Abstract: Apparatus for gripping, raising, orienting and transporting helicopters (2) in specially prepared areas or zones in particular on decks (1a) of ships (1), comprising a cross-piece (6) movable in a direction parallel to the longitudinal axis (X--X) of the ship in engagement with said rail (4), wherein the transverse arm (6b) of said cross-piece (6) has joined to it a substantially L-shaped frame (7; 107) and smaller arm (7a) movable relative to the cross-piece (6) in a transverse direction with respect to the longitudinal axis (X--X) itself through the action of associated actuating means (7c), the free end of said longitudinal arm (7a) of the frame (7) having rotationally attached to it a transverse member (9; 109) carrying at its opposite ends the devices (10) for gripping the main wheels of the helicopter (2).

Abstract: An airplane steering system which permits 180 degree turns with minimum tire scrub. The system involves steering of both the nose landing gear and the front and rear wheels of both main landing gear each consisting of three inline wheels; thus, the center of turn is placed between the main gears and allows the airplane to make 180 "pirouette" turns.

Abstract: The acceptability of the steering angle between the nose wheel of an aircraft and the longitudinal axis of the aircraft during transportation of the aircraft on the ground using a wheeled vehicle (with or without a tow bar) is provided. The wheeled vehicle has a source of collimated radiation (such as a laser beam emitting unit, or an LED or other light source with a lens and/or aperture system) which directs a beam on a surface of the aircraft having at least two significantly different collimated radiation reflecting areas (e.g. a light material arc bounded by dark material marks). In response to radiation from the collimated beam, or lack thereof, reflected from the surface of the aircraft back to a receiver on the wheeled vehicle, it can be determined if the nose wheel steering angle is within an acceptable range (typically no more than between about 60.degree.-80.degree., which would damage the nose wheel).

Abstract: A device for gripping, guiding and moving wheeled-type helicopters, particularly on board ships, platforms and the like, comprising a pair of crossmembers (6) located parallel to longitudinal axis (X--X) of the vessel and capable of moving transversally to such axis, in engagement with corresponding means of transverse guidance (2) integral with the ship's deck (3), each under the action of appropriate means of operation (7,8a, 8'a), independent of one another, and of further means of movement (12, 13) parallel to the longitudinal axis of the vessel, in engagement with corresponding longitudinal means of guidance (1), there being also provided a gripping and lifting arrangement (10,100) integral with each crossmember (6) and capable of moving in relation to the latter in order to grip, lift and guide the helicopter after landing, irrespective of its relative position with respect to deck (3) and its orientation with respect to longitudinal axis (X--X) of the vessel, and to position it in alignment with at lea

Abstract: An aircraft ground transporter is adapted particularly for the transport of wheelless, skid supported aircraft (e.g., helicopters) on the ground. The transporter is self propelled and includes seating for an operator thereon. The device is hydraulically powered and operated, with an engine providing power for a hydraulic pump, which in turn provides all lifting, steering, and mobility functions. The configuration of the vehicle includes a generally H-shaped frame, with the forward ends of the two arms of the H each including a steerable wheel or wheels thereon. Each arm includes a lifting bar thereon, which may be raised to lift an aircraft by the cross tubes of the landing skids. The opposite, rearward end of the vehicle includes the engine and most of the hydraulic apparatus, and seating and controls for the operator. Thus, the operator is always facing toward an aircraft being handled by the transporter, and may easily observe the transporter and aircraft being transported thereby.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: Landing gear axle steering for an aircraft having a six wheel three axle truck. A set of wheels driven about a vertical shaft utilizes a single actuator alone without a walking beam.

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: The invention is directed to landing gears for model airplanes. Both the nosegear and the main landing gear are constructed by using an in-line structure having an axial coil spring which is connected to the airplane structure by a shank. The shank is configured to be in-line and generally coaxial with axial coil spring.

Abstract: An aircraft extending along a longitudinal aircraft axis and having a nose wheel pivotal about an upright wheel axis can be maneuvered by a tractor extending along a longitudinal tractor axis and adapted to engage the nose wheel of the aircraft. The tractor and aircraft axes can extend at an angle to each other that should not exceed a predetermined maximum turnout angle. A turnout protection system has structure on the aircraft that is directed generally perpendicular of the aircraft axis and that is only directed toward the tractor when the aircraft and tractor axes extend generally at the maximum turnout angle relative to each other. At least one electronic sensor on the tractor directed toward the aircraft detects the structure when the aircraft and tractor axes extend generally at the maximum turnout angle relative to each other. A controller on the tractor takes action, e.g.

Abstract: A steering method and system for large aircraft wherein during low speed taxi the main landing gear wheels are steered and the nose gear is free to castor. During high speed taxi such as during take off and landing, the main gear steering is locked out while the nose gear is steered.

Abstract: A flying vehicle has wheels for highways, and a body and an engine. The body, engine and load define a center of mass (CG). Shrouded fans are located about the CG so as to produce, in conjunction with air jet redirection apparatus, the torques required to assume various attitudes. In one embodiment, an upper shrouded fan, with a diameter no greater than eight feet, produces an air jet, centered above the CG, for lifting the body. A second shrouded fan, smaller than the first, produces an air jet for lift, centered below the center of mass, on the longitudinal axis of the vehicle, forward of the CG. Third and fourth paired shrouded fans produce air jets for lift, centered below the CG, on either side of the longitudinal axis of the vehicle, toward the rear of the body. The paired second and third fans have equal diameters, no greater than half of the diameter of the upper fan, to keep the total width eight feet.

Abstract: A nose landing gear assembly on an airplane with a front fuselage section having a wheel bay defined therein and a pair of laterally spaced side compartments defined therein on each side of the wheel bay by respective laterally spaced side walls. A nose landing gear is mounted on the fuselage section for pivotal lifting and lowering movement into and out of the wheel bay. The nose landing gear assembly includes an actuator disposed in one of the side compartments for lifting the nose landing gear into and lowering the nose landing gear out of the wheel bay, and a steering device disposed in the other of the side compartments for steering the nose landing gear while the airplane is taxiing. Since the actuator and the steering device are concealed in the respective side compartments, they are protected from foreign-object damage. The nose landing gear assembly allows the airplane cabin to have increased space because the actuator and the steering device are positioned laterally of the nose landing gear.

Abstract: Portable RCS versus azimuth measurement apparatus for an aircraft to be tested has a dolly attached to the aircraft at a location on a supporting surface. A nose wheel adapter mounted on the dolly temporarily replaces the nose wheel of the aircraft with a spare nose wheel. An electric motor on the dolly coupled to the spare nose wheel rotates the spare nose wheel. A beam structure has a first end removably affixable to the dolly and a spaced opposite second end extending under the axis of rotation of the aircraft and between the main landing wheels. A synchronizing gearbox, mounted on the second end of the beam structure at the axis of rotation of the aircraft, has an output shaft and senses rotation of the aircraft about the axis of rotation, sensed rotation of the aircraft being indicated by rotation of the output shaft. Rotation of the output shaft of the gearbox is restrained relative to the surface by an anchor.

Abstract: A utility vehicle is shown for towing and servicing aircraft. The vehicle includes a frame and at least one tow hitch attached to the frame for towing an aircraft. An internal combustion engine is mounted on the frame within an enclosed interior and is connected by a power train to a pair of drive wheels for powering the vehicle. A heat recovery system within the enclosed interior receives warmed cooling air from the engine and products of combustion from the engine exhaust to route heated air to a flexible duct. The flexible duct is connected to an aircraft engine to be serviced in order to preheat the engine. The drive train of the vehicle includes a hydrostatic transmission and a differential gear box connected to the drive wheel axles. The hydrostatic transmission includes a self-centering servo mechanism for controlling the rate of speed change of the vehicle to prevent jerking an aircraft.

Abstract: The strut of the leg has a lateral extension on its outside above the rotary sleeve, the cylinder of a steering actuator is suspended from the lateral extension by means of a universal joint, the end of the rod off said actuator is hinged to a lateral steering lug of the rotary sleeve. This flexible disposition puts fewer constraints on implementation of the scissor linkage, and it improves guidance of the rotary sleeve.

Abstract: A towing vehicle for maneuvering airplanes without draw tongue, has a chassis (5), which exhibits a fork-shaped receiver space between the wheels of one wheel axle, in which a gripping and retracting device (28, 68) is attached that can be retracted and extended and works together with a lifting device, by means of which the nose wheel (24) of the airplane can be grasped and pulled onto a scoop (14) that can be raised and lowered relative to the chassis. In it, only a single scoop (14) is present to support the nose wheel (24) in the area of the nose wheel load line of application to prevent clamping and deformation forces on the nose wheel (24) during the retraction procedure or during raising. The scoop can be tipped around a horizontal axle attached to the chassis and its tipped position relative to the chassis can be adjusted by control.

Abstract: An aircraft landing locking pin (12) automatically repositions from an engage position, wherein a rotating portion (15) of the landing gear is prevented from rotating, to a released position, wherein the rotating portion if free to rotate, in response to excessive side loading on the landing gear. The locking pin comprises a spring loaded actuator (32,34,60) which urges a roller (19) of a lock pin assembly (20) in contact with a bushing (22). In response to a side loading on the landing gear in excess of a predetermined loading, the locking pin is automatically released wherein the roller is expelled from the bushing. The threshold loading is determined as a function of the spring force applied to the lock pin assembly via the actuator linkage. The locking pin automatically reengages when the lock pin assembly is aligned with the bushing.

Abstract: A tractor tows an aircraft with a landing gear having a nose wheel in accordance with a method for coupling the landing gear to the tractor. The tractor and the nose wheel are moved relative to each other on an apron until they contact each other. A shovel member of the tractor is coupled to the chassis of the tractor and movable within a recess of the chassis to be lowered to receive the nose wheel and raised to lift the nose wheel. The shovel member is slidable relative to the chassis and underneath the nose wheel so that it is located entirely between the nose wheel and the apron for receiving and at least partially supporting the nose wheel. The nose wheel is then immovably coupled to the shovel member. The shovel member is then raised to lift the nose wheel above the apron for towing the aircraft with the tractor.

Abstract: An aircraft towing vehicle including a chassis formed with a recess receiving a towing device for securing a nose wheel of an aircraft and including a transversely tiltable bearing frame, a vertically displaceable and longitudinally swingable lifting cradle provided with a pair of telescopic traction arms having respective gripping devices on respective rearward ends, the arms being longitudinally displaceable and adapted to swing about respective transverse axes, bringing thereby the gripping devices upwardly to engage the circumference of the nose wheel above an axle thereof.

Abstract: An aircraft tug assembly is provided for moving an aircraft on the ground. The tug assembly includes a self-propelled chassis responsive to operator control. A cradle assembly is pivotally attached to a front portion of the chassis. The cradle assembly has an adjustable nosewheel receiving apparatus comprising two lateral arms adjustably engaged with a rear gate to define a nosewheel receiving corral therebetween, with the corral sizable to accommodate varying sized aircraft nosewheels. The chassis has a winch, or alternatively a telescoping arm, for pulling an aircraft nosewheel onto the cradle assembly and into the corral. An optional front gate may be used to enclose the nosewheel within the corral. Hydraulic actuators lift the cradle assembly with the nosewheel thereon so the tug assembly may move the aircraft without starting the aircraft engine.

Abstract: An aircraft tug assembly is provided for moving an aircraft on the ground. The tug assembly includes a self-propelled chassis responsive to operator control. A cradle assembly is pivotally attached to a front portion of the chassis. The cradle assembly has an adjustable nosewheel receiving apparatus comprising two lateral arms adjustably engaged with a rear gate to define a nosewheel receiving corral therebetween, with the corral sizable to accommodate varying sized aircraft nosewheels. The chassis has a winch for pulling an aircraft nosewheel onto the cradle assembly and into the corral. An optional front gate may be used to enclose the nosewheel within the corral. Hydraulic actuators lift the cradle assembly with the nosewheel thereon so the tug assembly may move the aircraft without starting the aircraft engine.

Abstract: A vehicle with its own traveling gear for towing an aircraft without draw tongue, has a U-shaped chassis frame recess that is open in the forward direction with a clamping and lifting device arranged therein for the nose wheels of an aircraft. The clamping and lifting device, which is oscillatingly suspended on the chassis frame 1, includes a pivoting and lifting ramp 8, as well as two parallel telescoping arms 10 arranged rigidly on the pivoting and lifting ramp 8, with telescoping cylinders 11 and with gripping arms 14, which can be pivoted in and whose nose wheel contact surfaces 18 are rigidly attached to the gripping arms 14, and of telescopingly adjustable holddown devices 12, 13, which are hinged to the support 7.FIG. 3 shows the clamping and lifting devices with the nose wheels 17 lifted.

Abstract: A six wheel, three axle, bogie type main landing gear for an airplane is retractable as a unit and is provided with a rearward set of wheels or a forward set of wheels that is steerable with respect to the non-rotatable bogie beam. The set of wheels turns in response to steering of the nose wheel past a given angle. A wheel assembly is mounted for rotation with respect to a vertical shaft supported by a fork extending longitudinally of the beam, and a pair of hydraulic cylinders turns the wheel axles with respect to the beam.

Abstract: A launching device carrier (14) has fuselage supports (24, 44) and ground engaging wheels (18). A pair of outrigger assemblies (84, 122) are spaced laterally from the carrier (14) on opposite sides of the carrier (14). Each assembly includes a ground-engaging wheel truck (122) and a wing support (84) spaced laterally outwardly from the truck (122). The assemblies (84, 122) are connected to the carrier (14) by connector structures that permit relative vertical movement between the assemblies (84, 122) and the carrier (14). The carrier wheels (18) react centerline vertical loads to the ground. The outrigger wheels (126) independently react wing weight vertical loads to the ground. The connector structure preferably includes a main boom (64,64') hingedly connected to the carrier (14), and an outer boom (82, 132) pivotally attached to the outer end of the main boom (64, 64'). The outer end boom (82, 132) pivots to move the wing support (84) between an upper support position and a lower release position.

Abstract: An aircraft tug assembly is provided for moving an aircraft on the ground. The tug assembly includes a self-propelled chassis responsive to operator control. A cradle assembly is pivotally attached to a front portion of the chassis. The cradle assembly has an adjustable nosewheel receiving apparatus comprising two lateral arms adjustably engaged with a rear gate to define a nosewheel receiving corral therebetween, with the corral sizable to accommodate varying sized aircraft nosewheels. The chassis has a winch for pulling an aircraft nosewheel onto the cradle assembly and into the corral. An optional front gate may be used to enclosed the nosewheel within the corral. Hydraulic actuators lift the cradle assembly with the nosewheel thereon so the tug assembly may move the aircraft without starting the aircraft engine.

Abstract: A vehicle for conveying aircraft is disclosed which includes a carriage system capable of lifting, supporting and conveying an airplane. The system has alternately deployable primary and auxiliary sets of wheels mounted from the carriage chassis. The wheels of the auxiliary set are vertically displaceable relative to the primary set so that the carriage chassis can be alternatively supported by either. A mechanized steering system is provided for the primary set of wheels. A lifting system is provided to lift an airplane of interest between self-supported and carriage-supported dispositions, as required. An engine-driven hydraulic system is provided to operate the vehicle and power the wheel sets, lift mechanism and steering of the primary wheels.

Abstract: A tow connector engageable with a nose strut of an aircraft for towing the aircraft. The connector has an arm and a base extending therefrom with spaced fingers extending from the base parallel to the arm. Each finger has an upper portion which houses a slideable shaft and a notch located at the forward end of each finger for engaging lateral studs on a nose strut of an aircraft. The shafts are slideable between the notches in the fingers and a pair of stops mounted on the base. The tow connector includes an adjustment mechanism having a pin with a head biased upwardly by a spring to protrude above the top surface of each finger adjacent to the rear end of each shaft to maintain the shafts in the forward lock position. A moveable handle is connected to a compression plate to move the heads downwardly to provide clearance to move the shafts.

Abstract: The object of the invention is a transfer device that will grip double wheels of very different size, which is intended to move an aircraft (1) or other device equipped with double wheels on a base, which transfer device includes a fork-shaped frame and pairs of rollers (3, 4) attached to both forks (2), compression devices for them and devices to rotate the rollers, both pairs of which rollers (3, 4) being placed from the side in front and behind the wheel (6) of the device (1) to be moved. According to the invention the forks (2) are attached to the frame part (7) that connects them by means of parallelogram arms (5), which are adapted to provide the rollers (3, 4) with the lateral movement required when being placed around double wheels (6) and which transfer device includes operating devices (18) to turn the parallelogram arms.

Abstract: A towing vehicle for towing a large aircraft that lifts, supports and moves the nose wheel of and consequently the aircraft itself, is provided. The towing vehicle has a frame which internally receives the aircraft's nose wheels. Forward and rear arcuate shaped nose wheel engaging members contact a substantial portion of the front and rear circumferential surfaces of the nose wheels. The forward nose wheel engaging members are pivotally attached to the front of the frame. The rear nose wheel engaging members are connected through hydraulic rams to the rear of the frame. When the hydraulic rams are extended, the nose wheels are lifted and rotated around the pivotal connection of the forward nose wheel engaging members and the frame thereby lifting and supporting the nose wheels off the ground. Movement of the towing vehicle then also moves the aircraft whose nose wheels are supported.

Abstract: The present invention pertains to a gear drive assembly that will allow components that are not capable of continuous rotation to be coupled to a component that is capable of continuous rotation. The drive gear assembly includes a drive gear component which is actually comprised of two gear sectors, one used to mesh and drive a driven gear directly and the other used to drive the driven gear in a reverse direction through a reversing cluster gear arrangement. The drive gear sectors are arranged so that when one sector is coupled and driving the driven gear, the other sector is decoupled, and vice-versa. Gear jamming is prevented by properly timing the coupling and decoupling of the drive gear sectors with the driven gear and the reversing cluster gear arrangement. In addition, where gear teeth pairs clash during coupling, provision is made to allow one gear tooth of the clashing pair to deflect and allow passage of the other gear tooth to the proper position.

Abstract: A recreational vehicle combines a flying vehicle and a motorized surface vehicle, such as a boat, car, or truck or snowmobile. The flying vehicle is tethered to the surface vehicle by four rods, each of which is rotatably connected to the flying vehicle and surface vehicle, so that the angle of attack of the flying vehicle relative to the surface vehicle remains constant or decreases, depending only on altitude. On/off, throttling, and steering of the motorized surface vehicle are controlled by the pilot of the flying vehicle. The flaps of the flying vehicle are automatically lowered for landing to increase drag and lower the stall speed and raised following take-off to reduce drag. Ailerons are automatically controlled to roll the flying vehicle during turns.

Abstract: A system for automatic transportation of an aircraft on the ground in the region of a parking place comprises in this region a carriage which is co-nectible to the nose wheel of the aircraft and is, by means of capstans, drivable back and forth along guide means in the ground.

Abstract: The aircraft tractor arrangement maintains a uniform degree of reliability with which the nose wheel landing gear, which is standing on a lifting platform that is arranged on the front part and extends into a recess (26), is held down on the surface of the lifting platform which supports the nose wheel landing gear at different nose wheel diameters.Each telescoping rod (30) is hinged (40, 44, 46) to the front part (10.1) directly in the front. A connecting hydraulic cylinder (42) is provided in the rear. The hydraulic cylinder (46) for longitudinal adjustment, and also the hydraulic cylinder (36) for moving the holder (34) on the fixed part (30.1) of the telescoping rod (30) associated with it are arranged ridgedly.This arrangement allows an adjustability in height of the two rear tow arms and at the same time of the front holders, which can come into contact with the two desired zones of the wheel circumference, regardless of the nose wheel diameter.

Abstract: A vehicle chassis is supported on front and rear wheels for road and runway engagement. A propeller assembly is disposed between the front and rear wheels and faces the rear. Wing assemblies on opposite sides of the chassis are foldable along the sides of the chassis to form side panels for the road form of the vehicle. A tail assembly on the chassis is shiftable forwardly and rearwardly and has a pair of vertical stabilizers connected together at the top by a horizontal laterally extending stabilizer. A pressure regulated retractable stabilizing wheel is provided between the front and rear wheels and is arranged to engage a runway and provide stabilizing functions for take off and landing.

Abstract: The present invention pertains to an aircraft tractor without tow-bar. The arrangement avoids relative movement between the nose wheel of the aircraft and the tractor lifting platform by making the lifting platform (24) rotatable around a longitudinal axis (30) of the chassis, which axis is horizontal when the chassis is extended, and by making displaceable the transverse tow arms (38) and/or the holders (42) at right angles to this longitudinal axis (30). The tires of an oblique nose wheel landing gear of an aircraft being towed in a curve are handled very gently, because the tractor parts (24, 38, and 42) that are in contact with the nose wheel landing gear are able to follow the movements of the nose wheel landing gear and to adjust to its instantaneous position.

Abstract: In conventional towing vehicles the front wheels of the aircraft are pulled or pushed onto a lifting shovel or the like and the aircraft or the towing vehicle must be maintained in motion so that the front wheel assembly can be acted upon by undesirable forces.In order to ensure gentle and reliable retention and lifting of the front wheel assembly from a state of standstill as well as equally reliable and gentle towing away of the aircraft, there are provided for each front wheel four gripper arms which engage the periphery of the front wheel. The rear gripper arms are pivotable inwardly in a vertical plane. The idle positions of all gripper arms are selected by a computer which is programmed in dependency on the respective aircraft type.

Abstract: The steering apparatus of the invention comprises a body (4) containing a crank (8) with actuators (12) associated with the crank and free to pivot about respective pivot axes (14). The actuators co-operate with distribution members including feed circuits and return circuits carried by the body and opening out facing at least one actuator face (16) extending perpendicularly to the pivot axis (14) of the actuator, the face including at least one control orifice (17).

Abstract: An AGHV comprising a chassis 10 having front 11, 12 and rear 15, 16 wheels thereon, a support platform 25, 26 being movably mounted on the chassis 10 and jib 30 being provided on the chassis 10 for loading the nosewheels of an aircraft onto the platform 25, 26; said platform 25, 26 being longitudinally movable between the first position wherein said nose wheels can be loaded thereon so as to be supported by the platform 25, 26 on the chassis 10 and a second position which is clear of said first position.

Abstract: The apparatus disclosed comprises a universal tow and coupling bar for connecting automatically to an aircraft landing nose gear and towing the aircraft during ground transport. The aircraft engaging end of the tow bar has directional adjustment and is hydraulically controlled in three coordinates. The end of the tow bar opposite to the aircraft engaging end is semi permanently connected to the aircraft towing vehicle. The aircraft engaging end of the tow bar contains an automatic hydraulically controlled locking assembly arranged to engage and lock with a mating locking assembly permanently fixed to the aircraft nose wheel structure. In addition to the aforementioned features of the universal tow bar are means for controlling the length of the tow bar, interupting the aircraft's hydraulic steering system, and connecting to the aircraft's telephone system.

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: An aircraft ground handling tractor (1) includes a manoeuverable boom (6) mounted on it. The free end of the manoeuverable boom (6) includes a connector (18) capable of being connected to an aircraft nosewheel assembly so that the tractor (1) can be connected to the nosewheel assembly through the boom (6) to enable it to pull or push the aircraft. The manoeuverable boom (6) is retractable completely within the outer limits of the tractor (1) so that, when the tractor (1) is not pulling an aircraft the manoeuverable boom (6) is wholly retracted so that it is protected from damage. Preferably the tractor (1) includes a longitudinal tunnel (7), and the manoeuverable boom (6) is received within this tunnel (7) in its retracted position. Preferably the movement functions of the boom (6) are all powered and all controlled from a driving cab (2) of the ground handling tractor (1), and the tractor (1) includes a separate, hand held control unit which enables them to be controlled remotely from the driving cab.

Abstract: A novel approach is employed for attaching an aircraft tug to the nosewheel tire assembly of an airplane. A tire capturing mechanism comprising a pivoting capture arm and a transversally adjustable crossbar opens to allow positioning of the capturing mechanism around and beneath the portion of said tire that is not in contact with the runway surface. After tire capture is accomplished, said capturing mechanism is elevated off the runway surface by a lifting mechanism, so that the entire portion of the weight of said airplane supported by said tire is borne by said aircraft tug. A universal tire clamping mechanism is employed to secure said tire firmly to said capturing mechanism.

Abstract: A device for steering the wheels fitted to the bottom end of the leg (1) of the nose landing gear of an aircraft, the wheels being steered about the axis of the leg, the leg (1) comprising a strut (2) hinged to the structure of the aircraft, a tube (4) mounted to rotate inside the strut (2) and projecting outside the strut, a rod (5) slidably mounted inside the tube (4) and carrying the wheels at its free end, and a scissor linkage (6) for constraining the tube (4) and the rod (5) to rotate together.

Abstract: A braking system for an aircraft towing vehicle which supports the nose wheel of an aircraft in a raised position and firmly clamps it to the vehicle. The braking force generated by the front wheels of the towing vehicle is greater by about 2:1 to 8:1 than the braking force at the rear wheels. The braking system has two hydraulic circuits employing identical braking cylinders at all four wheels of the vehicle. The number of cylinders per wheel are varied and different effective lever arms are used to generate like braking forces at each side of the vehicle, and the relatively greater braking force at the front wheels, even if one of the hydraulic circuits fails. The system limits the braking force at the front and rear wheels to maximum values to prevent excessive forces from damaging the nose gear of relatively smaller aircraft.

Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.

Abstract: A parking trolley for light aircraft (1) with a couple of landing wheels (3,3), and a nose or rear supporting wheel (3'), comprising a mainly T-shaped frame (2) with adjustable supporting surfaces (4, 5,6) for the landing wheels (3,3) and the supporting wheel (3'). The T-frame is supported by wheels (12,13,14) at the free ends of the frame, the wheels being adjustable and lockable in a position with the turning axes of the wheels in parallel for transport of the parking trolley and light aircraft on the trolley by the aid of a traction vehicle. Furthermore, wheels (12,13,14) are adjustable to positions with their turning axes directed as radii of a turning point (9), alternatively a turning point (10) at a distance from turning point (9), which is connected with an anchoring means (11) in the ground, via a turning bolt.

Abstract: A towbar and come-along, especially for light aircraft, wherein a tongue is releasably attached to the axle of a nose wheel and carries a ratchet engageable with the periphery of the tire which is torqued by manipulation of a radially extended handle, acting as a second class lever which is adjustable and reversible and with anti-roll functions.

Abstract: An aircraft carrier (1) is provided that can be moved by the thrust of the aircraft (2) positioned on the carrier (1). The carrier (1) comprises a steering system that is powered by the nosewheel (9) of the aircraft (2).

Abstract: A servo-control system is provided for the steerable front wheels of a vehicle, particularly the steerable nose gear of an aircraft, at least the lower part of which having at least one wheel may rotate about its longitudinal axis. This system includes a high pass filter device whose input receives a signal containing at least a part representative of the oscillations about its longitudinal axis to which said lower part of said nose gear is subjected and whose output is connected to a device for subtracting the output signal of said high pass filter from said difference between said order and said signal representative of the real orientation, and the pass bank of said high pass filter covers the natural oscillation frequency of said lower part of the gear about its longitudinal axis.