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Patent Searching and Data


Matches 301 - 350 out of 1,142

Document Document Title
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 ...  
WO/2008/043903A3
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 ...  
WO/2008/006823A1
The invention relates to an engine assembly for an aircraft, comprising an engine, an engine mounting device (4) and a cowling enclosing the engine provided with fan shrouds (34), the mounting device (4) having a rigid structure (8) and ...  
WO/2008/000924A1
The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section...  
WO/2007/147965A2
Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment (15) of the anterior part (14) of the fairing (7) for the suspension pylon (6) is radially flexible.  
WO/2007/147965A3
Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment (15) of the anterior part (14) of the fairing (7) for the suspension pylon (6) is radially flexible.  
WO/2007/131979A1
The present invention relates to a device for attaching an aircraft engine comprising a rigid structure forming a box, and a device for taking up the thrust forces having a main brace (34) mounted fixedly on one of the longerons (17) for...  
WO/2007/120199A3
An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a thruster mounted to an aircraft ...  
WO/2007/107647A1
Aircraft having reduced environmental impact. According to the invention, said aircraft comprises at least one engine (10) with at least one propeller (12, 13) carried, at the rear, on the top of said aircraft with the propeller(s) locat...  
WO/2007/104940A1
In an aircraft comprising a payload region (2) and a wing section (21, 31) which carries an engine (24, 33) of a kind which, in use, generates a flow of exhaust gases, the wing section (21, 31) is provided with or has associated therewit...  
WO/2007/051938A3
The invention relates to a front device (100) for fastening a turbojet engine (1) to an aircraft fixing strut (3), which is used for absorbing trust loads of said turbojet engine and is characterised in that it comprises a top bracket (1...  
WO/2007/051914A1
Disclosed is an aircraft having a reduced environmental impact. According to the invention, this aircraft comprises at least one engine (7) having at least one propeller (9, 10) supported, at the rear, on the back of the aircraft with th...  
WO/2007/051938A2
The invention relates to a front device (100) for fastening a turbojet engine (1) to an aircraft fixing strut (3), which is used for absorbing trust loads of said turbojet engine and is characterised in that it comprises a top bracket (1...  
WO/2007/042508A1
The invention concerns a nut system (100) comprising a nut (104) provided with a main thread (106) of pitch p1 and arranged along a screwing axis (108) of the nut. The invention is characterized in that it further comprises a threaded me...  
WO/2007/042453A1
The invention concerns a rigid framework (8) for aircraft engine mounting structure, in the form of a structure box closed by first and second structure box side panels (34a, 34b), said framework comprising inter-rib spaces (381 à 388) ...  
WO/2007/039556A1
The invention concerns a turbojet engine mounting structure for aircraft comprising a central structure box (22) formed by the assembly of two panels joined via transverse ribs (23), the mounting structure further comprising two lateral ...  
WO/2007/039556A8
The invention concerns a turbojet engine mounting structure for aircraft comprising a central structure box (22) formed by the assembly of two panels joined via transverse ribs (23), the mounting structure further comprising two lateral ...  
WO/2007/036521A1
The invention concerns an engine assembly (1) for an aircraft comprising an engine (2) and an engine mounting structure (4), said structure comprising a rigid structure (10) including a structure box (24) and a mounting system (11) inter...  
WO/2007/036519A1
The invention concerns an engine mounting structure designed to be interposed between an aircraft wing system and said engine, the structure comprising a rigid structure (8) as well as front aerodynamic structure (24) mounted fixedly on ...  
WO/2007/036516A1
The invention concerns a novel engine mounting structure for coupling an aircraft engine assembly. The engine mounting structure (50) comprises a monolithic framework (20), constructed by smelting or welding for example, covered with mec...  
WO/2007/036527A1
The invention relates to an engine assembly for an aircraft, consisting of a turbojet, a pylon and a plurality of engine mounts, the latter comprising first and second front mounts (6a) which are fixed to the fan case and which are dispo...  
WO/2007/033995A1
The invention concerns a strut for locking (4) the engine of an aircraft, the strut comprising a rigid structure (10) forming a structure box closed at the front by a front closing rib (36), as well as a system for mounting the engine in...  
WO/2007/034094A1
The invention concerns a turbojet (1) for aircraft, characterized in that it supports at least one tail fin (7), said tail fin being fixed on the strong structure (11) of said turbojet so as to form a single-unit assembly. The turbojet m...  
WO/2007/033993A1
The invention concerns a method for mounting an aircraft engine on a rigid structure of a strut, comprising a step of fixing, on the structure a locking body (46) of an engine fastener, said locking body being designed to be pressed agai...  
WO/2007/028764A1
The invention relates to a system (33) for connecting a crossbar to the rigid structure of an aircraft engine pylon, comprising an axle system (32) which is mounted to slide in a first passage (38) in a fitting (34) such that it can move...  
WO/2007/022315A3
An integrated aircraft propulsion system includes a pulse detonation engine integrated with a lifting surface to achieve supercirculation. The exhaust from the pulse detonation engine is expelled in a rearward direction tangentially to t...  
WO/2007/017339A1
The invention relates to a primary engine (9) strut (11) structure of an aircraft characterized in that it comprises single-piece composite panels (1a, 2a, 3a, 4a) while replacing the metallic spars (1, 2) and metal panels (3, 4), said c...  
WO/2007/012667A1
The invention concerns an assembly for aircraft comprising a wing system element (2) as well as an attachment mast, the assembly further comprising means for attaching (8) the mast on the element (2), said means (8) including two front h...  
WO/2007/000546A2
The invention relates to an aircraft engine unit (1) comprising a jet engine (2), a suspension pylon (4) and a plurality of engine fasteners. According to said invention, the plurality of fasteners comprises first (6a) and second (6b) fr...  
WO/2007/000456A1
The invention relates to an engine mounting structure for an aircraft, said structure comprising a rear engine mount (8) provided with a rear mount body (54) and two lateral fittings (26), each comprising a longitudinal part which comes ...  

Matches 301 - 350 out of 1,142