| Document |
Document Title |
|
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/2010/138886A1 |
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/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/2010/052447A1 |
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/2010/012913A1 |
The invention relates to a protection panel (115) for a vehicle that comprises an outer surface (140) including at least one composite material, and is mounted via deformable parts on a mounting (135) attached to the vehicle structure. T...
|
|
WO/2010/011635A2 |
A shock strut includes a relief device that reduces the internal pressure within a sealed chamber of the shock strut when a load condition that exceeds a maximum operating load condition is encountered. The reduced pressure permits a tel...
|
|
WO/2010/009289A2 |
This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. An actuator is connected to the landing gear strut, and includes main and emergency drives housed within...
|
|
WO/2010/003911A1 |
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/2010/004200A2 |
The invention relates to a system for opening and closing a door (50) to the bay (20) of the landing gear (30) of an aircraft (10) with extensive freedom in positioning. According to the invention, the means of connection (60, 70, 81, 82...
|
|
WO/2010/000051A1 |
A landing gear mechanism for aircraft comprises at least a first connecting arm (2' ) and a second connecting arm (2), at least two wheels, a front wheel (3') and a rear wheel (3), each coupled to one of the connecting arms (2', 2), a ro...
|
|
WO/2009/156644A2 |
The invention relates to front aircraft landing gear built into electric control that includes: a landing gear leg (44) pivotably mounted on a structure of the aircraft between a retracted position and an extended position; an actuating ...
|
|
WO/2009/156617A2 |
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/2009/155553A1 |
A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhi...
|
|
WO/2009/150376A2 |
The invention relates to a jack device (50) for the landing gear (30) of an aircraft, that is hinged on a landing gear casing (20) and that can be easily locked in a predetermined configuration and unlocked. According to the invention, t...
|
|
WO/2009/146148A2 |
A locking mechanism includes a hydraulic actuator component and an electronic actuator component that are arranged coaxially, each of the actuator components being arranged to control a locking member that retains a movable component. In...
|
|
WO/2009/141554A2 |
- The subject of the invention is device for driving at least one wheel (22) of an aircraft landing gear which comprises at least one turbine machine (1) incorporated into the landing gear of the aircraft and which is designed to move th...
|
|
WO/2009/141550A2 |
Device for driving at least one wheel (22) of an aircraft landing gear, which comprises at least one turbine machine (1) incorporated into the landing gear (19) of the aircraft. Advantageously, the turbine machine (1) is a pneumatic turb...
|
|
WO/2009/127885A2 |
The flexible crankshaft (4) for software controllable aircraft wheel drive represents a steel flexible cable (4), located in a flexible plastic-rubber guide which is adapted for the transfer of the torque along all axis, and is connected...
|
|
WO/2009/125213A2 |
An aircraft landing gear arrangement comprises a nose landing gear assembly (18) and at least one main landing gear assembly (20). The nose landing gear assembly (18) has a nose landing gear wheel (26) with a high energy brake apparatus ...
|
|
WO/2009/124032A1 |
A pedal operated apparatus controls an aircraft rudder during flight using a mechanical linkage and controls a nose wheel power steering system while the aircraft is on the ground. The apparatus includes a pair of foot pedals operatively...
|
|
WO/2009/115224A1 |
The invention relates to a device (1) that comprises means (2, 3, 4, 7) for automatically controlling an aircraft on the ground along the lateral axis, by a dissymmetrical use of the engines and/or brakes of the aircraft.
|
|
WO/2009/115713A2 |
The invention relates to a landing gear mounted such that it can move on an aircraft between a retracted position and a down position, the landing gear comprising: - a box structure (1) mounted articulated on the aircraft; a breaking jur...
|
|
WO/2009/112735A1 |
The invention relates to a panel pivoting about an axis parallel to a side of the panel, which comprises a first continuous coating (1), a main structural frame of a composite stiffener (2, 3, 4, 5, 6) connected to the coating (1) and in...
|
|
WO/2009/109771A2 |
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...
|
|
WO/2009/103987A2 |
An emergency flotation device for an aircraft comprising a housing (9) containing an inflatable balloon (1) and a solid propellant cool gas generator (4) arranged to inflate the balloon when the aircraft ditches into water. The device is...
|
|
WO/2009/094603A2 |
The invention provides a novel, low-cost, spin-stabilized lander architecture capable (with appropriate system scaling tailored to the attributes of the target) of performing a soft- landing on a solar-system body such as Earth's Moon, M...
|
|
WO/2009/093223A2 |
A bogie-type landing gear (1) for aircrafts allows a remarkable weight and size reduction and comprises: one or more front wheels (2) and one or more rear wheels (3) connected to a beam (4), a rocking arm (7) centrally and rotatably conn...
|
|
WO/2009/086804A1 |
The motor (5) for driving the wheels (2) of an airplane landing gear, particularly nose landing gear, is disposed in the base (7) of the landing gear strut (1) or is installed as a wheel hub motor in the wheel hub or rim (3). The motor i...
|
|
WO/2009/089551A2 |
Various brake control systems and methods are provided herein. In one implementation, a brake pressure control system having a shutoff valve (24) in a hydraulic conduit (26, 30) between a pressure origination source (16, 18) and a wheel ...
|
|
WO/2009/079785A1 |
An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber...
|
|
WO/2009/082397A1 |
Α method and. device for supporting a torque bar (24) at a mid-span location in a wheel and 'brake assembly. 'A spacer block (150) interposed between the wheel well (18) and the torque bar generally restricts relative motion between the...
|
|
WO/2009/074134A1 |
The invention relates to a wheel bearing for aircraft, said bearing having a long service life, being very reliable and consisting of the lowest possible number of individual parts. The wheel bearing of an aircraft engine according to th...
|
|
WO/2009/053745A1 |
An aircraft noise-reduction apparatus comprise a flow-facing element(1)and a flow control device(2)positioned downstream of the flow-facing element(1). The flow (5) control device (2) is arranged, in use, to reduce noise induced by unste...
|
|
WO/2009/047367A2 |
A landing gear for an aircraft comprises: a shock absorber strut (1) with upper and lower telescoping portions (2, 3), the upper portion (2) being connectable to the airframe of the aircraft; an arm (4) to extend fore and aft relative to...
|
|
WO/2009/045788A2 |
Aircraft skid shoes (20) are provided with wear-resistant cladding layers (30). Powders of hard particles and braze material are impregnated into at least one cloth which is applied to the wear surface of a skid shoe (20) of a helicopter...
|
|
WO/2009/037687A1 |
A Separate and mobile landing gear which substitutes the existing fixed landing gear in aircrafts. This innovated landing gear locks on the landing aircraft in the manner described in the detailed description.
|
