Abstract: An apparatus for facilitating voice communication between persons outside an aircraft and persons inside an aircraft, is disclosed, comprising: an external control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons in said aircraft; receiving means for receiving voice information from persons in said aircraft; and amplifying means for enabling said voice information to be heard; and an in-aircraft control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons external to said aircraft; receiving means for receiving voice information from persons external to said aircraft; and amplifying means for enabling said voice information to be heard.

Abstract: A device for controlling an aircraft during non-flying operations has a retractable tiller that extends with the nose landing gear of the aircraft. Ground crew use the control device to maneuver the aircraft for various ground-based operations. The tiller provides left and right directional input to the steering of the nose wheel. The tiller also provides throttle and brake controls, such as a twist-grip handle on the tiller. The throttle and brake controls are spring-loaded to an engine idle and braked position. Separate brakes also may be provided for additional braking control. The control device also includes various auxiliary controls for additional operations such as wing fold, tail hook extension and retraction, launch bar extension and retraction, etc. Other functions including engine start, engine shutdown, a vehicle system built in test and other functions and tests also may be provided on the control device.

Abstract: An equipment-carrying crawler (20) includes a rolling track (44) and a structural support (70). The structural support (70) supports equipment (16). Lifting magnets (72) are coupled to the rolling track (44) and to the structural support (70). The lifting magnets (72) are configured to oppose each other, lift the structural support (70), and aid in the translation of the rolling track (44).

Abstract: An apparatus for controlling the movement of an aircraft having a self-propelled nosewheel, on the ground, is disclosed. The apparatus comprises a control arm; a control unit; means for transmitting information to said self-propelled nosewheel; means for receiving information at said self-propelled nosewheel; and means for controlling at least one of the speed and direction of said nosewheel; whereby airport ground staff can intuitively control the movements of said aircraft by holding said arm and moving it in the direction of required movement of said aircraft.

Abstract: A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).

Abstract: A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction means for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.

Abstract: An auxiliary on board power system for an aircraft provides the capability of taxiing the aircraft on the ground without using the main aircraft engine(s). The power system includes a small driver mounted on the aircraft. In one embodiment of the invention, the driver may be mounted at any desirable location on the aircraft and is designed to provide sufficient thrust to taxi the aircraft. Such a suitable system may be provided as original equipment to an aircraft or retrofitted to existing aircraft. In another embodiment of the invention, the driver includes a speed reducer with an output shaft to drive the wheels of one of the landing gear assemblies to provide power to taxi the aircraft. In a further embodiment of the invention, the auxiliary on board power system, in addition to the taxiing function, may be incorporated with an alternator to provide electrical power, an environmental control unit, and an emergency power units as desired.

Abstract: The invention relates to a method for managing a steering control of an aircraft landing gear provided with at least one wheel steerable by the steering control, comprising the following steps: monitoring one or several taxi parameter(s) (51, 54, 64, 59, 61) of the aircraft to determine whether said aircraft enters a towing situation, setting the steering control in a free steering mode of the steerable wheel, if the aircraft enters the towing situation; activating the steering control so that the steerable wheel has an angular controlled steering by the steering control if the aircraft leaves said towing situation.

Abstract: The invention relates to a system architecture for managing aircraft landing gear and suitable for extending/retracting retractable undercarriages, steering steerable wheels, and braking braked wheels. According to the invention, the architecture comprises a communications network having connected thereto extension/retraction actuators, steering actuators, and braking actuators, together with one or more control units adapted to control all of the actuators connected thereto, the communications network having transmission characteristics that are adapted to enabling the control unit(s) to implement antilock servo-control for controlling the braking actuators.

Abstract: A method for reducing the turnaround time of an aircraft having at least one self-propelled undercarriage wheel comprising the step of: moving the aircraft to a required location using at least one self-propelled undercarriage wheel; wherein thrust equipment, (e.g. turbines) are turned on only when needed for takeoff or prior to landing, and are turned off until takeoff or after landing; whereby departing equipment, arriving equipment, and turnaround equipment are not at risk from operating thrust equipment, (e.g. turbines). An apparatus for reducing the turnaround time of an aircraft is disclosed comprising a control unit for facilitating voice communication between a pilot and ground staff.

Abstract: A jack apparatus for lifting an aircraft having landing gear including snow skis comprising a generally rectangular base having a first end, a second end opposite the first end, and at least two lateral members extending between the ends. The base is sized and shaped for positioning between the snow skis. The apparatus further includes a lift having a base end pivotally connected to the base adjacent its second end and a lifting end opposite the base end. The apparatus also includes a slide slidably connected to the base and a brace having an upper pivot end pivotally connected to the lift and a lower pivot end pivotally connected to the slide. In addition, the apparatus includes an actuator connected between the base and the slide for sliding the slide along the base.

Abstract: A draw spring linkage includes a hollow rod formed with a shoulder structure at the first end of the rod and with a slot that extends longitudinally of the rod and is located between the shoulder structure and the second end of the hollow rod. A tongue member includes an attachment portion and a stem that projects from the attachment portion. The stem fits slidingly in the interior space of the hollow rod and is formed with a slot that is aligned with the slot in the hollow rod. A key extends through the slot in the tongue member and the slot in the hollow rod and projects laterally from the hollow rod. A hollow cylindrical spring is threaded by the hollow rod. The first end of the spring engages the shoulder structure, the second end of the spring engages the key, and the spring is held under compression between the shoulder structure and the key.

Abstract: A snow ski tow bar adapts a prior art aircraft tow bar for attachment to a landing gear of an aircraft to which a snow ski has been attached. The snow ski tow bar modifies an existing tow bar with a second set of connectors that adapt the snow ski tow bar for connection to the landing gear of the aircraft having the snow ski. In addition, the existing wheels of the prior art tow bar are replaced with a second set of wheels that are spaced outwardly from the original wheels. This positions the second set of wheels on the snow ski tow bar where they are extended outside the lateral width of the snow ski on the landing gear. The second set of wheels support the tow bar in a position above the snow ski with the second set of tow bar connectors connected to the aircraft landing gear.

Abstract: A hydraulic system for steering an aircraft while taxiing selectively applies pressurized fluid to different ports of a hydraulic motor to turn a landing gear wheel either left or right. Shimmy of the landing gear attached to the wheel is dampened by a device that is coupled across the hydraulic lines that are connected to the motor. That device has a piston in a bore with one hydraulic line connected via an orifice to a first chamber on one side of the piston and the other hydraulic line connected via a different orifice to a second chamber on the other side of the piston. The piston stroke is limited to control the effective oscillation damping amplitude. The shimmy produces an oscillating pressure differential in the two hydraulic lines which is dampened by the device.

Abstract: A method and system is utilized to produce an output corresponding to a safety level, particularly in relation to an activity on a moving body. The method involving producing an output corresponding to the ability to perform an operation within a safe limit on a moving vessel. The method comprising the steps of acquiring real time data from instrumentation on the vessel indicative of first and second elements of vessel motion relevant to the safety of the operation. Processing the data relating to each element of motion. Scaling the data relating to each element to a common scale to provide first and second values relating to the respective elements of vessel motion. Determining which value is of greatest significance and providing a output indicative of the greatest value.

Abstract: An aircraft handler (10) for use with an undercarriage of an aircraft, the handler being self-propelled and comprising a generally “U” shaped body (11) having arms (12 & 13) linked by a bridge (14) at one end thereof with a pair of drive wheels (16 & 17) located one at the free end of each arm, with at least one wheel(15) located adjacent the bridge(14). A pair of clamping jaws (51) are mounted on the body (11) between the drive wheels (16 & 17) and the bridge (14)and jaws (51) have a lower profile than the arms (12 & 17). The drive wheel (16 & 17) are driven by DC electric motors powered by batteries stored in the arms.

Abstract: A tug device for moving small aircraft having front wheels. A portable drill is connected to a drive wheel and a frame is attached to the wheel. The device is compact and easily assembled for use and disassembled for storage. The device includes a pair of drive wheels and is steerable when a locking latch is released. The locking latch provides rigidity to the device under load.

Abstract: A flying vehicle assembly apparatus comprises a winged flying craft and a powered craft for propelling the flying craft and a tether assembly comprising one or more first rigid struts having a first end pivotally secured to first biased pivot connections adjacent to the flying craft and a second end pivotally secured to second biased pivot connections, and one or more second rigid struts having a first end pivotally secured adjacent to the powered craft and a second end pivotally secured to a second biased pivot connection. The first and second biased pivot connections urge the flying craft and the powered craft toward one another, and whereby during flying operation, the powered craft is generally forward of the flying craft.

Abstract: An automatic guidance and control system for aircraft moving on the ground. On-ground taxi control is provided in response to steering commands for nosewheel positioning.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.

Abstract: A traction vehicle for moving a nose wheel of an aircraft comprises a wheel-mounted chassis including an engagement and hoisting device that can be raised and lowered. The engagement and hoisting device has a nose-wheel holder and a U-shaped stand having an opening facing the aircraft. The nose-wheel holder and the stand are shaped as two separate units and have co-operating journaling members arranged in a circular arc to provide rotational movement between the holder and the stand.

Abstract: A tug device for moving small aircraft having front wheels. A portable drill is connected to a drive wheel and a frame is attached to the wheel. The device is compact and easily assembled for use and disassembled for storage. The device includes a pair of drive wheels and is steerable when a locking latch is released. The locking latch provides rigidity to the device under load.

Abstract: A sea-land-sky craft capable of navigating on the water, running on the land and flying in the air (that is, climbing vertically, flying horizontally and hovering in the air) usable in a new transportation system 1. The sea-land-sky craft comprises rotating wings rotatable in opposite directions on their centers. Mounting shafts are disposed at positions eccentric to the centers of the rotating wings and mount the rotating wings so that the orientation of the rotating wings can be turned. A cylindrical duct encloses the outer circumferences of the maximum diameters of the rotations of the rotating wings. A fuselage is located at a central portion of the craft. Movable struts are provided for connecting the cylindrical duct and the fuselage. In the sea-land-sky craft, the cylindrical duct is deformed into a fixed wing by the actions of the movable struts.

Abstract: A method and system for braking aircraft landing gear wheels after initialization of landing gear retraction. The system includes monitors, controlling components, measurement components, a fault recording memory, fault annunciation components, wheel braking system and brakes. The monitors monitor speed of the landing gear wheels and landing gear position. The control component generates braking instructions based on the monitored speed of the wheels and position of the landing gear.

Abstract: An apparatus for steering a nosewheel on an aircraft, or the like, while the aircraft is on the ground. The apparatus includes a steering shaft that engages a cluster of gears and transfers torque from a steering command to the gears. The steering shaft is rotatable from a centered position in response to steering torque. A centering mechanism imparts a counter-torque on the cluster of gears to restore the steering shaft to the centered position when steering torque is released. The gear cluster comprises two drive gears that accurately guide the steering shaft to the centered position under the influence of the centering mechanism. The gear cluster is configured to minimize and compensate for gear wear, permitting accurate and consistent centering of the main shaft each time a steering torque is released.

Abstract: A road/air vehicle is able to quickly and easily convert between two configurations, air configuration and road configuration, to facilitate practical operation as both an aircraft and as an automobile. In air configuration the craft includes two laterally symmetrically flight surfaces; a smaller forward canard wing, generally horizontally disposed and a larger rearward main wing generally horizontally disposed with fin surfaces, generally vertically disposed, at each tip. Control surfaces on the main wing, the canard wing and the tip fins severally provide roll control, pitch control and yaw control in flight. The wheels/undercarriage are of a laterally symmetrical rectangular pattern, with the lateral distance between the two forward wheels and the two rearward wheels being similar. The forward wheels are steerable for ground operations. A suitable powerplant drives the rear wheels for ground operations. A second suitable powerplant provides direct atmospheric thrust for flight operations.

Abstract: A tug device for moving small aircraft having front wheels. A portable drill is connected to a drive wheel and a frame is attached to the wheel. The device is steerable, having a wheel mounted on a vertical set of pins such that the wheel is pivotable about the axis of the pins to permit turning the wheel on that axis and steering the tug while operating the drive mechanism.

Abstract: A tug device for moving small aircraft having front wheels. A portable drill is connected to a drive wheel and a frame is attached to the wheel. The device is steerable, having a wheel mounted on a vertical set of pins such that the wheel is pivotable about the axis of the pins to permit turning the wheel on that axis and steering the tug while operating the drive mechanism.

Abstract: A towbar for the towing of aircraft which will enable the user to attach the same to, selectively, the front nose wheel or the front wheel strut of an aircraft. The towbar includes a longitudinally extending towing bar with a vehicle attachment on one end thereof to facilitate attachment to a towing vehicle with the other end thereof provided with a pair of arms to engage the nose wheel or strut. The arms are openable and closeable for attachment to the wheel or strut and the mechanics for opening and closing are arranged within the longitudinal towing bar. The mechanism for opening and closing includes a slide moveable on the bar in a longitudinal direction and a structure for converting this longitudinal motion to rotational motion for rotating an arm control rod which, through a threaded end and threaded bearing will move one arm with respect to the other.

Abstract: A remotely controlled movably powered shuttle frame has foundation pads attached thereto at all four corner portions for separating skid pads of a helicopter from the flight deck of a marine vessel, wherein both the skid pads and the fight deck are outfitted with hook and loop fabrics. Skid blades displaced from retracted positions underlying the foundation pads are extended from the shuttle frame underlying a landed aircraft whose weight has been lifted off the flight deck by lifting arms pivotally mounted on the foundation pads. The aircraft carried by the lifting arms on the shuttle frame after the skid blades are retracted is shuttled by wheeled movement of the shuttle frame to a desired location on the flight deck.

Abstract: A VTOL aircraft (or other vehicle such as a sea vehicle) includes a pair of elongated ducts on opposite sides of the vehicle body, and a plurality of powered propellers (or other propulsion units such as jet engines) mounted within and enclosed by each of the elongated ducts, such as to produce an upward lift force to the vehicle. Each of the elongated ducts has a short transverse dimension slightly larger than the diameter of the blades of each propeller enclosed thereby, and a large transverse dimension slightly larger than the sum of the diameters of the blades of all the propellers enclosed thereby.

Abstract: The present invention relates to a vehicle for land and air transport and, more specifically, to a vertical take-off and landing vehicle for land, water and air transport which is submersible and utilizes compressed air to lift and propel said vehicle during travel. The land-based drive train and the aviatic air compression system are powered mechanically by the vehicle's engine or electrically by rechargeable battery banks and generators or a combination thereof thereby effectively reducing the present invention's reliance upon fossil fuel sources.

Abstract: A towbar for the towing of aircraft which will enable the user to attach the same to, selectively, the front nose wheel or the front wheel strut of an aircraft. The towbar includes a longitudinally extending towing bar with a vehicle attachment on one end thereof to facilitate attachment to a towing vehicle with the other end thereof provided with a pair of arms to engage the nose wheel or strut. The arms are openable and closeable for attachment to the wheel or strut and the mechanics for opening and closing are arranged within the longitudinal towing bar. The mechanism for opening and closing includes a slide moveable on the bar in a longitudinal direction and a structure for converting this longitudinal motion to rotational motion for rotating an arm control rod which, through a threaded end and threaded bearing will move one arm with respect to the other.

Abstract: An aircraft towbar apparatus comprises a pair of tubular members having proximal ends coupled to a hitch assembly for attachment to a towing vehicle. Each tubular member includes a gripping member at a distal end for gripping an aircraft wheel assembly. The apparatus includes a wheel assembly intermediate proximal and distal ends which serves as a fulcrum for vertical positioning of the gripping members relative to an aircraft wheel assembly. A support handle extends from the distal end of one tubular member to enable a user to vertically position the gripping members. A scissor jack is connected to the tubular members and extends therebetween at a position spaced from the distal ends. An elongate handle bar is coupled to the scissor jack and extends to a crank handle adjacent the hitch assembly such that a user may rotatably actuate the scissor jack to vary the spacing between the tubular members.

Abstract: The present invention is directed to a method of and an apparatus for the disassociation of water into hydrogen and oxygen via a thermolysis, heat/ignition process. The hydrogen and oxygen produced may be burned as fuel in a hydrogen thermolysis reactor to provide propellant for a turbine or to provide heat to generate steam for a steam engine or may be combusted in a combustion engine. The present invention can produce heat for space heat for buildings and for manufacturing, etc. or can produce mechanical drive that can generate electricity, power hydraulic systems, or provide thrust to propel airplanes, spaceships, rockets or submarines (which have their own oxygen supply for combustion in outer space or underwater from the oxygen contained in the water converted into hydrogen and oxygen) and can provide the energy needed to power automobiles, trucks, buses, trains, boats, etc.

Abstract: An aircraft towbar apparatus comprises a pair of tubular members having proximal ends coupled to a hitch assembly for attachment to a towing vehicle. Each tubular member includes a gripping member at a distal end for gripping an aircraft wheel assembly. The apparatus includes a wheel assembly intermediate proximal and distal ends which serves as a fulcrum for vertical positioning of the gripping members relative to an aircraft wheel assembly. A support handle extends from the distal end of one tubular member to enable a user to vertically position the gripping members. A scissor jack is connected to the tubular members and extends therebetween at a position spaced from the distal ends. An elongate handle bar is coupled to the scissor jack and extends to a crank handle adjacent the hitch assembly such that a user may rotatably actuate the scissor jack to vary the spacing between the tubular members.

Abstract: A system for aiding ground maneuvering of an airplane. The system includes at least one camera mounted on the airplane for generating video images of at last one gear with tires, preferably a main or nose landing gear and the surrounding ground. The cockpit of the airplane includes a video display device that displays the generated video images and a user interface that allows selection of the format for displaying the generated video images. A camera mounted within a moveable component of the airplane is mounted on a movable device that compensates for component movement. The system also includes a display generator for generating in real-time superimposed oversteer targets on the displayed video images. The video images with oversteer targets assist the pilot in determining the airplane's actual position relative to runways, taxiways, obstacles and other ground features and to maneuver a plane with a wide wheel track long wheelbase, or both accordingly.

Abstract: A device and method for lifting an aircraft wheel assembly. The device comprises first and second wheel-engaging supports connectable to a bearing structure and rotatable relative to one another between open and wheel-cradling configurations, the device further comprising an actuator connected to the bearing structure to enable raising or lowering of the supports relative to the ground when in the wheel-cradling configuration.

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: A transport cradle for a skid-supported helicopter having a pair of laterally spaced and generally parallel support skids. The transport cradle has a main frame (10) supported by transport wheels (16) and a pair of laterally spaced elongate supports (11) extending generally parallel to each other and forming part of the frame. The supports are each intended to engage and to lift a respective helicopter skid after the cradle has been presented to a helicopter supported on the ground by its skids. The cradle also comprises devices (13) for adjusting the spacing apart of the supports to correspond with the spacing apart of the helicopter skids. The cradle also has clamping devices (14, 15) provided on each support and operative to engage and clamp the respective skid to the support.

Abstract: A Ground-Effect Flying-Boat system with a special hull producing a very low drag, but high lift, both in the water and in the air. A high pivoting-wing of an auto-stable airfoil, and one or more rear spoilers fitted on the hull-stern of the vessel having a special airfoil and determined horizontal and vertical slots producing very low drag, but a strong downward airstream deflection so as to increase the height of the ground-effect. The wing configuration allows for automatic maintenance of horizontal flight and automatic inclination in turns as well as an automatic anti-crash system against strong descendent gusts. These automatic stability features allow the craft to fly in rain or foggy weather without need of I.F.R. instruments, due to slide and spin resistance. In addition, the craft will not stall "nose down", but lose altitude slowly, with the hull remaining always practically horizontal. Water-landing is possible at a very reduced speed and even vertically into very strong winds and waves.

Abstract: A roadable airplane consists of a single-seat three-wheeled vehicle with wing panels hung longitudinally on the sides of the chassis for road use and attached transversely to a spar box for flight. A power train is used that enables the simultaneous powering of two rear wheels and an overhead pusher propeller for transition from road to air travel. A transaxle for a four-wheel automotive vehicle was found to be advantageously suitable for this purpose. Multiple gears and differential outputs drive the wheels, providing a normal automotive performance on the road. Multiple gears are also available to drive the propeller, thereby providing the function of variable-pitch performance using a fixed-pitch propeller. The vehicle includes a standard automotive gear shift and pedal controls for clutch, brake and accelerator operation; a novel joystick assembly is used to steer the front wheel and to control wing flaps, an elevator and a rudder.

Abstract: A fixed-wing four-to-six-seat light aircraft that can be easily converted to a roadway vehicle within minutes by a single person in the field, comprising a one-piece wing center panel with foldable wing tips on each sides. The whole wing unit is then rotatably mounted on top of the fuselage. The aircraft features a conventional front-engine-and-propeller lay-out, with a foldable tail section for convenient roadability and garageability. All the wheels are retractable in flight, and it has a long-span, high aspect-ratio wing for exceptional climb and cruise efficiency. The vehicle has a low ride-height with a low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism for good ground handling ability. Ground propulsion is by automotive-style transmission driving the rear wheels or by hydraulic motors in the all-wheel retractable version.

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: An element (14) of a swivelling aircraft landing gear, such as an element of the swivelling, rear or tail gear of a wide-body aircraft, equipped with a swivelling, front or nose gear and a non-swivelling, underwing gear, has a swivelling truck (16) carrying a swivelling, front axle (20) and a swivelling, rear axle (22). The orientation of each of these axles is respectively ensured by two linkages (44-49), which are independent of one another and connected to a non-rotary, fixed support (30) carrying the truck (16), in such a way that the axes (Y1, Y2) of the front (20) and rear (22) axles and the axis of the truck (16) intersect at the instantaneous rotation center of the aircraft.

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: The present invention is provided to overcome the difficulties of a conventional tail wheel-type airplane such as the remarkably inferior straight ground-run properties during a take-off run (particularly, low-speed taxiing), and the extremely difficult control during the take-off run. A mechanism of the present invention is structured such that left and right coaxial gears and main wheel gears (or connection gears) are engaged together when not stepping on rudder pedals in take-off and landing run. Under this operation, since the above gears themselves are engaged together, left and right main wheels rotate synchronously through a co-axis, and as a result, an airframe makes a straight ground-run. When stepping on the rudder pedals in taxiing, the coaxial gears and main wheel gears (or connection gears) are disengaged from each other, the left and right main wheels then rotate independently, and as a result, the airframe easily taxis (i.e., a case of turning the airframe right or left).

Abstract: A universal aircraft steering by-pass pin (24) comprising a tridimensional shaft (26) that can be installed into various nose gears (28) of different types of aircraft (30), to remove the steering capability of a pilot during a push-out procedure, when a tow bar (32) of a tow vehicle (34) is connected to the nose gear (28) of the aircraft (30). The aircraft (30) can be safely towed to a position where the pilot can start the engines and steer the aircraft to an appropriate runway (36) for takeoff after the tridimensional shaft (26) and tow bar (32) are removed from the nose gear (28).

Abstract: In a towing vehicle (1) for manoeuvring aircraft (11) without a towbar, the chassis (5) of which vehicle has a fork-like receiving area (7) between the wheels (6) of a coaxial wheel suspension, in which receiving area there is arranged a retractable and extensible gripping and drawing-in device (9) which is fastened to a lifting blade (8) and by means of which the nosewheel (10) of an aircraft (11) can be gripped and drawn onto the lifting blade (8) which is pivotable relative to the chassis (5) both about a transverse axis and, for matching to oblique positions of a nosewheel (10) which has been received, about a longitudinal axis by means of two fluid piston-cylinder units (12) arranged symmetrically relative to one another between the chassis (5) and the lifting blade (8), the lifting blade (8) is coupled so as to be pivotable in all directions by means of a ball joint (25) which is fastened to the chassis (5) of the towing vehicle (1) and acts centrally on the back of the lifting blade (8).