Aircraft retractable landing gear |
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IPC classes for russian patent Aircraft retractable landing gear (RU 2415778):
   
 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 / 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
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 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. EFFECT: higher reliability of landing gear operation. 3 cl, 5 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 release-cleaning by rotation about an axis parallel to the longitudinal axis of the fuselage (SU 205716, VS 25/12, 1968; US 3899147, 1975; US 4047681, 1977; US 4063698, 1977; US 5478030, 1995; US 5875994, 1999). The closest analogue of the invention is the chassis of the plane containing the strut, pivotally attached to the hull of the aircraft, the actuator housekeeping issue of the chassis, the hinge coupled with the depreciation stand and the body of the aircraft, wheeled cart, mounted on the frame, a stabilizing strut connecting the trolley with the depreciation stand, with the spring strut is provided with a rigidly attached thereto, a first arm, bogie frame connected with depreciation stand can be rotated around its axis and provided with a second lever rigidly mounted on the frame, which is connected with the first lever of the power cylinder, and the beams are fixedly mounted on the frame, made with the hinges at the ends, each of which is provided with a lever connected to the corresponding beam power cylinder (EN 2099245, VS 25/12, 1997). The above analogues, including the closest, provide for cleaning of the chassis in the recess of the fuselage or wing by turning the strut carries the flax it is attached to the fuselage or wing, which does not allow to vary the location of the chassis relatively niche for cleaning. The objective of the invention is to provide a retractable into the fuselage of the chassis, in which the distance between the posts exceeds the diameter of the fuselage. The problem is solved due to the fact that the chassis contains a strut attached to her head plate, pivotally connected with a thrust housekeeping issue of the chassis, which, in turn, pivotally connected with the drive of a housekeeping issue and fuselage, as well as the mechanism of the reversal of the strut, while in the released position of the chassis spring strut and yoke rigidly fixed plug connection on the nacelle of the engine of the plane, and the mechanism of the reversal of the strut is made in the form located in the oblique plane of the two rods and rockers, hinged on the deadlift housekeeping issue of the chassis, with the first the link mechanism is pivoted one end to the fuselage, and the second on the first shoulder of a rocking chair, a second rod pivoted at one end on the front suspension and the other on the second shoulder, two shoulders rocking. The technical result of the claimed invention is to improve the reliability of the chassis by increasing the distance between the posts, with the landing gear in the retracted position of the chassis is a minimum is the first volume in the fuselage. This result is achieved due to the fact that the spring strut and yoke in a released position rigidly attached to the nacelle, and in the retracted position of the chassis is disconnected from the engine nacelle and is located in a recess of the fuselage of the aircraft. Due to the fact that the spring strut in the process of cleaning the chassis is rotated by a system of rods relative to the thrust housekeeping issue on an angle more than 90° were able to minimize the volume occupied by the landing gear in the retracted position. This embodiment allows, in spite of the great length of the rod housekeeping issue, to fit the chassis into a small volume niche in the fuselage. The invention is illustrated by drawings, which depict: figure 1 is a diagram of a retractable landing gear; figure 2 - the same, lateral view; figure 3 - cross section a-a from figure 2; figure 4 - section b-b from figure 2; figure 5 - General view of the landing gear of the aircraft (landing gear). Retractable gear aircraft, predominantly supersonic contains strut 1, a yoke 2, a bogie 3 associated slot-hinge 4 with stand 1, the rod 5 housekeeping edition chassis, drive cleaning-release 11 and the mechanism of the reversal of the strut. Thrust 5 housekeeping issue of the chassis at one end hinged to the fuselage, and the other pivotally connected to the bracket head plate 2. In addition, thrust 5 pivotally connected with the drive of a housekeeping issue is via the bracket, mounted at a distance from the hinge attachment 5 to the fuselage. In the released position of the chassis spring strut 1 and the yoke 2 is rigidly fixed plug connection 7 on the gondola 6 engine aircraft. The plug connection can be a connection type "ear-finger" or "loop-hook". For example, strut mount can be made in the form of two loops, interacting with the two hooks of the engine nacelle 6, and for beam 2 in the form of one loop to traverse and one hook on the nacelle 6. The mechanism of the reversal of the strut is made in the form lying in the plane located at an angle to the transverse plane of the two rods 8 and 9 and rocking 10, hinged to the bracket thrust 5 housekeeping issue of the chassis. The first thrust mechanism 8 hinged at one end to the fuselage, and the second on the first arm of the rocking chair 10, the second rod 9 is pivoted at one end on the front suspension 1 and the other on the second shoulder, two shoulders rocking 10. The right and left landing gear in the retracted position are located one after the other, which is achieved by the location in the oblique planes of the mechanisms of reversal of the amortization of the uprights, while the elements of the mechanism (rods and rockers) right and left rack 1 lie in parallel planes. The operation is carried out as the way. When cleaning the chassis of the command to disconnect plug connections 7 connecting strut 1 and the yoke 2 with the nacelle. Drive cleaning-release chassis acts on the rod 5, whereupon it is rotated about its hinge mounting to the fuselage together with depreciation the bar 1 and bar 2, while the spring strut is simultaneously deployed at the desired angle relative to the thrust 5 system linkage mechanism of spread. Rocking mechanism 10 pivot strut mounted on deadlift 5, transmits its motion to thrust 8 and 9. As a result, strut affects the total movement from the thrust 5 housekeeping issue of the chassis and from the first thrust mechanism 8 of a turn, rotatable about the axis of its mounting to the fuselage, the reversal of the rack provides a second thrust mechanism 9 of the reversal of the strut, where the total movement of the rod 5 and 8 are transmitted through the rocker 10. The landing gear is in reverse order. 1. Retractable landing gear of the plane containing strut attached to her head plate, pivotally connected with a thrust housekeeping issue of the chassis, which is pivotally connected with the drive of a housekeeping issue and the fuselage, characterized in that it is equipped with the mechanism of reversal of strut made in view is located in the same plane rocking, hinged to pull housekeeping issue of the chassis, and two rods, the first link mechanism is pivoted one end to the fuselage, and the second on the first shoulder of a rocking chair, a second rod pivoted at one end on the front suspension and the other on the second shoulder, two shoulders rocking, thus to lock in the released position, the spring strut and yoke provided with detachable fastening means for rigidly fasten the strut and yoke on the nacelle of the engine of the plane. 2. Retractable landing gear according to claim 1, characterized in that the mechanisms of the spread left and right shock absorbing bars are located in parallel planes. 3. Retractable landing gear according to claim 1, characterized in that the detachable connection of strut and beam with the nacelle of the engine of the plane is made in the form connections "ear-finger" or "loop-hook"for strut mount can be made in the form of two plug connections, and to traverse one.
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