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Matches 1 - 50 out of 570

Document Document Title
WO/2014/053057
An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust ...  
WO/2014/055103
A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives ...  
WO/2014/051669
A turbine engine system mounted on an aircraft wing includes a gas turbine engine having a spool, a turbine coupled with the spool, a fan coupled to be rotated about an axis through the spool, and a gear assembly coupled between the fan ...  
WO/2014/052857
An assembly for mounting a turbine engine case to a pylon. The assembly includes a beam and a shackle. The shackle includes a plurality of side segments, and an intermediate segment that is engaged rotatably to the beam. Each of the side...  
WO/2014/041310
The invention relates to a system for pylon attachment system (31) for mounting an engine (10) on the structure of an aircraft, in particular to the wings, comprising a first attachment means (31) which can be secured to the pylon and a ...  
WO/2014/036818
An electrodynamic dish-shaped flying generator comprises a body, a power plant, and a control system. The power plant includes a plurality of annular ferromagnetic guide rails for generating magnetic levitation, a plurality of rising for...  
WO/2014/036328
A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. A...  
WO/2014/021966
A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly com...  
WO/2014/021966
A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly com...  
WO/2014/021798
The invention relates to a system providing vertical take off and landing for military aircrafts or civilian airplanes, unmanned aerial vehicles and so on. The rotating fans working with electric motor taking electricity from the very po...  
WO/2014/013270
A method of flying an unmanned aerial vehicle (50) at an elevated altitude comprising at least two wings (53) comprising solar-energy collectors (not shown), the method involving flying the vehicle (50) for an extended period of time wit...  
WO/2013/186003
The invention relates to a method for providing predefined desired drive characteristics (38, 50) in an aircraft, characterized by the following steps: - driving a thrust generation element of the aircraft by means of an electric motor t...  
WO/2013/186003
The invention relates to a method for providing predefined desired drive characteristics (38, 50) in an aircraft, characterized by the following steps: - driving a thrust generation element of the aircraft by means of an electric motor t...  
WO/2013/186009
The invention relates to a hybrid aircraft (F). According to the invention, a suitable position for mounting an energy generation unit (14) in the aircraft is identified, said energy generation unit comprising an internal combustion engi...  
WO/2013/181722
The Road-and-air transport vehicle is intended to transport people (from 1 to 4 people] on the roads, as a light passenger vehicle, and in the air - as a small aircraft. It has a body (1] with a cabin (13), 4 wheels: 2 front wheels, cont...  
WO/2013/178776
The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or unmanned aerial system (UAS), comprising a rigid wing (2), which enables aerodynamic horizontal flight, and at least four rotors (4, 4'), which ar...  
WO/2013/162128
The present invention relates to a cable connection unmanned aerial vehicle system, wherein electricity required for the thrust motor of an unmanned aerial vehicle and the electronic equipment loaded thereto is supplied from the ground s...  
WO/2013/160390
The present invention relates to a device 10 for cabin pressure difference warning for an aircraft or spacecraft 1, comprising a cabin pressure difference sensor means 12 for detecting the current cabin pressure difference ΔΡ, a contac...  
WO/2013/162666
A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associ...  
WO/2013/138217
A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed.  
WO/2013/138215
An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging ai into a discharge manifold. The discharge manifold containin at le...  
WO/2013/133831
A mounting assembly (50) allows components (48) to be mounted on a beam (38) having a rectangularly shaped cross section and flat sides (64). The mounting assembly (50) includes a plurality of adapter members (52-58) and a strap (70). Ea...  
WO/2013/128123
According to the invention, the method for holding an adapter piece (19) on a tubular housing (5) of a turbo engine (1), said piece (19) being intended to at least partially cover said housing (5), is characterised in that the following ...  
WO/2013/126728
A turbine engine exhaust nozzle includes a core gas duct, a nozzle duct, and a thrust vectoring duct system having a duct valve, a first vectoring duct and a second vectoring duct. The nozzle duct directs a first portion of core gas from...  
WO/2013/119517
A connection for mounting an aircraft engine to an aircraft pylon includes a plate to be connected to a portion of an engine, and a body that extends rearward from the plate. A back-up connection, including a pin positioned within a slot...  
WO/2013/108999
Disclosed is a blended wing body provided with a canard. The blended wing body provided with the canard, according to the present invention, is the blended wing body provided with the canard in which main wings and a body are integrally ...  
WO/2013/102191
A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes ...  
WO/2013/100807
The invention relates to the aircraft industry field, in particular to tactical aviation aircraft providing for the detection and striking of air, above-water and land-based targets. The technical result to which the invention is dire...  
WO/2013/088068
The invention relates to a pylon (30) capable of securing a turbine engine (10) to a structural element (40) of an aircraft, said pylon (30) having an aerofoil defined by two opposite surfaces (36, 38) and longitudinally delimited betwee...  
WO/2013/079100
An aircraft comprises a turbine engine (104) suspended from a wing (102) by means of a pylon (105). Compressed hot air is bled off from the turbine engine (104). A bleed air duct (209) in the wing (102) conveys the compressed hot air tow...  
WO/2013/064768
A turbo engine attachment pylon configured to connect a turbo engine to a structural element of an aircraft, said pylon (30) having an aerodynamic profile defined by two opposite lateral faces and delimited longitudinally between a leadi...  
WO/2013/064768
A turbo engine attachment pylon, configured to connect a turbo engine to a structural element of an aircraft, said pylon (30) having an aerodynamic profile defined by two opposing lateral faces and delimited longitudinally between a lead...  
WO/2013/057355
Improved impact‑resistant and damage‑tolerant aircraft fuselage. The invention relates to a section (32) of the fuselage of an aircraft suffering impacts from external bodies, the fuselage of the aircraft having a curved form with at...  
WO/2013/056041
The present invention is an aero engine that is provided with compression combustion and weighs less than 725 lbs. The present invention is further a method of forming the aero engine.  
WO/2013/050715
The invention concerns an aircraft propulsion assembly comprising a turbojet engine (2), a support (10) transferring a force torque to the aircraft from a suspension assembly (100), and said suspension assembly (100) interposed between s...  
WO/2013/052912
A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engiune member, a transmission member and a propeller member, the control system including a sensor for sensing ...  
WO/2013/050714
The invention concerns an aircraft propulsion assembly of which the suspension assembly comprises the following upstream suspension fasteners mounted on a blower housing (34) and/or on said intermediate housing (30) of the turbojet engin...  
WO/2013/052912
A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engiune member, a transmission member and a propeller member, the control system including a sensor for sensing ...  
WO/2013/041025
Disclosed is a wing ring comprising an annular support (1) and a plurality of vanes (2) provided on the annular support (1), wherein the plurality of vanes (2) are disposed equidistantly on the annular support (1); each vane (2) is conne...  
WO/2013/040847
A through-flow air suspension platform comprises at least two through-flow blower fans (4). The through-flow blower fans (4) are arranged on the same plane. Each through-flow blower fan comprises a cylindrical blower fan shell (2). Two o...  
WO/2013/041025
Disclosed is a wing ring comprising an annular support (1) and a plurality of vanes (2) provided on the annular support (1), wherein the plurality of vanes (2) are disposed equidistantly on the annular support (1); each vane (2) is conne...  
WO/2013/039853
A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propul...  
WO/2013/030489
The invention relates to a rotary- or fixed-wing aircraft comprising one or more rotors and/or one or more propellers, in which the rotor(s) and/or propeller(s) are rotated at a variable or constant speed by at least one shaft (Rpl, Rp2,...  
WO/2013/030489
The invention relates to a rotary- or fixed-wing aircraft comprising one or more rotors and/or one or more propellers, in which the rotor(s) and/or propeller(s) are rotated at a variable or constant speed by at least one shaft and the ai...  
WO/2013/030498
In an assembly comprising a dual-flow turbine engine and a system for attaching the turbine engine to an aircraft structure, the attachment system includes a pylon, at least two rear fasteners connecting the pylon to two rear attachment ...  
WO/2013/030498
In an assembly comprising a dual-flow turbine engine and a system for attaching the turbine engine to an aircraft structure, the attachment system includes a pylon, at least two rear fasteners connecting the pylon to two rear attachment ...  
WO/2013/032490
A method and apparatus comprising a first wall (122) and a plurality of longitudinal members (120). The first wall is for an inlet (110) of an aircraft engine (108). The plurality of longitudinal members connects the first wall to a stru...  
WO/2013/017680
The object of the invention is a drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system, characterised in that the electrical energy is provided at least in part ...  
WO/2013/013084
A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with...  
WO/2012/175843
The invention relates to a structure for mounting a power train having non-ducted propellers onto the fuselage of an aircraft, said mounting structure being connected via first and second means for attaching onto so-called front and rear...  

Matches 1 - 50 out of 570