Abstract: A structural support comprises inner and outer elements which are telescopingly engaged, a cage secured to the inner element and having apertures in which balls are disposed which are disposed radially between the two elements, and a frangible connection securing the two elements against relative axial movement. In the locked relative positions of the elements, the outer element has locally an increased internal diameter portion and the balls are radially disposed in this position or are moved into the portion on being subjected to an axial force which breaks the frangible connection, so that the relative axial movement of the elements results in the ball plastically deforming the outer element and absorbing energy from the force to protect the body carried by the support. The support can be used to provide a brace operating as a strut and/or a tie, or a shock absorber, or, by mounting a damping piston slidably in the inner tubular element can provide a shock absorbing piston and cylinder unit.

Abstract: The undercarriage comprises: a leg (1) pivotally mounted about a first pivot axis (14) which is fixed relative to a rigid structure of the aircraft; a main side-brace (30) comprising at least two articulated levers (31 and 32) having first ends pivotally connected to each other about a fourth pivot axis (33), having respective other ends pivotally mounted about a second pivot axis (37) which is fixed relative to the rigid structure, and pivotally mounted about a third pivot axis (36) which is fixed relative to the leg; and a drive (40 to 48) for causing the levers to pivot relative to each other. The first, second, third, and fourth pivot axes are parallel to each other.

Abstract: The present invention relates to landing gears retractable between two positions.The landing gear includes essentially a lever (14 ) mounted rotatably around an axis (5), a rocker beam (7) mounted rotatably on the same axis (5), a strut (21) including two links (22,23) pivoting in relation to each other, the strut being connected to the lever, a shock absorber (18) fixed respectively on the lever (14) and the rocker beam (7), and an actuating cylinder (32) for applying a pivoting force to the lever (14). This landing gear finds a particularly advantageous application in aircraft of the commuter type.CROSS REFERENCE TO RELATED APPLICATIONThe present application relates to application Ser. No. 354,010 filed on Mar. 2, 1982, and entitled "FUSELAGE LANDING GEAR WITH TANDEM WHEELS" by inventors Andre Turiot and Michel Derrien, our reference 4126.

Abstract: The landing gear for aircraft comprises at least two rocker beams respectively carrying wheels, the rocker beams being connected rigidly and respectively to two points of the rigid structure of the aircraft, each rocker beam being connected to two other rigid points of the aircraft structure by an assembly composed of a lever and a shock absorber mounted rotatably on each other, and a connecting rod of constant length connecting two levers and an actuating cylinder to rotate at least one of the two said levers. The landing gear finds a particularly advantageous application as a fuselage landing gear with tandem mounted wheels.

Abstract: This invention relates to landing gears. The described landing gear is characterized essentially by the fact that it comprises a leg (3) at one end of which is fixed a wheel (14 ) for rolling around a pivoting pin (11), a shock absorber (15) of which one end (22) is connected to leg (3), a strut (24) whose end is connected to leg (3) and links (39, 37, 41) connecting the end of strut (24) to the pivoting pin (11) so as to cause the wheel to pivot when the landing gear is retracted. This landing gear finds an advantageous application as a fuselage landing gear of the tripod type.

Abstract: A three wheeled, generally in line, articulated landing gear with the lever trailing the lever hinge axis, applied in a pair. Each shock strut, axle, and rolling assembly counter twist 90.degree. upon retraction about a laterally offset post to present the smallest frontal area or pod size. The twisting mechanism, the door links and the over center down lock are all tied mechanically to the gear so that no other sequencing is required during gear retraction or extension.

Abstract: This invention relates to an improvement in a retractable landing gear for jumbo aircraft, in particular of the high-wing monoplane design, with a number of steerable landing units which are retractable into wells in the aircraft fuselage, the improvement comprising (a) means mounting a plurality of landing gear unit means which are spread into two or more rows that extend predominantly over a range at the aircraft fuselage running in the aircraft longitudinal direction, (b) said landing gear unit means and frames belonging to the airframe structure being designed in the manner of a grid division in which, between two particular unencroached main frames of the structure, a particular landing gear unit of one row is arranged and including means to retract it into well means between the frames, and (c) all landing gear units being made of identical components and being of the same dimensions.

Abstract: The front bearing for a landing gear trunion is carried by a rear wing spar and the rear bearing is carried by a landing gear beam which is pivotly attached at its inner end to the body frame. A main attach pin pivotally connects the outer end of such beam to a pair of connector plates, one located on each side of the connection. A pair of shear pins connect the connector plates to a short cantilever beam which is connected to and projects inwardly from the rear wing spar, generally in line with the landing gear beam. One of the shear pins is positioned generally horizontally outwardly from the main attach pin. The second shear pin is positioned generally vertically below the main attach pin. Generally vertical overloads are carried by the lower shear pin load and such shear pin is designed to fracture in response to a load slightly below the vertical load reacting capability of the reaction structure.

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: A main undercarriage train for an aircraft which is retractable substantially laterally, the train comprising two undercarriages which comprise identical legs each having a plane of symmetry which passes through its pivot mounting axis which is inclined relative to the plane of symmetry of the aircraft.

Abstract: Aircraft lowering and raising apparatus for loading and unloading purposes wherein the apparatus comprises four supporting structures, two located at a spaced distance at the left and two similarly at the right side of the fuselage. Each structure is horizontally carried within the aircraft and can be extended in a vertical position outside of the aircraft. Each structure includes a hydraulic telescoping piston cylinder arrangement with a ground feeler for extending a tripod carriage which is pivotally connected to the cylinder. Upon operation, the structure moves from its aircraft storage unit outside in vertical position and engages the ground by extension of its telescoping member to support the aircraft, thereupon the landing gears are contracted into the aircraft body, and thereafter the telescoping piston cylinder is contracted so that the aircraft is lowered for cargo handling.

Abstract: A punch type release lock intended for use primarily in retaining load supports such as pallets in locked position in an aircraft. The lock comprises a detent mechanism which is inserted into a recess preferably at the side of the load support. A preferred form of detent mechanism comprises a pair of relatively movable elements, at least one of which is pivoted. The elements include abutments which are movable apart as the elements are inserted into the recess. When a load is applied to the pivoted detent, as for example, by a parachute extracting system, movement of the element in a direction to withdraw the element to release the load support is prevented by a load cell comprising a fuse plate and punch, in which the punch is prevented from movement by the fuse plate until attainment of a predetermined load on the pivoted detent element.

Abstract: A strut release mechanism for the forward strut of a hydrofoil craft will predictably fail when the strut experiences a predetermined impact. The failure occurs about a horizontal axis so that the strut follows a predetermined path while separating from the craft and thereby avoids impact damage to the strut or to the craft. Shear failure and tension failure structures are disclosed.

Abstract: An aircraft landing gear including a leg member supporting at least one wheel, the leg having a first point of attachment around a first axis of rotation about a first point on the aircraft, a strut including a rod and a lever pivotally mounted on one another around a third axis, the rod having a second axis of rotation on a second point of attachment to the aircraft and the lever being pivoted about a fourth axis on the leg, and an operating jack applying at least one rotational torque to the strut and the leg wherein one end of the jack is connected to a third point on the leg and the other end of the jack is connected to a fourth point on the strut, the third and fourth points being located substantially near the first and second points of attachment.

Abstract: A body-braced main landing gear assembly for a commercial airplane includes a set of landing wheels journalled to a shock absorber strut. The shock strut and wheels are swingably attached to the underside of the wing structure by a trunion shaft for lateral as well as fore and aft swinging movement between an extended position wherein the wheels depend downwardly from the wing for taxiing and landing of the airplane and a retracted position wherein the wheels and shock strut are swung inwardly and upwardly into a wheel bay in the airplane fuselage. The shock strut is braced in the extended position by a foldable drag strut and a rigid radius brace. The foldable drag strut is attached at one end to the shock strut and is attached at its opposite end to the fuselage body at a point inward and forward of the trunion shaft. The radius brace is attached at one end to the shock strut and is attached at its opposite end to a point on the fuselage body inward and rearward of the trunion shaft.

Abstract: A fail safe retractable landing gear unit for model aircraft utilizing a fluid pressure powered piston type activator to retract and hold the landing gear retracted with sustained pressure. Upon release or loss of pressure a return spring acting on the piston automatically extends the landing gear. The hinged retracting mechanism and the activator are mounted rigidly in a unitary bracket, which holds the activator in sealed condition and precise alignment, the mechanism having positive locking in the retracted and extended positions to minimize landing gear loads on the mechanism and activator. Only a single pressure connection is required to each unit in a multiple unit landing gear installation.

Abstract: A main landing gear assembly for an airplane includes a set of landing wheels journalled to a shock-absorber strut. The shock strut and wheels are swingably attached to the wing structure by a pair of trunnion bearings for lateral swinging movement between an extended position wherein the wheels depend downwardly from the wing for taxiing or landing of the airplane and a retracted position wherein the wheels and shock strut are swung inwardy and upwardly into a wheel bay in the airplane fuselage. The shock strut is braced in the extended position by a foldable drag strut and a foldable side strut, each strut attached at an intermediate position on the shock strut. The foldable struts and the trunnion bearings provide a four-point support configuration which allows a net reduction in aircraft weight due to improved distribution of drag and static loads into the wing/body structure.

Abstract: A main landing gear with swing-bar and lateral lifting for aircraft. Two undercarriages are provided which are positioned symmetrically on either side of the longitudinal plane of symmetry of the aircraft, each one having a leg 1 articulated around a lifting axis 5, and a swing bar 16 around a transverse axis 18. The swing bar 16 carries a wheel 21 pivotally mounted around an axis of rotation 19. The maneuvering of the undercarriage and the bracing thereof are insured by a bracing jack 13, and the deflections of swing-bar 16 are damped by a shock absorber 10. The leg 1 of the undercarriage has a first plane of symmetry (X,X) perpendicular to the lifting axis 5 and the longitudinal plane of symmetry of the aircraft and the swing-bar 16 has a second plane of symmetry (Y,Y) defined by the transverse axis 18 of the axis of rotation 19.

Abstract: Shock absorbers and shock absorber jacks each of which comprises a shaft containing a low-pressure chamber and sliding in a first chamber of a first cylinder which is separated from another or second chamber which contains a high-pressure chamber, by means of a partition which is traversed by a grooved shaft borne by a separator piston in the other chamber and guided in a sleeve borne by the partition. In the event of the penetration of the shaft into the first cylinder at a rate of very much higher than normal, then the two grooves in the shaft communicate with each other and permit the flow of oil from the first chamber towards the second chamber and towards the low-pressure chamber because of a radial passage through the sleeve near the partition.

Abstract: A kneeling nose landing gear assembly for an airplane enables the nose of the airplane fuselage to be lowered to facilitate loading and unloading of cargo. A pair of hydraulic kneeling actuators pivotally coupled to the midsection of a pivotable landing gear strut are selectively positionable against a pair of retractable stop assemblies positioned above the strut. The actuators are pressurized against the cooperable stop assemblies to thereby cushion the descent of the airplane nose to a lowered position wherein the landing gear strut is pivoted forwardly into an angled kneeling position intermediate between an upright taxiing position and a retracted position. The kneeling actuators are subsequently pressurized to raise the nose of the airplane and swing the landing gear strut back into the taxiing position from the kneeling position.

Abstract: A wing mounted retractable aircraft undercarriage with a trailing wheel or wheels comprising a rigid leg casing, pivotally mounted on the wing about a retraction axis, a rocking lever pivoted on the leg casing, supporting the wheel or wheels and mounting the lower pivot connection of a shock absorber located behind the leg casing, an upper pivot connection of the shock absorber to a lever, which lever is pivotable on the leg casing about an articulation axis which is distinct from the retraction axis, a rod of fixed length pivoted at one end to the lever and at the other end to a fixed position on the wing, so that upon retraction of the undercarriage by the action of a retraction jack, the rod causes rotation of the lever with respect to the leg casing, which rotation, by traction of the expanded shock absorber causes pivoting, with respect to the leg casing, of the rocking lever mounting the wheel or wheels towards the retraction axis, and thus an overall shortening of the undercarriage.

Abstract: A retractable fuselage mounted undercarriage comprising a leg casing mounted to pivot on a main universal joint about an axis which extends longitudinally of the aircraft, the leg casing mounting a wheel assembly which can pivot on the leg casing, a lateral deflection shock absorber and a manoeuvreing and wind bracing jack each connected to the leg casing by a joint and each connected to the fuselage by a joint, the main universal joint being mounted to pivot on the fuselage about an inclined retraction axis which does not pass through the point where the shock absorber is connected to the fuselage, so that, during lowering and retraction of the undercarriage effected by extending or retracting the manoeuvreing and wind bracing jack, the shock absorber acts as a directer bar and orientates the axis of the leg casing, which leg casing is rotated as the main universal joint pivots on the fuselage about the inclined retraction axis.

Abstract: A vehicle for traveling in the air and/or on the ground is equipped with two, four, or eight propellers on vertical shafts, each driven by a rotary hydraulic motor of the radial-piston type. The motor may comprise two rotors which are connected in individual hydraulic circuits supplied with fluid from different hydraulic pumps. One embodiment of the vehicle comprises an automobile with the propellers mounted in oblique air ducts or in shrouds pivotable in the travel direction. Each rotor of the hydraulic motors is coupled to the shaft unidirectionally so that in case of failure, the shaft can be driven by the other rotor. Each hydraulic pump preferably produces four equal fluid flows and comprises two rotors on a common shaft, each rotor with two separate groups of cylinders, the eccentricity of at least one of the rotors being adjustable. Both the hydraulic motor and the pump have inlet and outlet connections on the radial periphery of the housing.

Abstract: A landing gear undercarriage which attaches to and retracts into the fuselage of an aircraft. The undercarriage has left and right matching portions, each of which includes a forward strut and a rearward hydraulic jack, both of which are coupled to the fuselage by cardan joints. A shock absorber is mounted on the fuselage outside of the strut and converges downwardly towards the strut to which it is coupled at the bottom by a cardan joint. A cylindrical sleeve is mounted at the bottom of the strut, and a spindle which supports a landing wheel is rotatably mounted in the sleeve. The bottom of the hydraulic jack is coupled to the spindle, and the arrangement is such that as the jack causes the undercarriage to retract into the fuselage, the spindle and wheel are rotated into a flat position in which they may be stored in a relatively small landing gear well.

Abstract: A landing gear assembly mounted to a trunnion for movement about a transverse horizontal axis to a stowed position. The trunnion is mounted to an intermediate member which is in turn mounted to the aircraft structure for rotation about an axis skewed with respect to the trunnion axis. The intermediate member is releasably held to the aircraft structure by a fuse pin which gives way under conditions of excessive loading on the landing gear assembly, so that the landing gear assembly is able to rotate about its skewed axis to an out-of-the-way location clear of the cargo compartment.

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: An aircraft landing gear assembly which is to be movable from a retracted position within the fuselage of the aircraft to a position extended outwardly from the fuselage of the aircraft. The landing gear assembly includes a main supporting strut leg assembly to which is pivotly secured a wheel lever assembly. The tire assembly is pivotly mounted upon the free end of the wheel lever assembly about an axis which is angularly disposed with respect to the longitudinal center axis of the tire assembly. A linkage assembly connects with the tire assembly to plane the tire to a different angular position with the landing gear assembly in the retracted position. A side brace assembly, to provide lateral support, is piovtly interconnected between the strut leg assembly and the aircraft. The side brace assembly comprises a pair of members which are foldable upon themselves when the landing gear is retracted.

Abstract: An aircraft letdown system is deployable in the event of power failure or mechanical failure over inhospitable terrain or in the event of environmental conditions which preclude VFR or IFR landings. A parachute system, which is attached to the aircraft at a point in approximate vertical alignment with the aircraft center of gravity, is selectively energized by the pilot when it becomes apparent that a safe normal landing cannot be made. On energization, the parachute canopy and the shroud lines are repositioned from the place of storage to a location external to the aircraft and deployed in the conventional manner. To alleviate the shock of landing to the passengers and cargo, a specially constructed impact absorbing landing gear is extended and the occupants are further protected from the landing shock through impact absorbing seats.

Abstract: An undercarriage for an aircraft has a safety device which fails under a predetermined breaking load to separate a leg member of the undercarriage from a rigid element of the undercarriage, the rigid element remaining on the aircraft. The aircraft has on the frame thereof a front mounting and a rear mounting for mounting the undercarriage and said undercarriage comprises said leg member and said rigid element which is mounted in and extends between said front and rear mountings and forms an axle about the axis of which the leg member of the undercarriage can be pivoted for raising the lowering the undercarriage.

Abstract: A ground-effect landing gear for use on aircraft intended for performing take-off and landing on unprepared soft ground comprises a platform mounting a flexible enclosure constructed in the form of a system of inflatable envelopes bounding an overpressure space near the ground surface. During transition to hovering and during movement of the aircraft the space is kept in communication with a compressed air source.

Abstract: A landing gear for an aerodyne which is raised towards the rear of the aerodyne, including a structural member with a shock absorber for each undercarriage and connected to at least one wheel, and at least one truss actuating jack operative to employ aerodynamic forces opposing the lowering of the undercarriages to aid in the locking of the truss actuating jack and thus the undercarriages in the landing gear down position.

Abstract: An aircraft which operates between the surface and the air as a rotating wing aircraft (helicopter-autogiro). When airborne a rotor pylon latch is released and the pilot flies the rotor system aft about its pivot to the fuselage to form the tail of a high speed jet propelled airplane. Altering the pitch angle of the blades controls the aircraft, called a convertiblade, for helicopter-autogiro and airplane configurations and for moving the rotor between its configurations. The rotor is revved up with rocket fuel piped to burner jet nozzles located at the blade tips. A jump-take-off may be used to efficiently get the convertiblade airborne at a good climbing speed. Prior to landing, the rotor blades are released from their operation as roll control surfaces for the airplane configuration; then, they are permitted to rev-up and act as a brake to reduce the speed of the airplane.

Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

Abstract: An air cushion landing system for an aircraft. The landing system has an air cushion assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with two folding portions, inflatable bags attached to the underside of the arm, and flaps to define an area of cushion air. The inflatable bags provide primary attenuation of landing impact. Actuators are provided to retract the assembly following takeoff and extend it for landing.

Abstract: The landing gear units for a high-wing aircraft are retractable into a single elongated carrier, which in turn revolves at a midpoint about a vertical axis in the fuselage. When deployed the carrier extends transversely outwardly from opposite sides of the fuselage to position the landing wheels in a transverse array. When stowed, with the wheels retracted into the carrier, the carrier is rotated into a longitudinal notch in the bottom of the fuselage.

Abstract: Disclosed is a steerable, articulated landing gear particularly useful on cargo aircraft and providing a capability to selectively raise and lower the aircraft fuselage, and hence the cargo deck, to a height convenient for loading and unloading of cargo therefrom. The gear includes a shock strut, and a wheel lever on one end of which are mounted two wheels. The wheel lever is pivotably connected to the lower end of the strut at an articulation point remote from the rotational axes of the truck wheels. An extendable-retractable shock absorber mounted within the strut is connected to the lever at a point between the strut-lever articulation and the rotational axes of the wheels. Retraction of the shock absorber lowers the strut-lever articulation relative to the axes of the wheels. A ground-engaging member or "kneeler" depending downwardly from the lower end of the strut at the strut-lever articulation defines a flat, horizontally orientable, ground engaging surface.

Abstract: An articulated, retractible landing gear for helicopters and the like includes a three member drag brace assembly having a retraction brace pivotally connected to the helicopter fuselage at its inboard end and to an upper drag brace at its outboard end, with the latter pivotal connection being along the articulation axis of the landing gear, the upper brace being pivotally connected at its other end to a lower brace which in turn is connected to the oleo strut of the landing gear by a universal joint, the pivotal connection between the upper and lower braces in the extended position of the landing gear being on an axis normal to both the drag brace center line and the articulation axis.