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Aircraft undercarriage with balance beam and deforming parallelogram Invention relates to aircraft engineering. Undercarriage comprises prop and two connecting links. Said prop comprises caisson with lower end with which articulated is the balance beam fitted thereat by means of king pin. Damper is arranged balance beam and caisson. Every connecting link has parallel axes of turn. Every connecting link is articulated with aircraft airframe and with said prop in parallel axes. Note here that one of said links is articulated with said prop by the pin extending through the end of balance beam king pin connected with caisson. |
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Aircraft retractable landing gear leg This leg comprises lever with wheel articulated with fuselage, extending shock absorber, leg retract-release cylinder, retracted-released position locks, link with one end coupled with gimbal articulated with fuselage and another end with shock absorber. Shock absorber rod is articulated with lever. Said retracted-released position locks are made integral and composed of interarticulated flexible link with retainer and pawl with roller arranged to swing from lock open cylinder arranged inside said link. Pawl roller is arranged to contact with release-retracted position grooves made in shock absorber lug. |
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Aircraft undercarriage with hollow structural member Invention relates to aircraft undercarriage with hollow structural member. The undercarriage includes longitudinal load-bearing member which represents diagonal truss member. Longitudinal structural member is hollow and contains nonbearing member located inside it. |
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Aircraft retractable landing gear Invention relates to a landing gear of an aircraft (A) and concerns a retractable landing gear. The retractable landing gear of the aircraft contains a stationary leg fastened to a hull, a depreciation leg, a cart with a wheel pair, a hinged connection, a lever spatial mechanism locking the mechanisms fixing positions of links in respect to stationary and mobile legs. The lever mechanism is capable to adopt the flat position - preset in motion by the engine. The lever spatial mechanism is designed comprising of six links which are connected to each other by hinges forming only rotary kinematic pairs. Four links are implemented in the form of rods with identical parameters, with identical distances between axes of the hinges and identical angles of crossing equal to 90° and connected to each other in series with a possibility of overlapping of points of the ends of the shortest distances between the axes of the hinges of the first and second links. Meanwhile one of the links is implemented as the driving one and is connected only to a single engine. |
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Aircraft retractable undercarriage strut Invention relates to aircraft (AC) alighting gears and concerns retractable undercarriage designs. Ac retractable undercarriage strut contains lever with wheel gimbal-mounted on fuselage, gear centring hydraulic cylinder with locks of extended and retracted position, where cylinder chambers are connected with AC hydraulic system, and gas-hydraulic shock-absorber one end of which is pivotally connected with the lever and the other - with fuselage. Hydraulic cylinder and shock-absorber are made articulated. Rods of hydraulic cylinder and shock-absorber are installed coaxially being capable to reciprocate relative to each other and to from cavities in one of which gas chamber is located and in the other liquid chamber is located. Hydraulic cylinder is provided with accumulating cavity with dividing piston and mechanical lock the elements of which are made capable to fix dividing piston in extended position and to contact with lock of retracted position. |
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Device and method for operation of aircraft undercarriage retraction-release drive Proposed device comprises leg with wheels arranged on its axle fitted in the main support secured in wheel well and leg lever rigidly secured at leg top end and electromechanical liner drive (EMLD) of leg turn about its axle. EDLD case and case-to-drive support joint secured in wheel well make a rotary pair. EMLD case houses the motor, screw mechanism to convert motor shaft rotation in extending link translation, said link interacting with said lever. Note here that said extending links make the contact pair with leg lever that had the contact uncoupling area. EMLD incorporates the mechanism for directing of extending link to leg lever to maintain the contact between said leg and said lever at EMLD case turn in undercarriage operation. Said directing mechanism makes the rotary kinematic pair with leg lever that feature one degree of freedom. In operation, extending link is pulled from the lever to diagnostics position. Before motor operation EMLD serviceability is tested. For this motor is switched on to vary extending link motion direction within the limits of its diagnostics range. In case EMLD serviceability is confirmed, extending link is moved to contact with the lever and motor is switched off. |
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Aircraft retractable landing gear (versions) Landing gear comprises lever with wheel articulated with fuselage, aligned hydraulic cylinder of landing gear in/out drive with locks of in/out positions, cylinder chambers being communicated with aircraft hydraulic system and has-hydraulic damper. The latter allows its chamber to be filled with working fluids via common charging union without their separation and is arranged in hydraulic cylinder chamber to make the pair “pipe-in-pipe” to act as hydraulic cylinder rod. Said hydraulic cylinder is equipped with high-pressure gas chamber composed by damper rod, piston fitted therein to interact with damper rod and extra fixed journal-box. |
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Device for landing gear unlocking in extended position and landing gear equipped with such device Aircraft (AC) landing gear contains leg pivotally mounted on AC, capable to rotate around retraction axis. The leg can be stabilised in extended position by means of brace containing two pivotally interconnected connecting rods and can be held in aligned position by stabilising element containing two pivotally interconnected links. One of the links is pivotally connected with brace, and the second link is pivotally connected with landing gear leg or with AC. The links are held in their aligned and locked position. The landing gear contains unlocking device. The unlocking device contains rotary drive, crank lever, lever pivotally mounted on the crank lever end and comprising recess, pin, returning device pressing lever to the pin. Drive axis is parallel to pivot of stabilising element links. The crank lever is connected with rotary drive shaft. The pin is rigidly fixed to one of stabilising element links and protrudes from this link. The crank lever is made capable to be shifted from the first angular position where the pin contacts with the lever being opposite the recess when links are in aligned position, to the second angular position to which the lever comes when lever recess thrusts away the pin thus bringing the stabilising element links out of aligned position. |
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Invention relates to aircraft undercarriage retractable NLG, particularly to three-wheel undercarriage. NLG comprises nacelle, leg and extension mechanism. In the case of tail-first configuration, NLG hinge makes the sleeve fitted on front horizontal fin axle. Undercarriage can have nacelle solely for NLG wheel. Note here that NLG is arranged inside the fuselage recess between NLG hinge and wheel nacelle. Besides, NLG can be arranged outside the fuselage, nearby it between NLG hinge and wheel nacelle. Every hinged flap of the wheel nacelle is articulated with the lever arranged said nacelle to contact with said wheel. Besides, every said articulated flap can be engaged with the lever fitted on the same hinge and engaged with said flap by contracting spring while stroke limiter is arranged between said flap and lever. |
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Device to decrease aircraft undercarriage length 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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Aircraft landing gear with folding brace stabiliser release 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. |
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Aircraft landing gear with, at least, one noise killer 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. |
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Aircraft retractable landing gear 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. |
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Aircraft retractable landing gear 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. |
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Aircraft retractable landing gear 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. |
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Main landing gear of aircraft chassis 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. |
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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. |
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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. |
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Aircraft landing gear main leg 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. |
Another patent 2550842.