Aircraft undercarriage strut |
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IPC classes for russian patent Aircraft undercarriage strut (RU 2307046):
      
 Aircraft landing gear main leg / 2297366
Aircraft landing gear leg has lever 1 with wheel 2 articulated on fuselage, gas-and-hydraulic shock absorber 4 whose rod 5 is articulated with lever, down lock 9, up lock 11 mounted on fuselage, down lock shackle 10, up lock shackle 12 articulated on lever, leg retraction-extension hydraulic cylinder 13. In center part, shock absorber body is articulated to member 7 made in form of fork whose other end is articulated via ears to cardan 8 which is articulated on fuselage; down lock is mounted on the same member ; down lock shackle is articulated on upper part of shock absorber body.
 The control mechanism of the landing gear of the aircraft / 2122964
The invention relates to aviation and management systems, the landing gear of the aircraft
 Retractable gear aircraft / 2088478
 Drive cleaning and landing gear of the aircraft / 2085445
The invention relates to the field of actuators cleaning and landing gear of the aircraft and can be used in the creation of new and modernization of existing aircraft
 Lock the retracted chassis / 2076827
The invention relates to mechanical engineering and can be used for securing cargo or structures up to a height of States, in particular in an aircraft, for fixing the landing gear of aircraft in the retracted position
 Power lock landing gear / 2068799
The invention relates to the field of aviation, and more particularly to a landing devices, and in particular to a retractable landing gear, and is intended for fixation of the retracted chassis
Aircraft landing gear main leg / 2297366
Aircraft landing gear leg has lever 1 with wheel 2 articulated on fuselage, gas-and-hydraulic shock absorber 4 whose rod 5 is articulated with lever, down lock 9, up lock 11 mounted on fuselage, down lock shackle 10, up lock shackle 12 articulated on lever, leg retraction-extension hydraulic cylinder 13. In center part, shock absorber body is articulated to member 7 made in form of fork whose other end is articulated via ears to cardan 8 which is articulated on fuselage; down lock is mounted on the same member ; down lock shackle is articulated on upper part of shock absorber body.
 Aircraft undercarriage strut / 2307046
Aircraft undercarriage strut contains shock absorber 1 with piston connected with fulcrum 2 by braces 3, folding strut with down position lock and up position lock lug. Eyes are formed on lower part of piston in which cardan is installed hinge connected with lug whose upper part gets into up position lock. Stops made on cardan and on lug limit deflection of lug relative to longitudinal and lateral axes.
 Stand of aviation chassis / 2360835
Stand of aviation chassis comprises hydraulic cylinder, cross brace and cross beam. On cross beam contact platforms are arranged, which are inverted at the angle that provides for self-braking under action of landing loads, and carriage is fixed in central upper part of stand for trajectory of chassis pulling-in and extension.
 Main landing gear of aircraft chassis / 2370413
Invention relates to aviation, namely to aircraft chassis gear. Walking-type chassis contains lifter and consists of shock-absorber hinge-connected to the aircraft framework. The shock-absorber is hinge-connected with brace coupled with carrier that actuates upper brace bearing hooking on a wing when the main landing gear is released. The carrier is provided with a tail, which is hinge-connected with a traction having hinged connection with framework. The brace is controlled by the lifter through the lever, which is hinge connected to the framework. Lifter and carrier are also in hinged connection with the lever. The lifter contains inner mechanical lock and is in hinge connection with the lever. One arm of the lever is hinge-fixed on lever framework, while the other arm is hinge connected with locking cylinder of emergency release of gear. The lock is represented with two jaws having grooves and latch, which are perpendicular to the released brace axis. Bushings of square external circuit are mounted on operating pins of the upper brace unit. Flat surfaces of bushings interact with hook grooves when main landing gear is released.
 Aircraft retractable landing gear / 2389650
Invention relates to aircraft engineering and aircraft retractable landing gear. Retractable landing gear consists of strut hinged to airframe, undercarriage, folding brace strut, retraction/extension drive, damper and undercarriage turning mechanism. Strut has hinged to be pivoted to folding brace strut, while folding brace strut other end is secured to airframe to revolve thereabout. Lever is arranged aligned with undercarriage wheels, oriented along flight direction and located in wheels rotational plane. Pivot is arranged on lever end for it to be jointed to said strut. Damper rod pivot joint is arranged between strut pivot joint and wheels axle on said lever. Dog is secured between aforesaid pivot joints in plane perpendicular to lever location plane. Proposed device comprises tie rod pivot-jointed to said dog and airframe. Said lever, dog and tie rod makes the wheels turning mechanism.
 Aircraft retractable landing gear / 2415777
Invention relates to aircraft engineering, particularly, to retractable landing gear. Proposed landing gear comprises leg 1 secured by suspension 2 to fuselage and articulated with folding brace 4 articulated with landing gear retraction drive 9, gear truck 3, damping cylinder 5, as well as gear truck turn mechanism with tie rod articulated with fuselage and damping cylinder 5. Said tie rod 6 is articulated with damping cylinder via ring 10 with lever 7 arranged on damping cylinder to rotate thereon and jointed with top link of splined hinge. Lever 7 is rigidly secured on ring 10 and has its free end pivoted to tie rod 6 of gear truck turn mechanism.
 Aircraft retractable landing gear / 2415778
Invention relates to aircraft engineering, particularly, to retractable landing gear. Proposed landing gear comprises shock absorbing leg 1 with crosspiece 2 secured thereon and articulated with landing gear IN/OUT tie rod 5. Said tie rod 4 is articulated with IN/OUT drive and aircraft fuselage. Shock absorbing leg turn mechanism is made up of two tie rods 8 and 9 located on one plate and rocker 10 pivoted on aforesaid tie rod 5. First tie rod 8 has its one end secured to fuselage and its other end secured to first arm of rocker 10. Second tie rod 9 has its one end secured to shock absorbing leg 1 and its other end secured to second arm of rocker 10. To be locked in OUT position, shock absorbing leg 1 and crosspiece 2 are provided with detachable fasteners 7 that allow rigid attachment of shock absorbing leg 1 and crosspiece 2 to aircraft engine nacelle 6.
 Aircraft landing gear with, at least, one noise killer / 2418716
Invention relates to aircraft engineering, particularly, to aircraft landing gear with noise killer and to aircraft equipped with said noise killer. Aircraft landing gear comprises noise killer 2, 3 linked with component 4 of said landing gear 1. Said noise killer 2, 3 incorporates separate circuit 5, 6 comprising geometrical cells 7. Note here that said circuit is arranged nearby component 4 so that one of its parts 8, 9 is, in fact, orthogonal with airflow E in final position of said component 4 with landing gear 1 in extended position.
 Aircraft landing gear with folding brace stabiliser release / 2453471
Aircraft landing gear comprises leg 1 pivoted to aircraft, folding brace 10 with two levers 11, 12, and brace stabiliser 20 in straight position. Said stabiliser 20 comprises two rods 21, 22 pivoted together and telescopic release 30 (release drive), for example, simple-action hydraulic cylinder. End 32 of release drive rod 31 is coupled with one of said rods 22. Rod 22 has arc-like slot 26 to receive rod 31. End of release drive rod 31 makes free moves in said arc-like slot without obstructing displacement of rod 22 outside of zigzag line position.
 Device to decrease aircraft undercarriage length / 2488523
Invention relates to aircraft engineering. Undercarriage comprises leg to be hinged to aircraft airframe and lower part with wheels mounted thereat. Lower part can move relative to said leg. Additionally, undercarriage comprises device decreasing undercarriage length between extended and retracted positions. Said device comprises interconnected first and second means. Said first means is engaged with undercarriage lower part or with moving element to displace together when lower part displaces relative to leg. Second means is articulated to airframe to allow it go to stop unless undercarriage is in retracted position.
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FIELD: aviation industry; aircraft takeoff and landing gears. SUBSTANCE: aircraft undercarriage strut contains shock absorber 1 with piston connected with fulcrum 2 by braces 3, folding strut with down position lock and up position lock lug. Eyes are formed on lower part of piston in which cardan is installed hinge connected with lug whose upper part gets into up position lock. Stops made on cardan and on lug limit deflection of lug relative to longitudinal and lateral axes. EFFECT: improved reliability of undercarriage in operation and closing of lock. 3 dwg
The present invention relates to a landing device for aircraft, namely to the support chassis, and can be used in mechanical devices fixing the landing gear in the lock retracted position during flight of the aircraft. The famous design of the front landing gear of the plane containing the shock absorber with a piston associated with traverse and braces. On the cylinder of the shock absorber is placed earring lock the retracted position. The shock absorber is installed steering device includes a steering cylinders, swing clamp, is attached to the lever of the wheels associated with the piston of the shock absorber. In the lower part of the lever installed the axis of the wheels mounted on it wheels with tires. (see instructions for the technical operation of the aircraft Il-62. Sec. 32-20-0, C.2, 3, 5. M: mechanical engineering, 1968) The disadvantage of this design is that the earring in the retracted position is close to the axis of rotation of the bearing, thus has a load greater than the weight of the support, as well as the fact that due to backlash in the device for fixing a support wheel located on a large shoulder, have increased movement and, consequently, between the wheels and the bottom of the compartment you want to install large gaps. The closest device to the claimed combination of essential characteristics is TNA is and chassis, containing the shock absorber with a piston associated with the crossmember braces (teeth with pins), a folding brace with lock released position and the shackle of the lock retracted position. Folding brace consists of upper and lower links. In addition, the lower part of the cylinder of the shock absorber is installed swivel yoke, to which one hinge plug with earring (loop) lock the retracted position. Another hinge plug is attached to the piston of the shock absorber. Inside the fork placed on the axis of the wheel with the tire. (see kN. Genitality, "Design aircraft", str, 264, RIS, M.: Mashinostroenie, 1995) For reasons that impede the achievement of the following result, is that because of the backlash in the joints swivel clamp, forks and earring lock the retracted require large clearances between the impeller and the bottom of the compartment, as well as the location of the earrings on the plug on a small shoulder relative to the axis of rotation of the support leads to an increase in the load lock, and consequently increase the mass of the castle and designs for its mounting, which reduces the reliability of support. The objective of the invention is to eliminate these disadvantages, namely improving the reliability of the chassis by reducing loads on the lock retracted position, reduce the impact of working backlashes in the gaps between the bottom from the ESA fuselage and support in the retracted position of the chassis, improve the reliability of the closing of the lock. This object is achieved in that in the landing gear of the aircraft, containing the shock absorber with a piston associated with traverse, braces, strut with the lock released position, and an earring lock retracted position, according to the invention on the lower part of the piston is formed lugs installed on the shaft, pivotally connected with the earring, the upper part of which is included in the lock retracted position, with the shaft as well as on the earring, made stops limiting deviation earrings relative to the longitudinal and transverse axes. Thus, placement earrings castle retracted position at the maximum distance from the axis of rotation of the bearing while cleaning reduces the load on the lock retracted support and reduce the effects of backlash in the joints of the hinge fitting support and lock the retracted to the gaps between the wheels and the bottom compartment of the chassis, install earrings castle retracted position articulated in the universal joint, the United swivel eyelets on the bottom of the piston, with the possibility of deviation in the longitudinal and transverse planes, allows for the classes earring advantageous position at the entrance of the castle to increase the reliability of the closing of the castle, which ultimately leads to reliability and increase reliability landing gear etc the simultaneous reduction of the dimensions of the compartment of the chassis to accommodate the support in the retracted position. These differences provide a reduction of load on the lock retracted position and reducing the effect of backlash in the lock retracted position in the gaps between the wheels and the chassis compartment. The invention is illustrated by the following drawings: figure 1 is a side view of the support, figure 2 - node I 1, figure 3 - view And figure 2. Bearing landing gear includes a shock absorber 1 (see figure 1)associated with the head plate 2, the braces 3, the folding strut 4 with the lock released position 5, steering device 6, the upper 7 and lower 8 slot-hinges. The axis of the wheel 9 fixed to the lower part 10 of the piston 11 of the shock absorber 1. On the lower part 10 (figure 2, figure 3) is made of lugs 12 for pivotally mounting shaft 13, to which the hinge is connected earring 14, lockable lock the retracted 15 (figure 1). On the shaft 13 (figure 2, figure 3) and the ring 14 is formed lugs 16, 17, respectively, bounding the deviation angle of the shaft 13 and earrings 14 relative to the longitudinal and transverse axes. The shaft 13 is held in one end position (pressed to the eye 12 of the piston 11) by the spring 18. Folding brace 4 (figure 1) pivotally connected to the cylinder 19 housekeeping issue front support, a rod pivotally connected with the head plate 2. Cleaning landing gear of the aircraft is performed in the following sequence: after opening the lock is released position 5 on folding strut 4, the pressure in the hydraulic cylinder 19, a rod which extends with a folding strut and cleaning support. When setting supports to lock the retracted position, the shackle 14 is in the lock 15 and is fixed in the retracted position. At the entrance earrings castle in the retracted 15 earring 14 and the shaft 13 are rotated in their hinges relative to the longitudinal and transverse axes to compensate deviations of the lugs 12 in the setup of the shaft 13 and thus earring 14 occupies the most advantageous position relative to the lock 15. Thus, the proposed design of the landing gear of the aircraft, in which the shackle of the lock retracted position pivotally connected with the shaft, pivotally mounted in the lugs of the lower part of the piston can be rotated in the longitudinal and transverse planes, allows to reduce the load on the lock retracted position and its weight, to reduce the impact of working backlashes in the hinge fitting support and lock the retracted position in the gaps between the bottom compartment of the fuselage and support in the retracted position of the chassis, to increase the reliability of the closing of the lock by providing a rotation earrings in longitudinal and transverse planes, which ultimately leads to durability and increased reliability landing gear of the aircraft. Support the chassis of the plane containing the shock absorber with a piston associated the crossmember braces, folding brace with lock released position and the shackle of the lock retracted position, wherein the lower piston part are formed lugs installed on the shaft, pivotally connected with the earring, the upper part of which is included in the lock retracted position, with the drive shafts, as well as the earring is made stops limiting deviation earrings relative to the longitudinal and transverse axes.
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