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WO/2007/048164A1 |
A mechanism employing an applied electrical current to achieve forward rotation of aircraft landing wheels prior to landing, plus the option of retardation assistance after landing, resulting from an imposed electric current in strategic...
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WO/2007/048911A1 |
The invention relates to a telescopic shock strut for aircraft landing gear, comprising a strut assembly (1) in which a rod (2) is mounted for sliding, the shock strut comprises controlled means (41 43) for retracting the rod into the st...
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WO2007001714B1 |
The invention is a process for landing a tailless or flying wing type aircraft having a nose and wings that produce lift. The process includes the step of allowing the nose of the aircraft to stay lower upon touchdown such that lift from...
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WO/2007/027588A1 |
An apparatus for driving a taxiing aircraft is disclosed, comprising, in an aircraft, two self-propelled nosewheels, each having an electric motor; equipment for flight; dual-function controlling means for controlling said equipment for ...
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WO/2007/023280A1 |
A landing gear monitor for aircraft landing gear including a plurality of pairs of wheels on a bogie, in which the main strut oil pressure serves to indicate landing load and is monitored in relation to, respectively, the two-wheel mode ...
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WO/2007/015104A1 |
A semi-levered landing gear for an aircraft comprises a main shock absorber strut (1) connected to the airframe; a bogie beam (4) extending fore and aft of the airframe with forward and aft wheels (J, T) and a main pivot connection (5) t...
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WO/2007/005040A2 |
An adaptive landing gear system for use in an aircraft includes a plurality of leveling struts. Each leveling strut includes an adaptive portion and landing pad. Each adaptive portion includes a fluid reservoir. A change in the volume of...
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WO/2007/001353A2 |
Disclosed is an arrangement in which the main landing gear assemblies of a large commercial airplane are each joined to the airplane at four attachement points. Two of the attachment points connect the landing gear side brace (12) and dr...
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WO/2007/001715A2 |
The method of landing a flying wing type aircraft in a crosswind includes the steps of disengaging the nose landing wheel upon impact with the runway so that it is free to castor; and thereafter, engaging the nose wheel after a specific ...
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WO/2007/000411A1 |
The invention relates to a steering device for the landing gear (1) of an aircraft, said steering device being characterised in that it comprises at least one means which is used to rotate (2, 3, 4, 5) the wheels (6) of the landing gear ...
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WO/2006/136755A2 |
A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimen...
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WO/2006/138267A2 |
A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A...
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WO/2006/133902A1 |
Described are a method and a device for supporting the take-off rotation of an aircraft, which aircraft comprises on each side of the aircraft at least two main landing gear units (10, 20), arranged one behind the other, which main landi...
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WO/2006/131641A1 |
The invention relates to a system for opening and closing the flap (1) of a casing for the landing gear of an aircraft, said system comprising mechanical connection means between the landing gear and the flap. Said connection means compr...
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WO/2006/130944A1 |
The present invention introduces a number of protrusion airfoils (1, 2, 3, 4) molded as part of an airplane tire placing at both sides of the outside walls of the tire which rotate the wheels prior to the landing of the aircraft in order...
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WO/2006/105424A2 |
An onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum. Pressure sensors are mounted in relation to each of the landing gear struts. A ...
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WO/2006/101662A1 |
A brake assembly includes a mounting plate, pressure members disposed in a substantially coplanar manner relative to the mounting plate, and electric actuators mounted to the mounting plate. The electric actuators are configured to selec...
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WO/2006/091555A1 |
Systems (110) and methods for braking aircraft (100) are disclosed. These systems (110) and methods can be employed on multi-main gear aircraft to reduce the radius with which the aircraft (100) makes low speed, pivot turns. Further syst...
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WO/2006/081664A1 |
A new alternative uplock release assembly is provided. The assembly comprises a pivot pin having a first end and a second end and an internal bore, a release system operatively connected to the first end of the pivot pin, said release sy...
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WO/2006/071263A2 |
A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to th...
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WO/2006/071262A1 |
A landing gear system for an aircraft comprises a truck beam (22); at least one steerable axle (42) mounted to the truck beam for pivotal steering movement; a steering actuator (46) connected to the steerable axle; and a locking mechanis...
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WO/2006/070014A1 |
The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) join...
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WO/2006/053433A1 |
The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, e...
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WO/2006/048519A1 |
According to the invention, the elevators (8) and/or the adjustable horizontal stabiliser (6) are operated in such a way that a negative lift (DP2) is generated and a nose-up moment (CDP) is thus created to counter the nose-down moment (...
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WO/2006/035132A2 |
A device (1) comprises an inertial reference station (7) for measuring the aircraft heading, an inertial reference unit (9) which is mountable on the wheel of a nose landing gear by means of a fixing system and is used for measuring the ...
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WO/2006/032811A1 |
The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control c...
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WO/2006/028859A2 |
A landing gear assembly for supporting a trailer. The landing gear assembly having first and second legs and a connecting member. Each leg is configured to selectively extend and retract in length. The connecting member operatively conne...
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WO/2006/028710A2 |
A landing gear assembly for supporting a trailer. The landing gear assembly having first and second legs and a connecting member. Each leg is configured to selectively extend and retract in length. The connecting member operatively conne...
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WO/2006/024145A1 |
The present invention provides a lock sensor for use in an actuator such as is used in aircraft landing gear systems. The lock sensor comprises at least one field emitting device (46) mounted on a locking actuator pressure vessel where t...
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WO/2006/024146A1 |
The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at l...
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WO/2006/022700A1 |
A weight-on-gear sensor for use on an aircraft with landing skids having a bracket and a displacement sensor attached to the bracket is disclosed. The bracket has a center member connecting a first end member to a second end member. The ...
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WO/2006/010890A1 |
Aircraft landing gear includes a retractable housing comprising an upper leg (11); a lower leg (15) including a wheel axle (16) slidingly disposed within the upper leg (11) and resiliently biassed to an extended condition; a turning coll...
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WO/2006/005550A1 |
In a commercial aircraft with a main deck (2) and a lower deck (5, 6), at least one passenger cabin (16, 16’) is also provided on the lower deck. The fuselage diameter lies on the order of a wide-body aircraft, and an energy-absorbing ...
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WO/2005/110828A1 |
In the field of avionics, it is difficult to justify initiation of new aircraft programmes for replacement of small numbers of niche aircraft. Instead, in many cases, retrofitting existing aircraft is preferred for economic reasons. In t...
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WO/2005/102839A2 |
Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The invention can provide motive force to the wheel when electri...
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WO/2005/100112A1 |
A brake controller function to optimally brake a wheel of a vehicle in motion, such as an aircraft. The brake pressure control self regulates by means of applying brake pressure in accordance with vehicle acceleration information and the...
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WO/2005/096721A2 |
A landing gear noise attenuator mitigates noise generated by airframe deployable landing gear. The noise attenuator can have a first position when the landing gear is in its deployed or down position, and a second position when the landi...
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WO/2005/095207A1 |
An aircraft wheel assembly including an axle housing means for sensing wheel speed, one end of the axle being covered by a cap member (10), the cap member (10) comprising a generally cuplike body (16) having an end wall (14) towards the ...
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WO/2005/077757A1 |
Methods and systems for performing landing gear operations. In one embodiment, a method for retracting a landing gear is useable with an aircraft having a gear door (128) that at least partially covers a gear well when the landing gear (...
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WO/2005/070761A2 |
An aircraft vehicular front wheel landing gear assembly is provided that includes a nonelastomeric outer upper strut tubular member (12) having an inner axial center bore (22) with a tubular cylindrical frictional interface inner surface...
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WO/2005/054027A1 |
A brake control system for an EMA-controlled brake (electromechanical actuator controlled brake) is disclosed that includes a brake controller (66, 68), at least one serial bus (70, 72, 74, 76) running from the brake controller (66, 68) ...
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WO/2005/035358A2 |
The present invention is a compound planetary gear system which has a moveable sun gear and a lockable sun gear to change the gear ratio between a high gear ratio and a pseudo 1:1 slipping ratio. The system makes use of a ratchet and paw...
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WO/2005/028304A2 |
In one embodiment the present invention includes a landing gear for an airplane comprising a plurality of connectors (102, 103,104,106,107) coupled to the airplane; a first support member (110) coupled to at least one of the plurality of...
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WO/2005/025982A1 |
The device for the self-rotation of aircraft landing gear wheels is made by attaching protrusions of the shape of a pyramid, a tetrahedron or a semi-cone on the lateral side of the wheel tires so that the wheels rotate by the resistance ...
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WO/2005/022101A1 |
The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit (6, 10, 11), a controllable microwave...
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WO/2005/022100A1 |
The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a processing unit, a plurality of controllable micro...
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WO/2005/022098A1 |
The load on an aircraft component, such as the load on or in a landing gear leg during braking, is measured with an all weather displacement measuring system. The system includes a processing unit, a controllable source (14) of laser lig...
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WO/2005/019026A2 |
An emergency floatation system for a helicopter includes a safety trigger device for inflating at least one raft during the course of an emergency. The safety trigger device includes a plurality of handles such that pulling any one of th...
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WO/2005/014390A2 |
Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft (140) and other flight devices or projectiles are described. In one embodiment, the aircraft (140) can be assembled fr...
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WO/2005/005252A1 |
A locking mechanism for aircraft landing gear has a hook (3) displaceable into and out of engagement with the landing gear capture pin (1). A roller (45) on a latch arm (40) engages a part (36) of the hook (3) to prevent it moving from a...
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