Aircraft retractable landing gear |
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IPC classes for russian patent Aircraft retractable landing gear (RU 2415777):
 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.
 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.
 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.
 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.
 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
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: transport. SUBSTANCE: 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. EFFECT: simplified design of landing gear. 2 dwg
The invention relates to the field of aviation technology and relates to retractable landing gear. In the prior art there are known various constructions of the chassis with the mechanism of the reversal of the truck, minimizing the volume occupied by the landing gear in the retracted position. In particular, it is the chassis that contains the rack with folding strut, wheel cart with a heel bumper, pivotally connected with the bar by means of a lever, while the chassis is equipped with the mechanism of reversal of the truck, consisting of the bottom of the swing and the top two shoulders rocking, interconnected thrust. The top two shoulders rocking hinged at the front and one shoulder connected with a thrust, and another shoulder thrust through connected to the lower rocking (EN 2088478, VS 25/10, 1997). It is also known retractable landing gear, located on the fuselage of the aircraft and contains wheeled cart, stand with shock absorber and lift-brace, rocker arm wheeled truck pivotally connected to the axis of the cylinder rack, which in turn contains the rocking associated with tie rods with lever mounted on the specified axis, and with the fuselage of the aircraft at a point beyond the pivot point of the mounting rack, the axis of which is inclined to the earth's surface and to the plane of symmetry of the aircraft toward the front of the latter. In the process of cleaning the chassis of the wheeled cart and stand make a rotation around the axis of the cylinder and hinge attaching the stand to the fuselage, respectively at an angle of about 90° each, and the lock spins is due to the location on the same line of the axes of rotation of the rocking rod connecting the latter with the lever, and due to the locking mechanism or lift strut (EN 305633, VS 25/10, 1971). Also known chassis design with the mechanism of the reversal of the truck, minimizing the volume occupied by the landing gear in the retracted position, is described in U.S. patent US 4170332, US 4422602, US 6349901. The closest analogue of the invention is the design of the chassis with the mechanism of the reversal of the truck for U.S. patent US 3951361, 244/102R, VS 25/10, 1976 Chassis contains a rack, folding strut and rod, pivotally connected with the fuselage and system rocking-pull wheeled trolley. Rod, hinged to the fuselage, the system rocking-craving hour and provide rotation of the wheel truck while cleaning the chassis. The disadvantages of the known devices, including the nearest analogue is their structural complexity. The objective of the invention is to simplify the design with the minimum volume occupied by the landing gear in the retracted position. The problem is solved due to the fact that in the claimed invention, containing rack (holder), fixed p the means of the hinge fitting on the fuselage and pivotally connected with the folding strut, connected to the actuator landing gear retraction, wheel cart, the front of the absorber, as well as the mechanism of the reversal of the wheel trucks with traction, which is articulated one end fixed to the fuselage, and the other is connected with the cylinder of the shock absorber, while the link mechanism of the reversal of the wheel of the truck is connected to the cylinder of the shock absorber through the ring with lever, with the ring installed on the front of the damper rotatably connected with the upper link slot-hinge, and a lever rigidly mounted on the ring and the free end pivotally connected to the thrust mechanism of the reversal of the wheel of the truck. The technical result from the use of the claimed invention is to simplify the design of the chassis with the minimum volume occupied by the landing gear in the retracted position. The invention is illustrated by drawings, where: 1 shows a chassis, side view; figure 2 - the same, front view. Retractable landing gear system includes a rack (holder) 1, hinged by hinge fitting 2 on the fuselage, a bogie 3, the folding strut 4, the actuator housekeeping issue 9, the shock absorber 5 and the mechanism of the reversal of the wheel of the truck. The absorber 5 is rigidly connected with the stand 1. Hour 1 has a hinge 8, whereby it is connected with the folding strut 4, the other end of the folding strut mounted on fu elage can be rotated. When cleaning the chassis design is as follows. Under the action of drive cleaning-landing gear strut (yoke) 1 is rotated in the hinge fitting, while the link mechanism of turn of the wheel of the truck 6, hinged to the fuselage, through the lever 7 and the ring 10 rotates cart 3. This chassis design provides a consolidation of the landing gear on the power elements of the fuselage remote layout considerations from the location of released rack, which is determined by the position of the center of gravity of the aircraft in landing configuration. The chassis is removed in a limited space, that contains the elements of the sample rack that allows you to reduce the volume of the aircraft intended for the landing gear. Retractable landing gear of the plane containing the rack, secured by hinge fitting on the fuselage and pivotally connected with the folding strut connected to the actuator landing gear retraction, wheel cart, the front of the absorber, as well as the mechanism of the reversal of the wheel trucks with traction, which is articulated one end fixed to the fuselage, and the other is connected with the cylinder of the shock absorber, characterized in that the link mechanism of the reversal of the wheel of the truck is connected to the cylinder of the shock absorber through the ring with lever and ring set is on the front of the damper rotatably connected with the upper link slot-hinge, and a lever rigidly mounted on the ring and the free end pivotally connected to the thrust mechanism of the reversal of the wheel truck.
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