| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244102000 | Strut locks | 13 |
| 20080210813 | FRONT AIRCRAFT PART COMPRISING A FLAT PARTITION BETWEEN A PRESSURISED ZONE AND A NON-PRESSURISED ZONE HOUSING LANDING GEAR - The present invention relates to a front aircraft part ( | 09-04-2008 |
| 20080223984 | Aircraft comprising a landing gear compartment permitting better integration of the landing gear - The object of the invention is an aircraft comprising at least one gear compartment in which is adapted to be disposed a landing gear ( | 09-18-2008 |
| 20080272234 | Aircraft Landing Gear - Aircraft landing gear includes a retractable housing comprising an upper leg ( | 11-06-2008 |
| 20080277525 | HYDRAULIC DISTRIBUTOR FOR AIRPLANE LANDING GEAR - A hydraulic distributor | 11-13-2008 |
| 20090014582 | AIRCRAFT LANDING GEAR COMPRISING AN OPERATION STRUT DEVICE AND AIRCRAFT PROVIDED THEREWITH - An aircraft landing gear including a leg, a bracket which defines the axis of rotation of the leg on the operating plane defined by the leg extension and retraction positions and a leg operating device consisting of at least one strut whose first end is provided with a first means for connecting to the landing gear element and second end is provided with a second means for connecting to the element of the gear-receiving landing gear casing for which the at least one strut expands outside of the operating plane of the gear leg. | 01-15-2009 |
| 20090050736 | LANDING GEAR - A semi-levered landing gear for an aircraft comprises a main shock absorber strut ( | 02-26-2009 |
| 20090078822 | LANDING GEAR SYSTEM AND LOAD DISTRIBUTION - In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of hoop frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members. | 03-26-2009 |
| 20090084894 | LANDING GEAR - An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains. | 04-02-2009 |
| 20090095839 | RETRACTION CYLINDER AND ROTORCRAFT UNDERCARRIAGE FURNISHED WITH SUCH A RETRACTION CYLINDER - A retraction cylinder ( | 04-16-2009 |
| 20090159743 | CASING AND FRONT LANDING GEAR ASSEMBLY FOR AN AIRCRAFT - The casing comprises a wall defining an internal housing open on the bottom in order to allow the retraction of a corresponding front landing gear into the interior of the housing. The said wall separates the said non-pressurized internal housing from a surrounding pressurized zone of the aircraft. A reinforcement structure is provided around the wall on the side of the surrounding pressurized zone. The separation wall is a shell coming to envelop the shape of the front landing gear, on the side opposite the opening of the internal housing, and the reinforcement structure comprises on the one hand longitudinal reinforcement elements extending on both sides of the shell and on the other hand transverse reinforcement elements connecting the longitudinal reinforcement elements. The shell has a first zone of considerable width accommodating the wheels of the landing gear, a second zone of lesser width accommodating the rod of the landing gear, and a third zone running from the second zone of lesser width, becoming wider and accommodating a portion of the mechanism for deployment/retraction of the landing gear. As a variant or in combination, the shell has on the one hand a front area of considerable height accommodating the wheels of the landing gear and on the other hand a rear area of lesser height accommodating the rod and a portion of the mechanism for deployment/retraction of the said landing gear and above which there extends at least one transverse reinforcement element making it possible to provide support for an equipment item of the aircraft. | 06-25-2009 |
| 20090321560 | ADJUSTABLE LANDING GEAR SYSTEM - A landing gear system includes a shock strut assembly and a linkage member coupled to an aircraft. Preferably, the shock strut assembly and linkage member are oriented or angled relative to one another in a non-parallel relationship. Actuation of the linkage member moves the shock strut from a de-hiked to a hiked configuration or vice-versa. In addition, the orientation of the linkage member relative to the shock strut assembly permits it to automatically move the shock strut assembly to the de-hiked position during retraction of the landing gear system and prevents the shock strut assembly from exceeding a desired length during retraction. The linkage member may take the form of a hydraulic actuator having a lower end portion coupled to an inner cylinder of the shock strut assembly and an upper end portion coupled to the aircraft aft of where the shock strut assembly is coupled to the aircraft. | 12-31-2009 |
| 20100001129 | STORAGE COMPARTMENT FOR THE NOSE GEAR OF AN AIRCRAFT - A front landing gear storage compartment configured for an airplane including a set of retractable landing gears including a front gear centered on a longitudinal median plane of the fuselage. The storage compartment forms an impervious partition between a pressurized zone and the housing for the front gear in its retracted position, and includes a reinforced upper face including a more or less flat zone, more or less horizontal when the airplane is on the ground, so as to form a floor of a pressurized area of the airplane. | 01-07-2010 |
| 20100012779 | AIRCRAFT LANDING GEAR ACTUATOR - 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 a common body and operable independently from one another. A controller in communication with the actuator is configured to command the actuator between the stowed and deployed positions in response to an input. The controller commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive. | 01-21-2010 |
| 20100038478 | Actuator - An actuator comprising: two motors; an output member; and a harmonic gear comprising: an elliptical wave generator component; a flexible spline component which is coupled to the wave generator by a bearing and flexes to conform to the elliptical shape of the wave generator; and a circular spline component which surrounds and meshes with the flexible spline component. One of the harmonic gear components is coupled to the output member, and each of the other harmonic gear components is coupled to a respective one of the motors. | 02-18-2010 |
| 20100084509 | Aerodynamically-Assisted Landing Gear - Apparatus and methods provide for the use of a lift-producing body with a landing gear assembly in order to provide a lifting force during landing gear operations that reduces the load on the landing gear actuator. According to embodiments, the lift-producing body may be configured for attachment to the landing gear assembly. The lift-producing body may be reconfigured while the landing gear assembly is being retracted or deployed in order to maximize the aerodynamic lift created by the lift-producing body or to minimize the drag induced by the lift-producing body. | 04-08-2010 |
| 20100140394 | ROLLER SLOT DOOR MECHANISM - 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. | 06-10-2010 |
| 20100140395 | DOUBLE HOOK DOOR MECHANISM - The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors. | 06-10-2010 |
| 20100176240 | LANDING GEAR CASING WITH REDUCED SPACE REQUIREMENT - The invention relates to a landing gear casing that comprises a longitudinal box with walls defining an inner housing ( | 07-15-2010 |
| 20100219289 | PURGE DEVICE AND HYDRAULIC SYSTEM COMPRISING SUCH A PURGE DEVICE - Purge device and hydraulic system comprising such a purge device. The purge device ( | 09-02-2010 |
| 20100237188 | Movable main undercarriage for an aircraft - The airplane comprises a fuselage having frames, and at least two undercarriages each comprising a support and at least one wheel, the support being carried directly by the fuselage and being hinged to the fuselage about an axis that lies outside the frames. | 09-23-2010 |
| 20100264265 | LANDING GEAR ACTUATION CONTROL SYSTEM - A hydraulic control system for an aircraft landing gear system comprises a hydraulic pressure source connected to a hydraulic fluid pressure transmission line, and at least one hydraulic actuator for extending and/or retracting a landing gear, wherein first and second valves are provided in series along the hydraulic fluid pressure transmission line, the first and second valves being adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator. The control system also controls uplock actuators. | 10-21-2010 |
| 20100282901 | Pneumatic Blow-Down Actuator - 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 a ball screw. Further, the actuator includes a ball screw housing forming a chamber for receiving the ball screw. Specifically, the ball screw and the housing are in threaded engagement to translate rotation of the ball screw into axial extension of the housing. To power electromechanical extension of the actuator, the ball screw is selectively engaged to a motor with a gear train. Importantly, fluid communication between the ball screw housing and a pressurized fluid is selectively provided by a valve. If electromechanical extension of the actuator fails, the gear train is disconnected from the ball screw and the pressurized fluid is introduced into the chamber to drive pneumomechanical extension. | 11-11-2010 |
| 20110031348 | LANDING GEAR WITH COMPOSITE LEAF SPRING - An aircraft landing gear comprising: an arm mounted to a pivot and carrying one or more wheel assemblies; and a composite leaf spring which is coupled to the arm and arranged to provide a resilient biasing force which opposes rotation of the arm about the pivot. The arm can be made relatively stiff in comparison with the leaf spring, so that load is transferred directly into the pivot without a large amount of bending of the leg. The leaf spring shock absorber typically has a reduced part count compared with a conventional oleo-pneumatic shock absorber. By forming the leaf spring from a composite material, its weight is significantly reduced in comparison with a conventional metal spring, making it suitable for use on a relatively large aircraft. | 02-10-2011 |
| 20110042511 | APPARATUS FOR USE ON AN AIRCRAFT - An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone. | 02-24-2011 |
| 20110127376 | SYSTEM FOR OPENING AND CLOSING THE DOOR OF AN AIRCRAFT LANDING GEAR COMPARTMENT - The invention concerns a system for opening and closing a door ( | 06-02-2011 |
| 20110180662 | LANDING GEAR - A bogie-type landing gear for aircraft is provided. The landing gear includes at least one front wheel and at least one rear wheel connected to a beam, a rocking arm centrally and rotatably connected to said beam, and a shock absorbing element. The rocking arm ends and the shock absorbing element, which are distal to the wheels, are articulated on a lever element hinged on the aircraft frame, onto which an actuator assembly for rotating said lever element urges between a position in which the wheels are in an operative configuration and a position in which the wheels are retracted in the landing gear bay. | 07-28-2011 |
| 20110186680 | Aircraft landing gear - An aircraft landing gear for an aircraft having an engine, an outer surface, a cavity formed in the outer surface, a cover arranged to close the cavity, the landing gear being arranged to be movable between a stowed configuration, in which it is stowed in the cavity, and a deployed configuration, the landing gear comprising an engine debris guard panel arranged to inhibit tyre propelled debris striking the engine whilst the landing gear is in the deployed configuration, wherein the guard panel is arranged to form at least a part of the cover when the landing gear is in the stowed configuration. | 08-04-2011 |
| 20110204182 | ROTARY WING AIRCRAFT PROVIDED WITH AN EMERGENCY UNDERCARRIAGE - A rotary wing aircraft ( | 08-25-2011 |
| 20110233328 | MULTIFUNCTIONAL ELECTROMECHANICAL DEVICE FOR LANDING GEAR - The invention provides a multifunction electromechanical device for an aircraft undercarriage, the device comprising at least: | 09-29-2011 |
| 20110260000 | ENERGY ABSORBER SYSTEM FOR AN UNDERCARRIAGE, AND AN AIRCRAFT PROVIDED WITH SAID ENERGY ABSORBER SYSTEM - An energy absorber system ( | 10-27-2011 |
| 20110303788 | PIN BEARING ARRANGEMENT FOR AIRCRAFT LANDING GEAR - Pin bearing arrangement ( | 12-15-2011 |
| 20120043418 | METHOD OF ATTENUATING NOISE IN AIRCRAFT, LANDING GEAR STRUCTURE OF AIRCRAFT, AND AIRCRAFT - If an engine undergoes high-load operations immediately after it is started up from its cold state, a thermostat is closed to inhibit passage of cooling water through the inside of the engine, and the cooling water stagnant in a cylinder head receives heat from a combustion chamber. Therefore, the cooling water will possibly boil. However, the thermostat is formed in such a manner that a valve body may be opened forcedly if the discharge flow rate of a water pump is greater than the flow rate in a normal use region. Therefore, in such a situation, the discharge flow rate of the water pump is increased greater than the flow rate in the normal use region to open the valve body with good response, thereby passing water into the engine quickly. This configuration prevents the cooling water stagnant in the cylinder head from boiling before the valve body is opened completely. | 02-23-2012 |
| 20120091271 | LANDING GEAR - A semi-levered landing gear for an aircraft includes a main shock absorber strut, a bogie beam and an auxiliary actuator mechanism. The bogie beam extends fore and aft of an airframe of the aircraft with forward and aft axles for respective forward and aft wheels, and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut. The auxiliary actuator mechanism includes a spring unit pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point offset from the pivot connection of the upper portion to the aircraft fuselage. During stowing the strut and spring unit pivot together about different pivot points, causing a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position. | 04-19-2012 |
| 20120119025 | LANDING GEAR - An auxiliary actuator mechanism includes a lever, a spring unit and a control linkage. The lever is pivotally connected to the upper portion of a main shock absorber strut, and pivotable between an upper position for take-off, and a lower position. The spring unit is pivotally connected at an upper end to the lever and at a lower end to the bogie at an auxiliary pivot forward of the main pivot. The control linkage is connected between the lever and the upper portion of the main shock absorber strut to define the upper predetermined position of the lever. The control linkage is connectable to an anchor point that moves relative to the upper portion of the main shock absorber strut during stowing, and is operated by initial stowing movement of the stowing mechanism to lower the lever from the upper position to a stowing position. | 05-17-2012 |
| 20120153078 | FRONT PART OF AN AIRCRAFT FUSELAGE INCORPORATING A BAY FOR STOWING LANDING GEAR - A front part of an aircraft fuselage according to this invention comprises:
| 06-21-2012 |
| 20120193470 | Wide-body supersonic airliner - An airliner in which the wheel bogies of the main landing gear are stored one behind the other in a narrow, hollow keel at the bottom of the fuselage. The narrow keel replaces the usual voluminous hold under the passenger cabin. This decreases the cross-sectional area of the fuselage, to reduce aerodynamic drag. | 08-02-2012 |
| 20120234971 | Wireless Power Transmission System and Method for an Aircraft Sensor System - An aircraft sensor system including a primary module configured to be attached to an aircraft portion and operative to transmit electrical power wirelessly. A secondary module configured to be attached to an aircraft component, the secondary module operative to receive electrical power wirelessly from the primary module. At least one sensor configured to be operatively attached to a portion of the aircraft component and electrically coupled to the secondary module, wherein the at least one sensor is operative to measure a desired parameter of the aircraft component. | 09-20-2012 |
| 20120305703 | LANDING GEAR - A landing gear, including an elongate axle pivotally connected to a bogie beam, the landing gear further including a locking device for locking the axle at a substantially fixed orientation with respect to the bogie beam, the locking device including first and second barrier arms that are movable between a first configuration, in which they define a barrier so as to maintain the maintain the axle in the substantially fixed orientation with respect to the bogie beam, and a second configuration, in which the axle may pivot about the bogie beam. | 12-06-2012 |
| 20130026291 | AIRCRAFT LANDING GEAR - A method, apparatus and software are disclosed for enabling asymmetric deployment or retraction of aircraft landing gear. | 01-31-2013 |
| 20130068885 | LANDING GEAR RETRACTION/EXTENSION DEVICE OF AIRCRAFT - A landing gear retraction/extension device includes a hydraulic actuator, a hydraulic circuit, a hydraulic pump, an electric motor, and a driver. Part of the hydraulic circuit is provided such that heat is exchangeable between operation oil and each of the electric motor and the driver. The driver supplies power to the electric motor before landing of an aircraft such that an operation oil temperature is higher than a predetermined temperature upon the landing of the aircraft. | 03-21-2013 |
| 20130099053 | Mid-Wing Multi-Deck Airplane - An airplane comprises a twin-deck fuselage in which an upper deck support structure is utilized for carry-through of a mid-mount main wing box. The main landing gear of the airplane is mounted to the fuselage and is stowed in a non-pressurized area below the main wing box (enabled due to an optimized wing box geometry). A pressurized passageway/cargo/galley complex separates the main landing gear box and the main wing box. The upper deck is continuous, while the lower deck is separated by the wheel wells into two distinct fore and aft areas (for either cargo or passengers). The airplane further comprises an integrated vertical fin and an aft-extended pressurized deck area for reduced double-deck wetted area. More specifically, the double-deck pressurized fuselage structure is extended to form a blending structure to which a structural box of the vertical fin is attached. | 04-25-2013 |
| 20130105624 | LANDING GEAR, AN AIRCRAFT, AND A METHOD | 05-02-2013 |
| 20130119197 | A DEVICE FOR UNLOCKING AN UNDERCARRIAGE IN A DEPLOYED POSITION, AND AN UNDERCARRIAGE FITTED WITH SUCH A DEVICE - A simple device for blocking and unblocking the locking member of an undercarriage having a breaker strut and including an unlocking device. The device comprises. a rotary actuator of axis parallel to the hinge axis of the links of the stabilizing member; a crank connected to a shaft of the actuator; a pawl hinged to the end of the crank and including a step; a pin secured to and at a distance from one of the links of the stabilizing member; and return means for urging the pawl towards the pin. The actuator is actuatable between a first angular position in which the pin is in contact with the pawl facing the step while the links are substantially in alignment, and a second angular position that the crank reaches when the step of the pawl has pushed back the pin, taking the links of the stabilizer member out of alignment. | 05-16-2013 |
| 20130146706 | METHOD AND A ROTARY WING AIRCRAFT OPTIMIZED FOR MINIMIZING THE CONSEQUENCES OF A RUNNING OFF-SPECIFICATION EMERGENCY LANDING - A method of minimizing the consequences of an off-specification landing for the occupants of an aircraft ( | 06-13-2013 |
| 20130186998 | LANDING GEAR - A landing gear, including an elongate axle pivotally connected to a bogie beam, the landing gear further including a locking device for locking the axle at a substantially fixed orientation with respect to the bogie beam, the locking device including first and second barrier arms that are movable between a first configuration, in which they define a barrier so as to maintain the maintain the axle in the substantially fixed orientation with respect to the bogie beam, and a second configuration, in which the axle may pivot about the bogie beam. | 07-25-2013 |
| 20130228649 | METHOD OF EXTENDING AIRCRAFT UNDERCARRIAGES IN EMERGENCY MODE - A method of actuating undercarriage latching boxes and associated hatch latching boxes of an aircraft in an emergency mode, the latching boxes having at least one feed port and at least one unlatching member that is operable when the port is fed with fluid under pressure, the aircraft also being provided with a hydraulic braking circuit. The method includes connecting at least one tapping circuit to the braking circuit of the aircraft in association with an isolation valve that is kept, in a normal mode, in an isolation state and that can be controlled to be placed in an open state in which at least some of the feed ports of the latching boxes are fed by the tapping circuit connected to the braking circuit. | 09-05-2013 |
| 20130264418 | METHOD OF MANAGING SYSTEMS ASSOCIATED WITH THE LANDING GEAR OF AN AIRCRAFT - The invention relates to a method of managing an aircraft having undercarriages carrying a certain number of braked wheels, the aircraft including:
| 10-10-2013 |
| 20130299631 | DRIVE SCREW ASSEMBLY AND LANDING GEAR ASSEMBLY WITH SAME - A landing gear assembly includes a leg that may be rotated between retracted and extended positions, a link assembly, and a drive screw assembly. The drive screw assembly includes a casing, a piston slidably coupled to the casing for reciprocation relative to the casing and a portion mounted to the link assembly and where the drive screw assembly is capable of locking and unlocking. | 11-14-2013 |
| 20130299632 | MOTORIZED AEROPLANE WITH HYBRID HYDRODYNAMIC AND AERODYNAMIC STRUCTURE FOR TAKING OFF AND LANDING ON WATER, THE GROUND OR SNOW - An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged downwards in the form of an inverted V. The junction between each hydrofoil and the fuselage is situated forward from the centre of gravity of the aeroplane. The distance separating the junction between each hydrofoil and the fuselage, with respect to the centre of gravity of the aeroplane is comprised between 0 and 170% of the mean aerodynamic chord of the main wing of the aeroplane, preferably between 20% and 135%. Each hydrofoil is inclined downwards, from its leading edge in the direction of its trailing edge. The straight line connecting these two edges form, a nominal pitch angle comprised between 2 and 12°, preferably between 6 and 8°. The part of the hydrofoil located beneath the tangential plane is situated forward from the centre of gravity. | 11-14-2013 |
| 20140077032 | Vertical Support System - A vertical support system includes a first articulated leg assembly configured to carry a first load, the first articulated leg assembly being selectively movable between a first retracted configuration and a first loaded configuration and a second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly being selectively movable between a second retracted configuration and a second loaded configuration, wherein a lateral width ratio is equal to a value of less than about 0.6, the lateral width ratio being defined as a ratio of (1) a maximum lateral width when the first articulated leg assembly and the second articulated leg assembly are in a retracted configuration to (2) a maximum lateral width when the first articulated leg assembly and the second articulated leg assembly are in a loaded configuration. | 03-20-2014 |
| 20140151501 | ELECTRO HYDROSTATIC ACTUATOR SYSTEM FOR RETRACTING/EXTENDING LANDING GEAR - An electro hydrostatic actuator system for retracting/extending a landing gear includes a plurality of hydraulic actuators and a plurality of hydraulic supply sources each including a single hydraulic pump and a single electric motor and provided in parallel to each other. In a normal state, the hydraulic supply sources together supply operation oil sequentially to the hydraulic actuators. When any of the hydraulic supply sources is failed, the other hydraulic supply source(s) other than the failed hydraulic supply source supplies operation oil sequentially to the hydraulic actuators. | 06-05-2014 |
| 20140263833 | LANDING GEAR - In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position. | 09-18-2014 |
| 20150069178 | FUSELAGE-MOUNTED LANDING GEAR ASSEMBLY FOR USE WITH A LOW WING AIRCRAFT - An aircraft comprises at least one wing comprising a trailing edge flap that is selectively moveable between a stowed position and an extended position. The aircraft also includes a fuselage comprising a first gear door on a side of the fuselage and a second gear door on a bottom of the fuselage. The first gear door is moveable in a gear door envelope between a closed position and an open position. The wing is coupled to the fuselage in a low-wing configuration. A landing gear assembly is coupled to the fuselage and is selectively moveable between a retracted position and a deployed position. The trailing edge flap may be extended simultaneously with, before, or after deployment of the landing gear assembly and opening of the first gear door. | 03-12-2015 |
| 20150083857 | LANDING GEAR FAIRING - An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels. | 03-26-2015 |
| 20150122945 | PASSENGER AIRCRAFT WITH AUTOMATICALLY DEPLOYABLE AND/OR RETRACTABLE LANDING GEAR - In embodiments, a passenger aircraft includes a body and a landing gear member that is retractable and deployable with respect to the body. The passenger aircraft also includes an altitude detection system. The landing gear member may become deployed automatically if a deploy condition related to the detected altitude is met, and/or retracted automatically if a retract condition related to the detected altitude is met. Accordingly, the action of deploying and/or retracting the landing gear becomes something that the pilot need only supervise, instead of doing. In addition, embodiments may become a helpful safety feature, in the event the pilot has become distracted. | 05-07-2015 |
| 20150144735 | METHOD FOR REDUCING THE APPARENT MANOEUVRING TIME FOR LANDING GEAR OF AN AIRCRAFT - The invention relates to a method for controlling the manoeuvring of the landing gear of an aircraft, in which at least one of the steps of pulling on the doors of the bay to relieve the door retaining hook, actuating the door hook or hooks to free the doors and opening the doors is executed in response to the detection of a flight situation suitable for the occurrence of a manoeuvre order, even before the manoeuvre order is received. | 05-28-2015 |
| 20150298798 | BOGIE BEAM ARTICULATION MECHANISM - A bogie articulation mechanism is provided comprising, for example, a first torque link and a second torque link coupled for rotation about a pivot joint, the first torque link coupled to a bogie beam, a pitch trimmer having a first terminus and a second terminus, the first terminus coupled to the pivot joint, a bell crank having a pivot point, a first coupling point and a second coupling point, first coupling point couple to the second terminus of the pitch trimmer, and a reaction link coupled to the second coupling point of the bell crank. | 10-22-2015 |
| 20150307185 | AIRCRAFT COMPRISING TWO LANDING GEAR DOORS AND A MANEUVERING SYSTEM INTENDED TO MANEUVER SAID DOORS - An aircraft comprising a first door and a second door, each being mobile between an open position and a closed position, and a maneuvering system. The maneuvering system includes an actuation mechanism, a first transmission chain configured to transmit the movements of the actuation mechanism to the first door, a second transmission chain configured to transmit the movements of the actuation mechanism to the second door. Such a maneuvering system uses a single actuation mechanism, which results in a simplification of the mechanism and a weight saving. | 10-29-2015 |
| 20160016657 | AIRCRAFT LANDING GEAR PROVIDED WITH AN ADJUSTABLE ROLLER - The invention relates to an aircraft undercarriage intended to be mounted so as to be able to move on the aircraft between a deployed position and a retracted position, the undercarriage comprising a roller ( | 01-21-2016 |
| 20160052623 | LANDING GEAR ASSEMBLY - The present invention provides a landing gear assembly for an aircraft landing gear, the assembly comprising a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, and an actuator arranged to actuate both the steering mechanism and the deployment mechanism. The invention also provides an aircraft landing gear, an aircraft and methods of operating an aircraft landing gear. | 02-25-2016 |
| 20160068260 | Stretchable Mesh for Cavity Noise Reduction - A stretchable mesh material extends across the opening of a cavity of the landing gear of an aircraft when the landing gear is in the deployed position. The mesh material alters the flow of air across the opening of the landing gear cavity and significantly reduces the amount of noise produced by the wheel well at low-to-mid frequencies. | 03-10-2016 |
| 20160114884 | METHOD OF FABRICATING A FORCE TRANSFER PART HAVING A LUG MADE OF COMPOSITE MATERIAL, AND A PART OBTAINED BY SUCH A METHOD - The invention provides a method of fabricating a force transfer part ( | 04-28-2016 |
| 20160129994 | LANDING GEAR WITH STRUCTURAL LOAD PATH DIVERTER BRACKET - A landing gear support arrangement may comprise a cylinder, a pin pivotally coupled to the cylinder, a head attached to the pin having a portion extending radially from the pin, and a bracket coupled to the portion of the head configured to axially support the pin. | 05-12-2016 |
| 20160137294 | AIRCRAFT ASSEMBLY WITH LOAD AND POSITION INDICATOR - An aircraft assembly ( | 05-19-2016 |
| 20160159468 | Multi-position Landing Gear - A multi-position landing gear for an aircraft may include a first landing skid disposed on a bottom side of the aircraft, and a second landing skid disposed on one of a top side or the bottom side of the aircraft, wherein the first landing skid and the second landing skid are rotatable relative to the aircraft. | 06-09-2016 |
| 20160159495 | AIRCRAFT LANDING GEAR ASSEMBLIES WITH NON-ROTATING LIGHT ELEMENT CLUSTERS - Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections. | 06-09-2016 |
| 20160167770 | SPRING ASSEMBLY FOR AIRCRAFT COMPONENTS | 06-16-2016 |
| 20160176513 | AIRCRAFT NOSE PROVIDED WITH A CONNECTING FRAME BETWEEN THE LANDING GEAR HOUSING AND THE OUTER SKIN OF THE FUSELAGE | 06-23-2016 |
| 20160200423 | NOSE LANDING GEAR ARRANGEMENTS INCLUDING A FLEXIBLE SHEET AND METHODS FOR MAKING THE SAME | 07-14-2016 |
| 20190144104 | METHODS OF MOVING AN AIRCRAFT UNDERCARRIAGE BETWEEN A RETRACTED POSITION AND A DEPLOYED POSITION | 05-16-2019 |
| 20080237396 | AUXILIARY NOSE UNDERCARRIAGE, A FORCE-TRANSMISSION STRUCTURE, AND A ROTARY WING AIRCRAFT - A steerable auxiliary nose undercarriage ( | 10-02-2008 |
| 20080308672 | METHODS AND SYSTEMS FOR OPERATING AIRCRAFT LANDING GEARS - 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 that at least partially covers a gear well when the landing gear is extended. The method can include receiving a first signal during movement of the aircraft down a runway for takeoff. The first signal can correspond to at least a first aspect of motion of the aircraft, such as upward rotation of the aircraft for liftoff. The gear door can be opened in response to receiving the first signal. The method can further include receiving a second signal after the aircraft has lifted off of the runway. The second signal can correspond to a second aspect of motion of the aircraft, such as the aircraft achieving a positive rate of climb. In response to receiving the second signal, the landing gear can be retracted into the gear well. | 12-18-2008 |
| 20090057484 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly comprises a four bar linkage arranged to be pivotably attached to an aircraft fuselage and movable between a deployed position and a retracted position, wherein when in the retracted position at least a first portion of the landing gear assembly is housed within a wing at the aircraft. | 03-05-2009 |
| 20090108131 | RETRACTABLE ARTICULATED LANDING GEAR - A landing gear for an aircraft, characterized by upper and lower pintle frame members ( | 04-30-2009 |
| 20090127389 | System for opening and closing the flap of a casing for the landing gear of an aircraft - The invention relates to a system for opening and closing the flap ( | 05-21-2009 |
| 20090250552 | Actuator - An actuator comprises an actuator shaft mounted for rotation by a drive shaft, releasable lock means operable to restrict axial movement of the actuator shaft relative to the drive shaft, and an output member co-operating with the actuator shaft such that rotation of the actuator shaft drives the output member for translating movement relative to the actuator shaft. | 10-08-2009 |
| 20090283634 | LOCKING MECHANISM WITH BI-MODAL ACTUATOR - 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 one version, each of the actuator components can individually engage a mechanical detent to enable unlocking of the movable component, for use, for example, in an uplock mechanism for aircraft. | 11-19-2009 |
| 20100032521 | LANDING GEAR CASING PROVIDED WITH A DISSOCIATED STRUCTURE - A reduced-volume casing for a landing gear including a chassis for fixing and taking up loads, to which the landing gear is exposed and an envelope-type structure arranged on the chassis for taking up pressurization forces. The chassis can include, in particular, a frame which is even to the output opening of the landing gear and is provided with beams used for receiving means for maintaining the fastening bearings of the gear and also including polygons which are used for receiving the fastening bearings of the gear manoeuvring strut and are fixed to the beams, wherein the beams and polygons form a lattice structure. | 02-11-2010 |
| 20100116930 | LANDING GEAR - In an aircraft having an aircraft landing gear, the aircraft landing gear includes an arm, a leg and a bogie at the lower end of the leg. The bogie is moveable in a direction along the length of the leg and pivotable between a trimmed deployed position and a stowable position. The arm is mounted on the landing gear and is rotatable between a first position in which the bogie is positioned in the trimmed deployed position, and a second position in which the bogie is positioned in the stowable position. Movement of the arm can be effected by a positioning rotary actuator, which is not located in the primary or secondary load paths. | 05-13-2010 |
| 20100181422 | NOSE LANDING GEAR ARRANGEMENT FOR AN AIRCRAFT AND AN AIRCRAFT HAVING SUCH AN ARRANGEMENT - A nose landing gear arrangement comprises a leg assembly with a pivot axis A at one end thereof and a landing gear wheel mounting at the other end thereof. Two stays are provided, each stay being mounted at one end thereof to the leg assembly and mountable at the other end thereof to an aircraft. Each stay comprises an upper stay part and a lower stay part which are hinged together by means of a simple hinge. The upper stay part has a cardan joint at its end spaced from the hinge to enable hinged mounting to an aircraft. The lower stay part has a cardan joint at its lower end spaced from the hinge, the cardan joint of the lower stay part hingedly mounting the lower stay part to the leg assembly. The leg assembly and the stays are arranged so that the stays extend from the leg assembly on opposite sides thereof and the stays fold into a stowed position so that they lie substantially alongside the leg assembly when the leg assembly is retracted. | 07-22-2010 |
| 20100243797 | Landing Gear Mechanism for Model Airplane - A radio controlled model airplane has landing gear including a wheel rotatably mounted on a strut. The wheel and strut are retractable into the airplane wing. The strut is angled forwardly relative to the wing surface where the strut is attached such that the wheel is forward of the airplane center of gravity just prior to takeoff and touchdown. The landing gear includes a control assembly mounted on the wing. The control assembly includes a housing and a pivot pin on which the strut is mounted. The pivot pin is rotatable and pivotable around one of its ends. The control assembly also includes a cam which causes the pivot pin to pivot upon rotation, thereby causing the strut to move through a plane oblique to the wing. | 09-30-2010 |
| 20110049293 | RETRACTABLE UNDERCARRIAGE FOR AN AIRCRAFT - An undercarriage for a rotary wing aircraft, includes a tubular structure ( | 03-03-2011 |
| 20110147518 | Aircraft Landing Gear - A landing gear for an aircraft, having mounting means fitted to the fuselage of the aircraft; at least one wheel; and at least one supporting arm having a first end portion connected to the mounting means, and a second end portion opposite the first end portion, and to which the wheel is suspended. The first end portion of the supporting arm has a seating portion fitted in rotary manner to a pin connected to the mounting means and extending crosswise to the supporting arm; and an electrically controlled actuator is fitted to the seating portion, and is activated selectively to rotate the supporting arm, about the pin, between a first and second operating position defining a stowed in-flight configuration and a lowered landing configuration of the landing gear respectively. | 06-23-2011 |
| 20110174924 | LANDING GEAR MECHANISM FOR AIRCRAFT - Landing gear mechanism for aircraft comprising at least a first connecting arm ( | 07-21-2011 |
| 20110233327 | SEMI-LEVERED LANDING GEAR AND ASSOCIATED METHOD - A semi-levered landing gear is provided that includes a shock strut, a truck beam pivotally connected to the shock strut and a semi-levered landing gear mechanism including at least three links configured to angularly orient the truck beam and a truck pitch actuation system operatively connected to at least one of the three links. The landing gear mechanism may be configured to cooperate with an extension of a shock strut by positioning the truck pitch actuator in a retracted position, thereby positioning a forward end of the truck beam in a raised position relative to the aft end of the truck beam. The landing gear mechanism may also be configured to cooperate with a retraction of the shock strut into the wheel well by extending the truck pitch actuator to position a forward end of the truck beam in a lower position relative to the aft end of the truck beam. | 09-29-2011 |
| 20120080558 | UNDERCARRIAGE, AN AIRCRAFT INCLUDING SAID UNDERCARRIAGE, AND A METHOD OF LANDING SAID AIRCRAFT - An undercarriage ( | 04-05-2012 |
| 20120080559 | METHOD FOR OPERATING A LANDING GEAR ASSEMBLY WITH A BREAKER STRUT - A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut ( | 04-05-2012 |
| 20120111999 | VERTICALLY RETRACTING SIDE ARTICULATING LANDING GEAR FOR AIRCRAFT - A side articulating main landing gear assembly for an aircraft is disclosed which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking. | 05-10-2012 |
| 20120112000 | NOSE GEAR OF AN AIRCRAFT COMPRISING A SINGLE CONTROL DEVICE FOR RETRACTION AND STEERING - A landing gear of an aircraft, including a strut including two arms forming a rotational axis for retracting the gear, a rotating tube mounted in a mobile manner such that it rotates inside the strut about a pivoting axis, a sliding rod that is mobile in a translatory manner in the rotating tube along the pivoting axis, and carries wheels of the gear at one of its ends, and at least one bearing point that is located on one of the elements of the gear at a distance from the retraction axis and can bear necessary efforts for the retraction, the bearing point being located on the rotating tube. | 05-10-2012 |
| 20120145827 | AIRCRAFT LANDING GEAR UNLOCK ACTUATOR - This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition. | 06-14-2012 |
| 20120168561 | FUSELAGE MOUNTED LANDING GEAR - A landing gear for an aircraft. The landing gear may have a wheel/truck assembly, an oleo strut/support frame for supporting the wheel/truck assembly, and a retraction assembly attached to the oleo strut/support frame, the retraction assembly for moving the landing gear between a deployed position and a retracted position. The retraction assembly may have a pivoting trunnion brace attached to the oleo strut/support frame and to a fuselage of the aircraft for positioning the wheel/truck assembly, the oleo strut/support frame and the retraction assembly at least substantially fully within the fuselage of the aircraft in the retracted position. | 07-05-2012 |
| 20120168562 | DEVICE FOR CONTROLLING TRAPDOORS CLOSING THE HOLD OF AIRCRAFT LANDING GEAR - A device for driving at least one door ( | 07-05-2012 |
| 20120217341 | MAIN LANDING GEAR WITH RIGID REAR STAY - 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 the aircraft fuselage; a shock strut pivotally coupled at a first end to the elongate beam and coupled at a second end to a wheel assembly; a folding forward stay pivotally coupled at a first end to the elongate beam and pivotally coupled at a second end to the shock strut; and a rigid rear stay pivotally coupled at a first end to the aircraft and pivotally coupled at a second end to the shock strut, the rigid rear stay being arranged to restrain the path of the shock strut when moving between a deployed and a retracted position such that the wheel assembly is located forward and inboard in the retracted position in comparison with its location in the deployed position. | 08-30-2012 |
| 20120292443 | DOUBLE HOOK DOOR MECHANISM - The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors. | 11-22-2012 |
| 20130020436 | AIRCRAFT LANDING GEAR OF THE ROCKER-ARM AND DEFORMABLE-PARALLELOGRAM TYPE - The invention relates to an aircraft landing gear of deformable-parallelogram type, including:
| 01-24-2013 |
| 20130056582 | LANDING GEAR MOUNTED UNDER AN AIRCRAFT WING - A landing gear mounted under an aircraft wing is provided. The aircraft can comprise a fuselage and wings each comprising at least one longitudinal spar connected to a wing box being part of the structure of the fuselage. The landing gear can comprise one leg that pivots, on its upper end, around a rotation axis to occupy at least one extended position and one retracted position and which is provided, on its lower end, with rolling means, the leg being connected, on its upper end, to the longitudinal spar of said wing. The landing gear can also comprise at least one inclined front strut connected, on its lower end, to said leg and connected, on its upper end, to the structure of the fuselage thru connecting means. The connecting means can comprise a sliding bearing crossed by at least one part of the upper end of said strut. | 03-07-2013 |
| 20130068884 | MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS JOINED TO THE STRUCTURE OF THE AIRCRAFT IN AN ARTICULATED MANNER - An aircraft undercarriage comprising two rocker beams ( | 03-21-2013 |
| 20130134259 | FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR - A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another. | 05-30-2013 |
| 20130181091 | ELECTRICAL ACTUATOR INCORPORATING A FREE PLAY MECHANISM TO ELIMINATE FORCE FIGHTING - An actuator which is operable in response to one of an electrical and an electro-mechanical input signal is provided. The actuator includes an outer casing defined about a central axis, an output shaft disposed within the casing, the output shaft being axially moveable over a stroke length. Further, the actuator also includes a drive mechanism co-operable with the output shaft to drive the output shaft along a part of the stroke length, wherein the actuator is configured such that the output shaft is drivable along all or part of the remainder of the stroke length by external loading while being unconstrained by the drive mechanism. | 07-18-2013 |
| 20130233968 | AIRCRAFT LANDING GEAR - An aircraft landing gear including: a main strut having an upper portion arranged to be coupled to the underside of an aircraft and a lower portion telescopically mounted with respect to the upper portion; a bogie including a bogie beam pivotally coupled to the lower portion of the main strut, the bogie beam having a plurality of axles mounted on it, each axle carrying one or more wheel assemblies; an actuator arranged such that a change in its effective length causes a change in the angular position of the bogie relative to the main strut, and a control port arranged to be coupled to a control fluid supply system, wherein the aircraft landing gear includes or is in combination with a control valve having a first configuration in which it permits control fluid to be supplied to the control port of the actuator at a first pressure and a second configuration in which the control valve permits the supply of control fluid to the control port at a second pressure less than the first pressure so as to reduce loads experienced by components of the actuator during taxiing. | 09-12-2013 |
| 20130256455 | METHOD OF POSITIONING LANDING GEAR - A method of positioning landing gear of an airplane is provided that includes providing the landing gear including a shock strut, a truck beam operatively pivotally connected to the shock strut, first and second interconnected links operatively connected to the truck beam and a third link extending between the shock strut and the first and second links with the third link pivotally connected to the second link at a third pivot. When the landing gear is commanded to a lowered position, the third pivot is positioned in a first position to support a taxi mode, a take-off mode and a landing mode if the landing gear is operational and in a second position to support an alternate landing mode if the landing gear is not fully operational. When the landing gear is commanded to a raised position, the third pivot is in the second position to support a stow mode. | 10-03-2013 |
| 20130313360 | LANDING GEAR FOR AN AIRCRAFT - The invention provides a landing gear | 11-28-2013 |
| 20140151500 | DEVICE FOR INTERMEDIATE FASTENING BETWEEN AN AIRCRAFT FUSELAGE AND AN AIRCRAFT LANDING GEAR - A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls. | 06-05-2014 |
| 20140197275 | AIRCRAFT LANDING GEAR AND METHOD OF OPERATING THE SAME - A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss, where actuation of the actuator causes the extension plates to move up or down with respect to the truss raising and lowering the wheels. | 07-17-2014 |
| 20140197276 | AIRCRAFT LANDING GEAR AND METHOD OF OPERATING THE SAME - A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where refraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead. | 07-17-2014 |
| 20140209738 | DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT - A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated. | 07-31-2014 |
| 20140246542 | Front landing-gear well - A forward part of an aircraft comprising a fuselage and a landing gear well housing a forward landing gear comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, configuration in which said breaker strut lies in a strut plane parallel to the transverse direction of the forward part. The forward part comprises a transverse beam resisting strut reactions located above the landing gear well and mounted on the fuselage at its two ends, the beam having a globally rectangular cross-section, in which the median plane parallel to the length of the rectangle is coincident with said strut plane. | 09-04-2014 |
| 20140263832 | MULTIFUNCTION DEVICE FOR AN UNDERCARRIAGE - A multifunction device for an undercarriage, the device comprising at least a first shaft rotatably mounted on the aircraft to rotate about an axis of rotation that is substantially parallel to a hinge axis hinging the undercarriage to the aircraft, a telescopic second shaft rotatably mounted in the undercarriage and extending down along the undercarriage to the proximity of wheels carried thereby, and motor means adapted to cause the first shaft to rotate. The telescopic second shaft is a single shaft and it extends inside the undercarriage to the proximity of an axle carrying the wheels of the undercarriage, being connected to a differential connected to the wheels via drive shafts extending inside the axle. | 09-18-2014 |
| 20140346273 | Active Semi-Levered Landing Gear - An active oleo system for an aircraft semi-levered landing gear system disclosed herein includes a main strut, an auxiliary strut, bogie beam, and a pressure boost mechanism. During a takeoff roll phase, the pressure boost mechanism may increase the pressure in the main strut, forcing the main strut piston to the fully extended length. Thru the action of main strut, auxiliary strut, and bogie beam this may increase the height of the aircraft above ground, providing for a larger achievable rotation angle of the aircraft. | 11-27-2014 |
| 20150041587 | LANDING GEAR - A landing gear for an aircraft having a main fitting arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm movably coupled to the main fitting. A torsion spring is coupled to the trailing arm such that the movement of the trailing arm causes torsion loading of the torsion spring. A stay assembly is provided which comprises the torsion spring, the stay assembly having a first condition in which it is arranged to react axial loading thereof so as to maintain the main fitting in the deployed condition and a second condition in which it is arranged to permit the main fitting to move between the stowed condition and the deployed condition. | 02-12-2015 |
| 20150097080 | ROCKING BOGIE MECHANISM - A rocking bogie mechanism may include an upper link, a lower link, a central link, a forward link, an articulation actuator, a trimmer, and a bell crank. The upper link may be coupled to a cylinder at a first joint. The lower link and trimmer may be coupled to the piston at second joint. The upper link, lower link, and central link may be coupled at a third joint. The articulation actuator may be coupled to the upper link at a fourth joint. The trimmer and bell crank may be coupled at a fifth joint. The central link and bell crank may be coupled at a sixth joint. The articulation actuator and bell crank may be coupled at a seventh joint. The central link and forward link may be coupled at an eighth joint. The forward link may be coupled to a bogie beam at a ninth joint. | 04-09-2015 |
| 20150291278 | LANDING GEAR DEPLOYMENT SYSTEMS AND METHODS - Some embodiments provide apparatuses configured to deploy a landing gear of an aircraft, comprising: a landing gear coupler configured to couple with the landing gear; a release link configured to cooperate the landing gear coupler with a drive shaft that is configured to drive the landing gear between a stowed position and a deployed position; an override driver cooperated with the landing gear coupler; wherein the release link is configured to releasably maintain a relative position of landing gear coupler relative to the drive shaft, and the release link is configured to disengage a coupling between the drive shaft and the landing gear coupler such that the landing gear coupler is configured to move independent of the drive shaft; and wherein the override driver is configured to drive the landing gear coupler to the deployed position. | 10-15-2015 |
| 20150314860 | LANDING GEAR WITH REALIGNING LOCK LINK ASSEMBLY - The invention relates to aircraft landing gear comprising: a leg ( | 11-05-2015 |
| 20150314861 | LANDING GEAR ASSEMBLY AND METHODS - A landing gear assembly having a first part movable relative to a second part, and a spring coupled to the first and second parts via first and second anchor points. A lost motion assembly is provided to enable one of the anchor points to translate along one of the parts. As such, the spring extends less as the first part moves relative to the second part than it would if each anchor point was fixed to a respective part. | 11-05-2015 |
| 20160023750 | AIRCRAFT LANDING GEAR - An aircraft landing gear including: a sprung arm mounted to a main pivot and carrying one or more wheels; leaf springs; a transfer arm attached to each of the leaf springs; and a swinging link with a first end which is pivotally coupled to the sprung arm via a first swinging link pivot and a second end which is pivotally coupled to the transfer arm via a second swinging link pivot. The leaf springs are arranged to provide a resilient biasing force via the transfer arm and the swinging link which opposes rotation of the sprung arm about the main pivot. Each leaf spring only absorbs a portion of the landing loads, so load and stress levels in each individual spring are lower. The swinging link enables the leaf springs to be positioned remotely from the sprung arm, in a suitable position to optimise the use of space and distribute loads efficiently into the airframe. | 01-28-2016 |
| 20160129995 | LINKAGE MECHANISM FOR DRIVING AIRCRAFT LANDING GEAR BAY DOOR - A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors. | 05-12-2016 |
| 20160129996 | APPARATUS AND METHOD FOR CONTROLLING LANDING GEAR - A landing gear system includes landing gear, an uplock that is releasably engageable with the landing gear, an uplock hydraulic actuator operably connected to the uplock, a landing gear hydraulic actuator operatively connected to the landing gear, and a controller operatively connected to the uplock hydraulic actuator and the landing gear hydraulic actuator. In response to receipt of a command to deploy the landing gear, the controller actuates the uplock hydraulic actuator and the landing gear hydraulic actuator to the UP condition and then actuates the uplock hydraulic actuator and the landing gear actuator to the DOWN condition. An alternative embodiment incorporates a piloted check valve upstream of the landing gear hydraulic actuator. The piloted check valve delays operation of the landing gear hydraulic actuator until release of the landing gear by the uplock. | 05-12-2016 |
| 20160137295 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly includes a lock link and a rotary electromechanical actuator which includes motor and gearbox unit arranged to move a pawl into contact with the lock link to break the lock link. A release mechanism is provided to enable the lock link to be made in the event of the motor and gearbox unit jamming. | 05-19-2016 |
| 20160144952 | VERTICALLY RETRACTING SIDE ARTICULATING LANDING GEAR FOR AIRCRAFT - A side articulating main landing gear assembly for an aircraft is disclosed which includes a wheel axle fitting oriented in a horizontal plane when the landing gear is in an extended condition deployed from a landing gear bay of the aircraft, a tire supported on the wheel axle fitting and oriented in a vertical plane when the landing gear is in the extended condition, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a set of articulating links connected to the wheel axle fitting, the shock absorber and the aircraft, and configured to maintain the tire in a vertical plane as the shock absorber strokes between the extended state and the compressed state, a set of tire planing links connected to the wheel axle fitting and the articulating links, and configured to maintain the wheel axle fitting in a horizontal plane as the shock absorber strokes between the extended state and the compressed state, and a drive crank connected to the shock absorber, the tire planing links, the articulating links and the aircraft, for moving the landing gear assembly between the extended condition and an inverted retracted condition stowed in the landing gear bay. | 05-26-2016 |
| 20160194078 | AIRCRAFT SPRING ASSEMBLY | 07-07-2016 |
| 20160375993 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber. | 12-29-2016 |
| 20220135213 | CONTROLLING MOVEMENT OF LANDING GEAR OR LANDING GEAR BAY DOORS - A method of operating a landing gear controller for an aircraft, including: the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method may also include the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals. | 05-05-2022 |
| 20090057485 | BRACE-LOCKING DEVICE FOR AN AIRCRAFT UNDERCARRIAGE - The invention relates to a wind-brace device for an aircraft undercarriage, the device comprising a hinged brace movable between a folded position and a stabilization position for stabilizing the undercarriage in the deployed position, a stabilizer member for stabilizing the brace comprising two hinged-together arms, one of the arms having one end hinged to the brace about a hinge axis, and a spring member for urging the arm of the stabilizer member towards the locked position. The spring member is connected to a lever hinged to the brace, the lever presenting a slot in which there is engaged a finger secured to the arm that is hinged to the brace. | 03-05-2009 |
| 20090101754 | Aircraft nose gear control apparatus - The invention relates to an assembly for controlling the rotational degree of freedom for an aircraft landing gear wheel, which can advantageously be used to prevent damage to the aircraft during taxing. In a general embodiment, an upper connection arm is supported by the descending shaft of the landing gear and a pivoting control arm is affixed to a lower region of the landing gear, and a control lock can be used to connect the connection arm to the control arm in order to restrict the rotation of the wheel to a desired range. | 04-23-2009 |
| 20090218444 | UNDERCARRIAGE SHOCK ABSORBER WITH POSITIVE RETENTION IN A RETRACTED POSITION AND WITH CRASH OVERTRAVEL - The invention relates to a telescopic shock absorber for an aircraft undercarriage, the shock absorber comprising a strut ( | 09-03-2009 |
| 20090242696 | DEVICE FOR LOCKING A MOVABLE COMPONENT OF AN AIRCRAFT - The present invention relates to a device for locking a movable component of an aircraft. The device includes an electronic tag adapted for receiving a polling signal and returning an identification signal. The present invention also involves an on-board system allowing for detection of such locking devices. | 10-01-2009 |
| 20100219290 | ELECTRIC-POWERED TRANSFER CYLINDER FOR LANDING GEAR SYSTEM - A shock strut for an aircraft landing gear having a retract actuator that is moveable in length to deploy or retract the landing gear, that includes a shrink strut and a transfer device. The shrink strut may be compressed in length for stowage in the fuselage. The transfer device may be in closed fluid communication with the strut shrink for transferring and receiving hydraulic fluid to and from the strut shrink. When actuated by an aircraft hydraulic or electric system independent of any motion of the retract actuator, the transfer device may drive hydraulic fluid to the strut shrink thereby compressing or shrinking the shrink strut to a partially compressed length. | 09-02-2010 |
| 20110024557 | LANDING GEAR - In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position. | 02-03-2011 |
| 20110036945 | FRONT AIRCRAFT LANDING GEAR BUILT INTO ELECTRIC CONTROL - A front aircraft landing gear built into an electric control including: a landing gear leg to be pivotably mounted on a structure of the aircraft between a retracted position and an extended position; an actuating cylinder moving the landing gear leg from the retracted position to the extended position; a strut that maintains the landing gear leg in the extended position thereof; an uplock housing that maintains the landing gear leg in the retracted position thereof; an uplock housing an operating mode control and a backup mode for the same housing; and four stress-adding points adding stress to the aircraft structure, namely two points for the pivotal movement of the landing gear leg and two points for the pivotal movement of the strut. | 02-17-2011 |
| 20110163202 | UNLOCKING OF A STABILIZING MEMBER OF A FOLDING STRUT OF AIRCRAFT LANDING GEAR - The invention relates to landing gear mounted on an aircraft in such a way as to be movable between a stowed position and a deployed position, the landing gear incorporating: a barrel mounted in a hinged way on the aircraft; a folding strut with two arms; a stabilizing member to stabilize the strut in an aligned position, having two rods hinged to each other; a telescopic unlocking member having one end coupled to one of the rods, the telescopic member being selectively activatable to break an alignment of the rods. According to the invention, said rod has an aperture in which the end of the telescopic unlocking member engages and which is arranged in such a way that, when the telescopic member is activated, said end interacts with an end of the aperture to move the associated rod toward a non-aligned position which said rod reaches when the telescopic member reaches an internal stop, the aperture allowing any hinged movement of the rod beyond the non-aligned position. | 07-07-2011 |
| 20110278394 | ELECTRICALLY POWERED DOWNLOCK ACTUATION SYSTEM - An electrically-powered downlock actuation system for a landing gear that does not convert rotary motor output into linear motion during the actuation process, but instead uses the rotary motor output to directly drive a locking mechanism coupled to upper and lower landing gear braces. The electrically-powered downlock actuation system may include an electric motor, a gearbox (optional), a clutch (optional) and a fixed link to replace a hydraulically powered downlock actuation system. Further, the electrically-powered downlock actuation system may be controlled with motor control electronics that cooperate with one or more sensors arranged to detect a position of an output shaft. | 11-17-2011 |
| 20120037752 | AIRCRAFT LANDING GEAR UNLOCK ACTUATOR - This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition. | 02-16-2012 |
| 20120056035 | Shrink shock strut locking mechanism for retractable aircraft landing gear - A shrink shock strut assembly for retractable aircraft landing gear is disclosed which includes an elongated strut cylinder, an elongated strut piston coaxially mounted for reciprocal movement within the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft, and a blocking mechanism operatively associated with the strut cylinder and mounted for movement into a blocking position with respect to the strut piston, when the landing gear is retracted within the wheel well, to prevent axial movement of the strut piston into the fully extended condition within the wheel well. | 03-08-2012 |
| 20130299633 | LANDING GEAR FOR AN AIRCRAFT - A landing gear assembly for an aircraft includes a leg having a first rotational mount for rotatably mounting the leg to the aircraft for rotating the leg between retracted and extended positions, a wheel mount provided on the leg, a drag stay having an upper link rotatably mounted to a lower link, and an actuator to move the leg between the retracted and extended positions. The landing gear may be included on a variety of aircraft. | 11-14-2013 |
| 20130306792 | AIRCRAFT GROUND MAINTENANCE TETHER ASSEMBLY - A ground maintenance assembly for in aircraft generally including a support member provided with a longitudinal bore and a rigid post portion, a first inner member provided with a longitudinal bore disposed in and secured in such support member and a second inner member provided with a longitudinal recess adapted to receive a pitot tube of such aircraft. | 11-21-2013 |
| 20100072319 | LANDING GEAR CASING PROVIDED WITH A BOX STRUCTURE - A reduced-volume landing gear casing for the landing gear of an aircraft including a box structure to which the landing gear is fixed and which takes up the toads acting thereon. The box structure can include, in particular, means for receiving the fixing bearings of the landing gear. | 03-25-2010 |
| 20100096499 | SHRINKING SHOCK STRUT SYSTEM FOR RETRACTABLE LANDING GEAR - A shrinking shock strut system for an aircraft landing gear having a retract actuator that is moveable in length to deploy or retract the landing gear, that includes a shrink strut and a transfer device. The shrink strut may be compressed in length for stowage in the fuselage. The transfer device may be in closed fluid communication with the strut shrink for transferring and receiving hydraulic fluid to and from the strut shrink. When actuated by an aircraft hydraulic system independent of any motion of the retract actuator, the transfer device may drive hydraulic fluid to the strut shrink thereby compressing or shrinking the shrink strut to a partially compressed length. | 04-22-2010 |
| 20100116931 | VARIABLE STROKE REAR LANDING GEAR STRUT - Variable-height rear landing gear for an aircraft, the strut ( | 05-13-2010 |
| 20100237189 | LANDING GEAR CASING PROVIDED WITH A BOX STRUCTURE - A reduced-volume landing gear casing for the landing gear of an aircraft including a box structure to which the landing gear is fixed and which takes up the toads acting thereon. The box structure can include, in particular, means for receiving the fixing bearings of the landing gear. | 09-23-2010 |
| 20110198441 | DEVICE FOR RETRACTING AIRCRAFT LANDING GEAR - An aircraft undercarriage comprising a strut ( | 08-18-2011 |
| 20120112001 | LANDING GEAR - An auxiliary mechanism includes a lever unit, a spring unit and a positioning unit. One of the units pivotally connects to the upper portion of a main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position. Another unit pivotally connects at an upper end to the upper portion of the main shock absorber strut and pivotally connects at a lower end to the first unit. A third unit pivotally connects at a lower end to the bogie beam at an auxiliary pivot and connects at an upper end to the lever. The positioning unit assumes either a contracted state or extended state for taxiing, take-off and landing, and assumes the other state for stowing the landing gear after take-off. The spring unit provides spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing. | 05-10-2012 |
| 20130112808 | COMPACT IMPROVED AIRCRAFT LANDING GEAR - A breaker strut of an aircraft landing gear, including means to adjust the length of at least one of its lower and upper portions and/or a space allowing a nesting of the lower and upper portions in the folded position of the strut. A landing gear including such a strut and/or retraction means including two slider-crank mechanisms which are phase shifted by a non-zero angle φ allowing a reduction of the variations of torque C applied to the undercarriage of the gear as it moves between the lowered and raised states of the latter. | 05-09-2013 |
| 20150102163 | SHRINK STRUT LANDING GEAR SYSTEM, METHOD, AND APPARATUS - The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and a shrink valve that are capable of shrinking a landing gear by up to 40% of its available stroke, or more depending on the air spring configuration. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and shrink valve may be part of a strut shrink system. | 04-16-2015 |
