Abstract: An aircraft landing gear brake arrangement wherein a landing gear stub axle and brake pressure plate are integrated. Each of the integrated assemblies is attached to a support fitting which pivots on the truck axle thereby causing the torque links to be unaffected by steering operations.

Abstract: An aircraft nose landing gear installation that utilizes a single piece pin inserted through the gear fittings and into the two piece, fail safe support structure without requiring mechanical retention on the outside of the wheel well.

Abstract: A main landing gear system which employs Ackermann type steering utilizing kingpins and tierods wherein a plurality of paired wheels are employed and wherein each truck axle is adapted for independent steering. Electronic control means along with hydraulic directional valve means are utilized.

Abstract: A main landing gear system which employs Ackermann type steering utilizing kingpins and tierods wherein a plurality of paired wheels are employed and wherein each truck axle is adapted for independent steering. Electronic control means along with hydraulic directional valve means are utilized. A main landing gear having single wheel or king pin steering. Pivot pin tilting is utilized in truck type main landing gear, e.g. where a truck axle is adapted for independent steering or where single wheel or king pin steering is utilized.

Abstract: A main landing gear system which employs Ackermann type steering utilizing kingpins and tierods wherein a plurality of paired wheels are employed and wherein each truck axle is adapted for independent steering. Electronic control means along with hydraulic directional valve means are utilized. A main landing gear having single wheel or king pin steering. Pivot pin tilting is utilized in truck type main landing gear, e.g. where a truck axle is adapted for independent steering or where single wheel or king pin steering is utilized.

Abstract: A low-profile transportation and storage assembly is readily substitutable with a conventional pair of skid landing gear. The low-profile transportation and storage assembly includes a front auxiliary crosstube having low-profile wheels attached to opposing ends of the front auxiliary crosstube, and a rear auxiliary crosstube having low-profile wheels attached to opposing ends of the rear auxiliary crosstube. Both the front auxiliary crosstube and the rear auxiliary crosstube are readily substitutable with the pair of skid landing gear of a conventional helicopter. A pair of front saddle mounts and a pair of rear saddle mounts secure the front crosstube and the back crosstube of the pair of skid landing gear to the helicopter. The pair of front saddle mounts and the pair of rear saddle mounts can be quickly removed from the aft crosstube and the forward crosstube by removal of expandable bushing fittings of the saddle mounts.

Abstract: An easily-attachable supplemental wheel apparatus that allows one person to perform the ground-handling functions necessary to maneuver an aircraft or helicopter having a skid configured landing gear. The apparatus includes an axle extending across the landing skids having a pair of spaced eyelets attached to the axle in such a position that one of the landing skids can easily slide through each eyelet. The apparatus includes a pair of wheels rotatably attached to the axle to allow for easy ground movement along with an attachment for securing the axle to the airframe.

Abstract: Adjacent wheel brake assemblies on aircraft multi-wheel landing gear are interconnected by a ring spring damped brake rod for torque compensation and to provide the added function of vibration damping.

Abstract: An aircraft landing gear wheel stowage structure including a wing rear spar extending laterally across the aircraft; a mid bulkhead extending laterally across the aircraft and displaced rearwardly of the wing rear spar; a pressure bulkhead extending laterally across the aircraft and displaced rearwardly of the mid bulkhead; first and second longitudinal keel structures laterally spaced on each side of a longitudinal axis of the aircraft and traversing the wing rear spar, the mid bulkhead and the pressure bulkhead. The wing rear spar, the mid bulkhead, the first keel structure, and the second keel structure form a first forward outboard wheel well compartment that is outboard of the first keel structure, a second forward outboard wheel well compartment that is outboard of the second keel structure, and a forward central wheel well compartment that is between the first keel structure and the second keel structure.

Abstract: The present invention relates to a protective cover for an airplane nose-wheel fairing. The protective cover prevents a nose-wheel fairing from becoming cracked or scratched as an airplane tow bar is attached or removed from the nose-wheel strut.

Abstract: A steerable landing gear for an aircraft having a six wheel, three axle truck has a steerable axle on either the rear or both forward and rear axles of the truck. A set of wheels driven about a vertical shaft utilizes a single actuator and a walking beam.The present invention relates to multi-wheel landing gear trucks or bogies for large aircraft and particularly to a method and apparatus for steering a set of wheels.

Abstract: An arrangement of sensors on the landing gear of an aircraft measure the weight and position of center of gravity of the aircraft. In order to compensate for errors caused by moment of torsion, one sensor each is arranged on a pair of lugs (53, 54) at two measurement points of an axle (55) or bogie beam lying opposite each other on the outside or of a shock-absorber landing-gear leg. Each of the sensors gives off an electric output variable corresponding to a vertical displacement (sensor deflection) between the lugs of a pair. The lugs (53, 54) are tapered at their roots (61, 62).

Abstract: A wheel protector for protecting a demounted aircraft wheel 54 and its bearing sets 56.1, 56.2 comprises an inboard cover disc 10, and an outboard cover disc 12. An axially outwardly extending part 18 of the inboard cover disc slopes at an angle radially inwardly so as to form a deflecting surface for objects approaching the cover disc in a radial direction. The inboard cover disc has flutings 28 which form between them recesses for accommodating the brake lugs of an aircraft wheel. When in position, the inboard cover disc also protects the heat shields which are located between the brake lugs. A ridge formation 38 serves to locate a pair of wheels against sliding relative to one another when stacked. Foam pads 32.1, 32.2, 33, 40 and 41 are provided where the cover discs contact the wheel or its bearing sets.

Abstract: A space shuttle wheel acceleration system includes a plurality of attachm bands located in the grooves of a tire and extending around the circumference of the tire with collapsible cups attached to the attachment bands located at spaced intervals around the tire that pop open on the downwind portion of a tire revolution to catch the wind and rotate the tire and collapse on the downwind portion of a revolution to reduce drag. The cups include elastic-bands to maintain the cup in a collapsed state when not catching the wind and also include stiffeners to prevent the cups from folding over when catching the wind. A breakaway buckle attaches the ends of each attachment band and automatically fails when the tire touches down to shed the space shuttle wheel acceleration system for smooth runway performance.

Abstract: The locking device of the invention comprises a locking device mounted to pivot relative to a beam and having ends associated with an axle to lock the axle in a first position of the locking device and to release the axle by the locking device pivoting towards a second position, together with a control actuator and a set of two links for controlling the position of the locking device.

Abstract: An arrangement in which at least one sensor is provided on the landing gear of an aircraft for measuring its weight and the position of its center of gravity, and in which a sensor for a measurement of shear is arranged at a measurement point formed by a pair of lugs on an axle or bogie beam. The axle (9) or bogie beam is of constant cross section above the measurement point and symmetrical to a vertical axis which lies centrally between the two lugs of a pair (10, 13 and 14, 15 respectively).

Abstract: The arrangement of a rotary apparatus for aircraft landing gears comprises, disposed in an aircraft wheel axlea modular assembly in one unit comprising a stator and a rotor which is mounted in the stator by two rolling bearings, the stator and the rotor being respectively divided into two stator parts and two rotor parts forming a genetachometer and an electromagnetic coupling of the rotating transformer type for sensors carried by the wheel.

Abstract: To monitor for the formation of a crack in a metal wheel such as that of an aircraft tire and wheel assembly the wheel is provided with an optical fiber arranged to extend no-rectilinearly in a position of the wheel surface selected to be preferential for the development of a crack; preferably the preferential region for crack development is the tire bead seat region and the optical fiber is arranged to extend non-rectilinearly around the circumference of the tire bead seat region thereby to lie interposed between the wheel and tire.

Abstract: A device to induce rotation of aircraft landing wheels is disclosed, using only the force of oncoming air to bring them up to synchronous ground (landing) speed during approach to landing. A complete, independently operating system with its own sensors, microcontroller, motors and control linkages, which does not interface with any of the aircraft's instumentation or systems, continually measures the actual ground speed of the aircraft during final approach, transmitting this flow of data to a microcontroller for continuous translation into required RPM for each tire diameter and monitors the precise RPM of each landing wheel through non-contact photo-tachometers whose outputs are multiplexed into the microcontroller. The system provides continuous control over the RPM of each landing wheel through air intake ducts with servo motor driven inlet vanes gating incoming air to the wheel-mounted impellers.

Abstract: A braking device for a vehicle utilizing a plurality of wheels for motion relative to a surface. The present invention includes a bent axle for supporting at least one of the wheels. The bent axle has a first axle portion being disposed parallel to a y-axis which is perpendicular to an x-axis, the x-axis defining the longitudinal axis of a main structure of the vehicle, the x-axis also defining the direction of vehicle motion. The bent axle includes at least one terminal axle portion angularly disposed from the first axle portion. The first axle portion of the bent axle rotatably engages with the main structure of the vehicle, along an axis parallel to the y-axis. The terminal axle portion of the bent axle rotatably engages with the wheel. Therefore, the wheel rotates in a plane that is not parallel to the direction of vehicle motion.

Abstract: A vertically mounted deflector attached to a landing gear, that prevents debris from being thrown by the tires into the engine of an aircraft. The deflector has two vertically mounted plates that have oblique stepped surfaces facing the tires.

Abstract: A tire (10) suitable for use on an aircraft equippped with cambered landing gear has a symmetrical carcass structure (11) and belt structure (12) but has an asymmetrical tread portion (16). On one side of a central groove (17) the tread portion is devoid of any grooves, but on the other side of the central groove a number of grooves (18, 19) extend circumferentially about the tread.

Abstract: The disclosed invention provides a main landing gear (12, 14, 16, 18) for a high speed (supersonic) aircraft (10) which may be wing-stowed and -mounted in a relatively thin wing (22, 24). The main landing gear (12, 14, 16, 18) is characterized by an inboard gear (12, 14) including a post (58) having a transverse trunnion (52) at a first end (56 or 54) operably mounted on the wing (22, 24). The trunnion (52) is journalled for rotation about an axis for movement of the post (58) between operative and stowed positions. This axis is substantially transverse to the body of the aircraft for forward rotation of the inboard gear (12, 14). A wheel assembly (78, 80) is operably attached at a second end of the post (58). The wheel assembly (78, 80) has a plane of rotation which when stowed in the wing (22, 24) is substantially vertical. In combination with the inboard gear (12, 14) is an outboard gear (16, 18) which includes a post (90) having a skewed trunnion (92) at a first end operably mounted on the wing (22, 24).

Abstract: Landing gear comprising a pivoting strut (1) receiving the rod of a shock absorber (2) which projects downwardly from the strut and is movable in an axial direction (3) relative thereto, a rocking beam (4) mounted to tilt at the bottom end of the shock absorber rod (2) and supporting leading and trailing wheel sets (6), a torque linkage comprising a top branch (7) and a bottom branch (8) which are hinged to each other, the top branch (7) being hinged to the strut (1) and the bottom branch (8) being hinged to the rocking beam, and locking means (9, 15) for limiting a downwards pivot movement of the top branch (7) of the torque linkage while the shock absorber rod (2) is not fully extended.

Abstract: An assembly comprises drive key wearplates mounted in pairs to longitudinal side surfaces of each of a plurality of wheel key bosses and retaining members are fastened transversely across the top of a boss to engage both wearplates of the pair. A heatshield is positioned within the wheel bore between adjacent wheel key bosses and its opposite lateral edges engage respective wearplates in a manner such that it may not move either axially or radially within the bore.

Abstract: Axial motion of the wheel assembly of a flat-spring undercarriage for vertical-lift aircraft is provided to permit proper deflection of the flat spring so as to effectively cushion the touchdown of such an aircraft from a hover.

Abstract: A method and system for reducing stopping distance for an aircraft on a wet runway, which includes blowing away water on a wet landing surface in front of the aircraft tires so that the tires contact a relatively dry surface and simultaneously blowing air on the tires to remove water that may have collected on them. The system includes ducting from the aircraft engine to the landing gear to receive high pressure air bled from the aircraft engine and nozzles connected to the ducting for exhausting high pressure air to the runway in front of the wheels and to the rear portion of the tires. A system of valves in the ducting can be actuated by switches in the cockpit to bleed high pressure air from the engine to the ducting and nozzles during landing of the aircraft.

Abstract: A heavy duty pneumatic radial tire for use in airplanes and the like is disclosed, which comprises a toroidal radial carcass, a belt superimposed about a crown region of the carcass and composed of at least three cord layers, and a bead portion reinforcement consisting of a stiffener composed of a hard rubber stock and a soft rubber stock, a main chafer made from aromatic polyamide fiber cords, and an auxiliary chafer of at least two cord layers covering the outside of said main chafer and at least one cord layer arranged along the inside of the turnup portion as an inner cord layer, and having such a triangular truss structure that cords of at least two cord layers are arranged at inclination angles of 65.degree..about.90.degree. and 35.degree..about.55.degree. with respect to the meridional plane of the tire, respectively, and cords of the remaining cord layer are arranged at an inclination angle of -50.degree..about.70.degree. with respect to the meridional plane.

Abstract: A novel inflation/deflation system for the pneumatic tires of a vehicle, and particularly of an aircraft, is described, which comprises a housing on the vehicle, such as in the form of a fixed axle housing, on which the tire and wheel are mounted for rotation, and defining a cavity coaxial with the axis of rotation of the wheel for housing the valve and related components; a manifold within the housing defines a manifold chamber containing and supporting an axially movable poppet valve; a remotely controllable solenoid is mounted within the axle housing coaxially with the manifold and poppet valve, the plunger of the solenoid being operatively connected to the poppet valve for axial movement of the poppet valve between open and closed positions in response to operation of the solenoid, whereby pressurized air may be selectively supplied from a pneumatic source to the manifold and to the tire through pneumatic lines connected thereto.

Abstract: A nose landing gear supported deflector for preventing ingestion of nose wheel side spray into wing-mounted engines. The deflector extends horizontally with respect to the runway surface and in front of the nose wheels while permitting landing gear and deflector retraction into the nose gear wheel well through the nose gear doorway. A four-point deflector attachment method permits nose wheel and tire changes without requiring removal of the entire deflector assembly.

Abstract: On a shaft (2) which carries a wheel there are mounted: firstly a toothed sector (3) which meshes with a rack (4) on a piston rod (5) which is a part of a double-acting hydraulic actuator (8); and secondly a cam (12) which acts on two rocking levers (13, 14) to apply a bolt (13B, 14B) against a stop face (10A, 10B) of the rod (5) when, by directly swivelling the wheel, the toothed sector (3) is disengaged from the rack (4).

Abstract: A device (10) for venting aircraft tires comprises a fusible plug (42) and a spring-biased piston (30), both plug (42) and piston (30) being positioned within a single bore (B) of the device. The plug (42) is meltable out of the bore when the wheel (12) temperature increases above a specific limit set by the eutectic material which frees the piston (30) to move out of a spring-biased and bore-sealing position within a sealing ring (22) by an overpressure within the tire which overcomes the spring bias. The piston (30) will return to a sealing position when the pressure drops below a value which is insufficient to overcome the spring bias.

Abstract: The tripartite crown reinforcement of this tire is subdivided into a median portion composed of two plies of cables whose extensibility is practically zero, flanked by two lateral portions each composed of three plies of cables whose extensibility is very great. When this tire is not inflated, the edges of its tread resume the falling shape which has been imparted to them in the vulcanization mold.

Abstract: A tire, particularly for aircraft, has a crown reinforcement formed of plies of circumferential cables having a relative extensibility upon rupture of at least 8%, preferably between 10% and 26%, when the vulcanized tire is mounted on its service rim but not yet inflated, and a relative contraction under the effect of the heat at the temperature of vulcanization of at least 1.25%, preferably between 2% and 8%.

Abstract: A nose landing gear supported deflector for preventing ingestion of nose wheel side spray into wing mounted engines. The deflector extends horizontally with respect to the runway surface and in front of the nose wheels while permitting landing gear and deflector retraction into the nose gear wheel well through the nose gear doorway.

Abstract: The present invention relates to a fuse for a wheel equipped with a pneumatic tire.The fuse is constituted in the form of a screw (1) whereof the head (7) is traversed by an evacuation duct (3) receiving a check valve (8) obturating this duct (3); the fuse being characterized by the fact that it comprises a retainer (17), a part of which is embedded in the head, and another part cooperates with the check valve to hold it.

Abstract: An aircraft tire having a liquid deflector extending outwardly from at least one sidewall, a first plurality of grooves in the tread and a second plurality of grooves disposed axially outwardly of the tire relative to the first plurality of grooves for directing water from the first plurality of grooves toward the respective liquid deflectng means. The first plurality of grooves may interconnect to direct water to the second plurality of grooves each of which may extend at an angle of between about 25 and 35 degrees relative to a radial plane of the tire passing through the respective groove.

Abstract: A retainer member is connected to a relief valve attached to a rim of an aircraft tire containing a fluid under pressure. The relief valve has a core made of a fusible material which is responsive to a predetermined temperature that causes the fusible material to change from a solid to a liquid. The pressure of the fluid in the tire causes the fluid to be expelled from the relief valve and thereafter allow fluid to escape from the tire to prevent damaging the tire through a pressure resulting from the predetermined temperature. The retainer member captures the core material to prevent injuring any person on the expulsion of the liquid from the relief valve.

Abstract: A wheel and bearing protector apparatus useful in protecting airplane wheels and bearings from damage or contamination and for preventing loss of bearings during handling prior to mounting on an airplane axle. The apparatus has two wheel and bearing protectors for being mounted on opposite sides of a wheel. Each wheel and bearing protector has an annular central concavity from which a central protrusion extends into the central bore of the bearing in position in a bearing-retaining region of the wheel. An adjacent, substantially radially, annular surface is positioned immediately adjacent to a bearing-retaining cavity in the wheel for holding the bearing snugly in the bearing-retaining cavity to prevent loss or damage. A peripheral rim fits snugly about the outer edge on one side of the wheel. A lock rod apparatus for clamping the two protectors together has a T-rod which is extended through a noncircular slot in the two protectors and through the center bore of the wheel.

Abstract: An aircraft low tire pressure sensing and cockpit display and warning system utilizing axle wheel pair comparator circuitry to provide signals representative of pressures of the axle wheel pair less than a predetermined value, e.g. 15 percent less than a preset value determined by tire requirements or a difference between axle wheel pair pressures greater than a given value, e.g. 25 psi. In the event of tire master warning lamp illumination on the flight deck warning display, further push button interrogation and identification of the axle pair causing the warning can be made by a crew member on the flight deck warning display.

Abstract: An improved aircraft wheel configuration obviates the hazard of wheel failure during take-off and landing situations when tire deflation occurs and the wheel accepts full loading on its flanges. The wheel is configured to provide a differential flange height between the inboard and outboard flanges such that the total load applied to the wheel is distributed equally between the flanges. Alternatively, and/or in addition the flanges are restructured to provide an increased section modulus and the inboard flange is designed to provide a wider contact surface.

Abstract: A tire and wheel assembly is disclosed in which a low profile pneumatic tire having sidewalls which deflect inwardly under load and a wheel having a rim featuring a narrow central channel and extended rim flanges form the combination. The extended rim flanges support the tire sidewalls under static and dynamic loading conditions to produce a combination particularly suited to aircraft applications.

Abstract: An aircraft landing gear assembly includes a strut and tire arranged for load-bearing contact with an underlying surface. A weight transfer shoe interposed between the tire and support surface at touchdown and arranged to pivot to a clear position after touchdown cushions the impact between the tire and the support surface to extend the service life of the tire.

Abstract: Mobile platform units for separate selective engagement with the normal ground contact elements of aircraft undercarriage components (inclusive of wheels and tires, etc.) for distributing the usual highly concentrated loadings thereof over a greater ground contact area. The mobile units have a platform supported above ground level by rolling support components that may comprise a plurality of rotatably mounted rollers, or wheels, and/or endless belt tracks disposed thereabout to collectively provide a total ground contact area which is greater than that of the aircraft ground contact element being supported. Ramp components of resilient construction are hinged to the platform in a manner providing a downturned inwardly disposed leg that is adjacent to the rotatably mounted rollers, etc. when the ramp is in a down position whereby the weight of an aircraft on the resilient ramp moves the downwardly turned leg to an interfering position providing braking action for the units.

Abstract: A ground traction device is disclosed which comprises ground engaging members including first and second parts, the parts being mounted for rotation on a fixed axis and being rotationally offset with respect to each other about the axis. The peripheral surface of each part includes three individual areas arranged in the form of an equilateral triangle with ends of adjacent areas being joined by lobe portions. The ground engaging portions are constructed of molded rubber and provide improved traction in soft ground. The properties of the rubber are selected in relation to the weight of a vehicle to be moved so that the ground engaging member rotates about a true rolling radius over hard ground.

Abstract: This invention relates to aircraft and particularly to the landing gear, and specifically to a device for promptly sanding an unexpectedly slippery runway as the aircraft is in the process of landing thereon so that the aircraft can be controlled and safely stopped after it is on the ground.

Abstract: An auxiliary landing gear for an aircraft including a pair of auxiliary wheels mounted from the wings and including an exterior rim composed of segments connected to a hub by expansible members whereby expansion from a collapsed inoperative disposition to an expanded operative disposition to facilitate landing on rough terrain is achieved.

Abstract: A drag-reducing construction adapted for use with a non-retractable landing gear for aircraft which includes an oleo strut and two torque links. The improvement involves placing an aerodynamically streamlined afterbody behind the cyindrical oleo strut, and the afterbody enveloping the torque links so as to shield them from the airstream during flight. The afterbody may be one-piece or several pieces, and it is rigidly attached to one or both of the torque links; it rotates out of the way when the oleo strut is stroked--such as during landing. In a specific embodiment having a relatively short stroke (e.g., approx. 5 inches), a single afterbody in the form of a hollow shell is rigidly attached to one of the torque links; and the aterbody is relatively tall so that it at least partially envelopes the other torque link.

Abstract: Disclosed is an aircraft landing gear assembly comprising a shock strut and three-wheel truck depending therefrom. The truck comprises a rigid, U-shaped frame including two parallel side beams spaced apart on opposite sides of the strut and interconnected at their forward ends by a downwardly offset end beam in the form of a torque tube. Two coaxial forward wheels are mounted outboard of and on opposite sides of the forward end of the truck. An aft wheel is mounted on an axle rigidly interconnecting the aft ends of the side beams. The lower end of the shock strut is disposed between the forward ends of the side beams and includes two rearwardly diverging arms, the divergent ends of which are connected to the side beams in such a manner that the truck is rotatable about an axis passing through the connection points between the arms and the side beams.