fuselage. The thruster includes a power turbine (7), located inside a main flow jet, and at least one fan (9), located inside a secon...
|
|
WO/2017/013077A1 |
The invention relates to a drive device for an aircraft, comprising a shaft turbine coupled to an impeller by means of a shaft. The impeller comprises a suction side and a thrust side. The shaft turbine is arranged in the region of the s...
|
