Aircraft landing gear main leg |
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IPC classes for russian patent Aircraft landing gear main leg (RU 2297366):
      
 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: alighting gears for flying vehicles. SUBSTANCE: 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. EFFECT: reduced dimensions of leg, avoidance of bending load on member; reduced load on down lock; reduced mass of leg. 3 dwg
The invention relates to aeronautical engineering, namely to boarding devices aircraft and, in particular, to a retractable main landing gear. Known retractable main support chassis of the plane containing the lever with the wheel, hinged to the fuselage, remote gatherplace unit, including gatherplace the shock absorber, cylinder cleaning-release bearings, collet locks retracted and released positions of support, pivotally connected with the lever and the fuselage (See. patent RU 2183179, CL VS 25/10, 25/58). The combination of known construction gothicrainbow shock absorber, cylinder cleaning-release bearings, collet locks retracted and released positions of support leads to an increase in the length of the unit as a whole, because the stroke of the hydraulic cylinder cleaning-release support in such a considerably longer stroke shock absorber, which defines the length of a conventional shock absorber, in addition, such a design is impossible visual inspection of the work and condition of the collet locks retracted and released positions of support, which reduces the reliability of locks, it is impossible to associate with the locking elements of locks actuators limit switches, signals which are used to indicate the closed and open position castles, as well as for other chassis systems. The combination of the aggregate functions and the of ordinator, cylinder cleaning-release locks retracted and released positions reduces the reliability of the unit as a whole, affects its operational adaptability, as failures in included in the Assembly of the shock absorber, cylinder locks retracted and released positions of support lead to removal from service expensive unit as a whole. It is also known multisupport chassis, consisting of several independent supports, arranged one after the other. Each support includes a lever with a wheel pivoted on the beam, still installed on the fuselage, remote gatherplace damper housing which ends with the eye, the hinge is attached to the lever, and a rod pivotally connected to the bottom eyelet of the link that the other eye pivotally attached to the beam, cylinder cleaning-release support, pivotally connected with the beam and the parts of the mechanism cleaning-release support, lock mechanism released position of the tower (See. patent FR 2702446, CL VS 25/34, 25/22), while in the released position, the support link is kept locking mechanism in a stationary position. When the shock absorber link also remains motionless. For reasons that impede the achievement of specified following technical result is that such a shock mount to link increases the size and weight od the market, in addition, when the shock absorber link remains stationary while the damper is rotated relative to the link (the longitudinal axis of the shock absorber and link form an angle), and the link is loaded with a bending moment transmitted also the locking mechanism that holds the link in a fixed position, which leads to increased size and weight support. The objective of the invention is to remedy these disadvantages, namely the reduction of the dimensions of the supports, the exception loading level bending stress, improve working conditions the locking mechanism is released position of support, weight loss support. This object is achieved in that the main landing gear of the aircraft, containing the lever with the wheel, hinged to the fuselage, remote gatherplace the shock absorber, the piston rod of which is pivotally connected to the lever, the lock released position, the lock retracted position, mounted on the fuselage, earring lock retracted position, pivotally mounted on the lever, cylinder cleaning-release support, according to the invention the housing of the shock absorber in the middle part of the hinge attached to is made in the form of a fork link connected to the other end of the hinge through the eyelets shaft mounted articulated on the fuselage, with the lock released position posted on this the same star is e, and earring lock released position pivotally mounted on the upper housing of the shock absorber, and in a released position supports the shock absorber lock released position is fixed relative to the link so that the longitudinal axis of the link and the shock absorber are the same, and when cleaning support the shock absorber in the joint of the suspension to the link pivots relative to the link. The invention is illustrated by drawings, where figure 1 - General view of the main landing gear; figure 2 is a front view of figure 1; figure 3 - General view multisupport chassis. Bearing holds the lever 1 with the wheel 2, pivotally mounted on the fuselage 3, remote gatherplace the shock absorber 4, a rod 5 which is hinged to the lever 1 and the housing through a pin 6 located in the Central part of the body, pivotally connected with made in the form of a fork element 7 connected to the other end of the hinge shaft 8, mounted articulated on the fuselage, the lock released position 9 mounted on the link 7, earring lock released position 10, pivotally connected with the upper part of the body of the shock absorber lock retracted position 11 mounted on the fuselage, earring lock the retracted 12, pivotally mounted on the lever 1, the hydraulic cylinder cleaning-release bearing 13, pivotally connected with the fuselage and link. Multisupport chassis consists of several before agemy by the applicant supports. The support works as follows. In the released position, the damper 4 is fixed stationary relative to the link 7 with the lock released position 9, is placed on the link, and earring lock released position 10, hinged to the upper part of the body of the shock absorber. During the movement of aircraft on the airfield when the lever 1, the shock absorber rod 4 is moved, and the shock absorber 4, together with the link 7 is rotated about the axis of the hinge mounting shaft 8 to the fuselage. The longitudinal axis of the shock absorber 4 and level 7 when released position always support, including when the shock absorber, are on the same line (same). Due to this, the lock released position 9 is effective minimum load. During cleaning support opens the lock released position 9, is released earring lock released position 10, and when the pressure in the hydraulic cylinder cleaning-release bearing 13 link 7 is rotated, carrying with it the shock absorber 4, the lever 1 with the wheel 2. In the retracted position of the bearing can be locked retracted position 11. The release process is in reverse order. Thus, the proposed design retractable main landing gear of the aircraft, in which the lever with the wheel hinged to the fuselage, remote gatherplace damper rod ball the IRNA is connected with the lever, and a hinge in the middle part of the body of the shock absorber is associated with made in the form of a fork element, in a released position located along the strut, the other end pivotally connected with a shaft mounted articulated on the fuselage, the lock released position is set on the link, earring lock released position pivotally mounted on the upper housing of the shock absorber lock the retracted installed on the fuselage, earring lock retracted position pivotally mounted on the lever, cylinder cleaning-release support hinged to the fuselage and the link that allows you to reduce the dimensions of the bearing, to exclude the loading of the link bending stress, reduce the load on the lock released position and support to reduce the weight of support. The main support chassis of the aircraft, containing the lever with the wheel, hinged to the fuselage, remote gatherplace the shock absorber, the piston rod of which is pivotally connected to the lever, the lock released position, the lock retracted position, mounted on the fuselage, earring lock released position, the shackle of the lock retracted position, pivotally mounted on the lever, cylinder cleaning-release support, characterized in that the damper casing in the middle part of the hinge attached to is made in the form of a fork link connected to the other end of the ball of the IRNA through eyelets shaft, mounted articulated on the fuselage, with the lock released position posted on the same link, and earring lock released position pivotally mounted on the upper housing of the shock absorber.
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