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Matches 301 - 350 out of 1,213

Document Document Title
WO/2009/053560A3
The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of...  
WO/2009/053560A8
The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of...  
WO/2009/048713A1
A heat shield (2) includes a ceramic composite heat shield panel (3) having a generally concave first surface and a generally convex second surface and a pair of thickened panel edge portions (9) provided in the heat shield panel. A heat...  
WO/2009/043924A1
Arrangement for mounting a propulsive system on an aircraft airframe (12) by means of an external strut (4) which connects the engine (1) with the airframe (12), said strut (4) comprising a plurality of spars (8) intruding into the airfr...  
WO/2009/036465A9
A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a...  
WO/2009/036465A1
A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a...  
WO/2009/027333A1
The invention mainly relates to a device for attaching an aircraft engine that comprises a rigid structure (10) and a means for attaching the engine on said rigid structure, said attachment means including a rear engine fastener (8) and ...  
WO/2009/027336A1
The invention relates to an engine assembly for an aircraft, that comprises an engine, a device for attaching the engine (4) and a nacelle surrounding the engine and provided with fan coils (34) the attachment device (4) including a rigi...  
WO/2009/007562A1
Steel characterized in that its composition is, in percentages by weight: - C = 0.20 - 0.30%; - Co = traces - 1%; - Cr = 2 - 5%; - Al = 1 - 2%; - Mo + W/2 = 1 - 4%; - V = traces - 0.3%; - Nb = traces - 0.1%; - B = traces - 30 ppm; - Ni =...  
WO/2009/007354A1
The invention relates to an aircraft engine attachment pylon comprising a system for mounting the engine (11) including a device (9) for reacting thrust forces which is equipped with two lateral link rods (90) and with a spreader beam (9...  
WO/2009/007520A3
The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing...  
WO/2009/007520A2
The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing...  
WO/2008/155497A1
The invention relates to a securing mast (100) for securing an engine (1) to the wing (3) of an aircraft, wherein the device includes two fasteners (101, 102), a first end (110, 112) of each fastener being secured to the engine and the s...  
WO/2008/155386A1
Device for coupling an aircraft engine comprising a rigid structure and means for coupling the said engine to the said rigid structure, the said coupling means comprising two link rods (26) for absorbing the thrust forces mechanically li...  
WO/2008/155376A1
The invention relates to a pylon for coupling an engine for an aircraft comprising a rigid structure (10) forming a casing and a system for mounting the engine (11) mounted on the structure (10) and comprising a rear engine attachment (8...  
WO/2008/150213A1
The invention relates to a mounting element (51) for transferring loads between a gas turbine engine (1) and an airframe (2), the mounting element (51) presenting a cylindrical hole (511) for receiving a fastening element, such as a pin ...  
WO/2008/148722A1
The present invention relates to an engine assembly for an aircraft, comprising a turboprop (2) and the device (1) for attaching it to a wing structure (4), the device comprising a rigid structure (8) and means of fastening the turboprop...  
WO/2008/150202A1
The invention relates to a structure for transferring loads in a gas turbine engine (1), and/or between a gas turbine engine (1) and an airframe (2). The structure comprises a collapsible element (513), and is adapted to operate in a fir...  
WO/2008/142098A1
The invention relates to a coupling pylon (4) for an aircraft engine (2), the pylon comprising a rigid structure (10) forming a casing provided with an inclined bottom frame member (28) and a top frame member (26), and an engine mounting...  
WO/2008/135364A1
The invention relates to an aircraft engine mounting structure including an intermediate part (120) disposed between a crossbar supporting element (100) and a rigid structure box (10), a first shearing pin (124) extending through a first...  
WO/2008/135366A1
The invention relates to an aircraft engine mounting device including a rigid structure and means for mounting the engine on said rigid structure, said mounting means including a device (14) for absorbing the thrust force generated by th...  
WO/2008/132077A1
The invention relates to an aircraft engine attachment pylon comprising a rigid structure (10) forming a box section and an engine rear attachment (8) comprising an attachment body (42) and at least one lateral fitting (34) positioned on...  
WO/2008/132375A1
According to the invention, in order to generate an efficient aerodynamic braking force independently from the speed of a vehicle such as an aircraft moving in the air, the method comprises a step of generating energy using the vehicle, ...  
WO/2008/129042A1
The invention relates to an assembly (1) for an aircraft comprising a wing member (2) and a pylon (4) for securing a turboshaft engine (10), that comprises a rigid structure (6) forming a box defined on the outside by a first spar (26), ...  
WO/2008/125077A1
Disclosed is an aircraft comprising an internal combustion engine, the driving power of which drives a propeller. The internal combustion engine (1) cooperates with an electric machine (9) which can be operated as an electric motor in a ...  
WO/2008/125631A1
The main subject of the present invention is a device for attaching an aircraft engine comprising a load reacting device that has a main fitting (24) intended to be fixed to an engine mounting boom (25) fixed to a box structure (8), an a...  
WO/2008/121047A1
A gas turbine engine component comprising - at least one ring element (114), and - a plurality of circumferentially spaced load carrying vanes (112) extending in a radial direction of the ring element (114), wherein the load carrying van...  
WO/2008/121774A3
A solar thermal powered aircraft (100) powered by heat energy from the sun. A Rankine-Bray ton hybrid cycle heat engine (140) is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller (109) or ot...  
WO/2008/121774A2
A solar thermal powered aircraft (100) powered by heat energy from the sun. A Rankine-Bray ton hybrid cycle heat engine (140) is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller (109) or ot...  
WO/2008/118229A2
A hybrid composite-metal component is provided. The component includes an elongate inner metal piece, an outer metal piece disposed about at least a portion of the inner metal piece, and composite material disposed between the inner meta...  
WO2008054521B1
Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features suc...  
WO/2008/111992A2
An aircraft engine nacelle (10) includes a pivot-door type thrust reverser. The thrust reverser (22) includes a monolithic fan duct barrel (24) with an annular wall (50) that includes a forward section (46), a door section (54), and an a...  
WO/2008/103735A3
Modification or retrofit components for an aircraft having wing mounted engines. A replacement wing torque box has thickened spar webs machined with raised bosses around holes in the web to lower stress concentration. The spar caps have ...  
WO/2008/096073A2
The invention relates to an aircraft fuselage comprising a front part (2) with a cockpit, a central part (4) and a rear part (6). The central part of the fuselage includes a first zone (10) which is located at the front part and which in...  
WO/2008/096073A3
The invention relates to an aircraft fuselage comprising a front part (2) with a cockpit, a central part (4) and a rear part (6). The central part of the fuselage includes a first zone (10) which is located at the front part and which in...  
WO/2008/097325A3
An airfoil for use with an aircraft having an engine (3) positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element (14, 16). The upper surfac...  
WO/2008/097325A2
An airfoil for use with an aircraft having an engine (3) positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element (14, 16). The upper surfac...  
WO/2008/081098A1
The invention relates to a rear tail assembly (1) for an aircraft, including a fuselage (3), a wing (2) and at least one propulsion engine (5, 5a, 5b) attached in the rear portion of the fuselage located behind the wing (2) along the X l...  
WO/2008/081098A8
The invention relates to a rear tail assembly (1) for an aircraft, including a fuselage (3), a wing (2) and at least one propulsion engine (5, 5a, 5b) attached in the rear portion of the fuselage located behind the wing (2) along the X l...  
WO/2008/080135A2
An aircraft (100) including a wing (110) and a pylon (114), wherein the pylon provides an airfoil (134) inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series Learjets are dis...  
WO/2008/080135A3
An aircraft (100) including a wing (110) and a pylon (114), wherein the pylon provides an airfoil (134) inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series Learjets are dis...  
WO/2008/073069A3
An unmanned aerial vehicle includes a fuselage, a horizontal stabilizer assembly, a wing assembly, a forward propulsion device, and at least one rear propulsion device. The fuselage has a forward end portion and a rearward portion. The h...  
WO/2008/064881A1
The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a propulsion unit (1) and an energy converter (4). The energy converter (4) is is adapted for providing propulsion energy to the propul...  
WO/2008/065065A1
The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter (4), a second energy converter (5) and a propulsion unit (1). The first energy converter (4) provides first pr...  
WO/2008/057251A3
This invention relates to internal combustion engine powered fixed wing aircraft. More particularly, this invention relates to engine mount configurations applicable to such aircraft.  
WO/2008/054521A2
Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features suc...  
WO/2008/054521A3
Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features suc...  
WO/2008/048830A3
A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). which then converts (105) such...  
WO/2008/046872A1
This aircraft comprises both thrusters (7, 16, 17) for conventional aircraft flight through the atmosphere and for high-altitude use as a rocket. It is divided into a payload compartment (8) and a compartment (13) chiefly containing the ...  
WO/2008/043903A2
The nacelle (1) comprises an air intake (5) upstream of the turbojet engine (2), a middle section (6) an internal casing (6a) of which is intended to surround a fan (3) of the turbojet engine (2), and a downstream section (7) comprising ...  

Matches 301 - 350 out of 1,213