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Patent Searching and Data


Matches 501 - 550 out of 2,527

Document Document Title
WO/2011/070340A1
An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairin...  
WO/2011/054084A1
A helicopter settling protector and method of manufacturing same, the settling protector being made of a thermoformed thermoplastic, preferably a polycarbonate resin thermoplastic, and adapted to be connected to a skid tube of a helicopt...  
WO/2011/006746A3
The invention relates to the landing gear of an aircraft, comprising a strut (1) having two arms forming a rotational axis (2) for retracting the gear, a rotating tube (6) mounted in a mobile manner in such a way that it rotates inside t...  
WO/2011/048394A1
An aircraft landing gear assembly including a bogie beam, a landing gear strut (1) having a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam (3), and a stop (13) arranged to l...  
WO/2011/048393A1
Aircraft landing gear including at least one load bearing longitudinal structural element (116) wherein said longitudinal structural element is hollow and is arranged to have at least one non-structural element (118) located inside.  
WO/2010/133971A3
This invention relates to an improved float for use with an aircraft having water landing capabilities comprising at least one float capable of increasing/decreasing its volume arranged to at least substantially support said aircraft in ...  
WO/2010/055354A4
An overload detecting assembly comprising a lateral probe (18) which cooperates with a first load bearing member (10) as it moves towards a second load bearing member (11) and in turn deflects an indicator member (20) which may take a pe...  
WO/2010/140082A9
A UAV with an engine (34) attached to rear (38) of its fuselage by an engine mounting assembly with the rotational axis of the engine generally parallel with the axis (45) of the fuselage. The engine mounting assembly includes a fuselage...  
WO/2011/030365A2
The invention concerns a device and a method to cause the rotation of at least one wheel of the landing gear of aircraft, according to which between the supporting structure (12) of the landing gear and the brake group (19, 20) of the wh...  
WO/2010/141628A3
A damper for a landing gear of a helicopter having a barrel, a piston defining a first hydraulic cavity between the piston and a bottom end of the barrel and a second hydraulic cavity between the piston and a top of the barrel, a stack o...  
WO/2011/023505A2
An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un- sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a...  
WO/2011/023980A2
A main landing gear assembly for an aircraft comprising: an elongate beam pivotally coupled about its longitudinal axis to the aircraft such that the axis of rotation of the elongate beam is generally parallel to the longitudinal axis of...  
WO/2010/055354A9
An overload detecting assembly comprising a lateral probe (18) which cooperates with a first load bearing member (10) as it moves towards a second load bearing member (11) and in turn deflects an indicator member (20) which may take a pe...  
WO/2011/014153A1
A crash attenuation system for an aircraft includes an airbag carried by the aircraft that is inflatable generally adjacent an exterior of the aircraft. The airbag is in fluid communication with at least one vent passage for channeling g...  
WO/2011/006747A1
The invention relates to a means for rotating the strut (1) of the landing gear of an aircraft about a retraction axis (2), such as an actuator (12a, 12b) comprising a first end that can be fixed to the structure of the aircraft and a se...  
WO/2010/116383A9
An undercarriage (40) which combines both tracks (9) and tyres (14) is provided. During the landing roll phase, only the tracks (9) take the brunt of the impact, and the flaps (42, 42a) incorporated at a convenient spot near the mouth of...  
WO/2011/006746A2
The invention relates to the landing gear of an aircraft, comprising a strut (1) having two arms forming a rotational axis (2) for retracting the gear, a rotating tube (6) mounted in a mobile manner in such a way that it rotates inside t...  
WO/2011/000971A2
The invention relates to a device for controlling at least one trapdoor (4a, 4b) of the hold of aircraft landing gear, the device comprising a permanent mechanical link (20, 23, 24, 25a, 25b) between the trapdoor and the landing gear. Ac...  
WO/2010/055354A3
An overload detecting assembly comprising a lateral probe (18) which cooperates with a first load bearing member (10) as it moves towards a second load bearing member (11) and in turn deflects an indicator member (20) which may take a pe...  
WO/2010/150760A1
Provided is a steering angle control system for aircraft. Said control system minimizes the amount that an aircraft slips while turning on a low-μ surface such as a frozen surface, and allows directional control of the aircraft via stee...  
WO/2010/145018A1
A method for manufacturing a part selected from a plurality of part types is disclosed. The method involves the step of selecting, from a supply of workpieces, a workpiece of a type that is associated with the type of part selected, the ...  
WO/2010/146045A1
The invention relates to a drive system for an aircraft, comprising an electric motor. With the aim of allowing aircraft to be driven on the ground more efficiently and also more quietly, the invention provides that the electric motor is...  
WO/2010/139756A1
The invention relates to a method for operating between an extended position and a retracted position an aircraft landing gear assembly comprising a leg hinged to the aircraft, the leg being stabilized in the extended position by a break...  
WO/2010/141628A2
A damper for a landing gear of a helicopter having a barrel, a piston defining a first hydraulic cavity between the piston and a bottom end of the barrel and a second hydraulic cavity between the piston and a top of the barrel, a stack o...  
WO/2010/140082A1
A UAV with an engine (34) attached to rear (38) of its fuselage by an engine mounting assembly with the rotational axis of the engine generally parallel with the axis (45) of the fuselage. The engine mounting assembly includes a fuselage...  
WO/2010/136892A1
A method for controlling a plant assembly, in particular a steering system for a nose wheel of an aircraft, includes providing a plant assembly (12) having a first plant (14) including a first sensor (52a) that monitors the first plant. ...  
WO/2010/116383A3
An undercarriage (40) which combines both tracks (9) and tyres (14) is provided. During the landing roll phase, only the tracks (9) take the brunt of the impact, and the flaps (42, 42a) incorporated at a convenient spot near the mouth of...  
WO/2010/138886A1
A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7 % aluminum, 4.8 to 5.2 % vanadium, 0.7 to 0.9 % iron, 4.6 to 5.3 % molybdenum, 2.0 to 2.5 % chromium, and 0.12 to 0.16 % oxygen with balance titanium and inciden...  
WO/2010/129960A1
An electromechanical linear actuator includes a pneumomechanical back-up system to ensure extension of retractable landing gear for landing an aircraft. Structurally, the linear actuator includes a stator forming a channel for receiving ...  
WO/2010/119109A1
The invention relates to a device for reducing the aerodynamic noise of aircraft landing gear deployed during the landing and/or take-off phase. The device comprises two flanges (4a, 4b) for respectively blocking each end (2a, 2b) of a h...  
WO/2010/116658A1
A first method comprises a step (S5) for investigating the start point of a shear layer as the flow field characteristics around the original shape of an object to be designed, and a step (S7) for giving a planar object to the vicinity o...  
WO/2010/115893A1
The invention relates to an aircraft landing gear provided with a selective force transmission device including a first element (1; 101; 201) and a second element (2; 102; 202) which is movably mounted on the first element, a friction me...  
WO/2009/068801A3
The invention relates to a method for deactivating the orientation system of the front landing gear of an aircraft, that comprises the following steps: (a) detecting an activated condition of the orientation system (2); (b) detecting a c...  
WO/2010/099730A1
An amphibious large aircraft without airstairs is provided. The fuselage (7) of the amphibious large aircraft is flat,and the shape of its bottom is rectangular. The longitudinal cross-section of the fuselage has a shape of the cross-s...  
WO/2010/095261A1
Provided is an airframe position adjusting structure capable of adjusting the position of an airframe (A) inclined laterally. The airframe position adjusting structure (1) is made such that a component force (FV), as taken in the vertica...  
WO/2010/092253A1
The invention relates to an aerodyne (10) comprising a lift propeller (84), a fairing (14) surrounding the propeller, and an electric motor (26) for rotating the propeller relative to the fairing. The aerodyne also comprises a landing ge...  
WO/2010/082352A1
A shock absorption system (1) wherein an airbag (4) is expanded by a high pressure air cylinder (5) at the time of collision to the ground due to impossible flight, a cover body (2) is developed to the outside for the footprint (11a) of ...  
WO/2010/072916A1
The invention relates to a method for making a structural part comprising a tubular portion (30) from which a structural member made of a composite material protrudes, said method comprising the steps of: shaping a planar preform (59) in...  
WO/2010/063893A1
The present invention relates to aircraft landing gear, comprising a box-type structure (1) to be mounted in a hinged manner onto a structure of the aircraft, and a lower portion (2) carrying the wheels and which is movable relative to t...  
WO/2010/063109A1
The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door.  
WO/2010/063895A1
The invention relates to a multifunctional electromechanical device for aircraft landing gear, comprising at least: a first shaft (10) rotatably mounted onto the aircraft around a rotational axis (R) substantially parallel to a hinge axi...  
WO/2010/063110A1
The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.  
WO/2010/056193A1
A transportation apparatus (1) is disclosed, comprising a payload receiving unit (30), a transportation body (10), and a compensation system (20) arranged there between and devised to allow adjustment of a desired spatial relationship be...  
WO/2010/009289A3
This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions. An actuator (18) is connected to the landing gear strut, and includes main and emergency drive...  
WO/2009/156617A3
The invention relates to an aircraft braking circuit comprising electro-mechanical actuator brakes (3) for braking wheels placed on the lower end of at least one landing gear. In accordance with the invention, a relocated housing (10) is...  
WO/2010/052447A1
An engine debris guard (14) for preventing tyre propelled debris striking an aircraft engine (3), the debris guard comprising a guard bar (20) pivotably connected to an aircraft main landing gear (10) having at least one wheel and tyre a...  
WO/2010/046679A1
The present invention provides a method of, and apparatus for, reducing noise caused by the interaction of airflow between two bluff bodies which are in a generally tandem arrangement, the method comprising providing flow control such th...  
WO/2010/003911A4
The invention relates to a wheel drive system for an aircraft, comprising at least one electric motor (8) and at least one fuel cell (20) as an energy source for the electric motor (8), wherein the electric motor can be coupled to at lea...  
WO/2010/011635A3
A shock strut (11) includes a relief device (70) that reduces the internal pressure within a sealed chamber (42) of the shock strut when a load condition that exceeds a maximum operating load condition is encountered. The reduced pressur...  
WO/2009/109771A3
An aircraft landing gear comprising: an arm (17) mounted to a pivot (18) and carrying one or more wheel assemblies (19); and a composite leaf spring (20) which is coupled to the arm and arranged to provide a resilient biasing force which...  

Matches 501 - 550 out of 2,527