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Lock the retracted chassis |
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IPC classes for russian patent Lock the retracted chassis (RU 2076827):
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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(57) Abstract: 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. Lock the retracted chassis includes a housing consisting of two interconnected cheeks 1, the hook 2, the power cylinder 3, the elastic element 4. The castle is equipped with a two-tier mechanism, the upper link 5 which is made in the form of two shoulders of the lever pivotally connected to one arm, with the end of the elastic element 4, and the other with the hook 2. 1 C.p. f-crystals, 2 Il. The invention relates to mechanical engineering and can be used for securing cargo or structures up to a height of the state, in particular in an aircraft, for fixing the landing gear of aircraft in the retracted position. The famous castle suspension nose gear of the aircraft Tu-154, comprising a housing consisting of two cheeks, a hook with a roller pivotally mounted between the cheeks, a power cylinder, a spring and a latch pivoted between the jaws and pivotally connected with the rod of the hydraulic cylinder, the mechanism end off the-42-3154, M. 1978). The castle is rather bulky and heavy (2,40 kg). It has a latch to lock the hook in the closed position, which is made of shaped groove, into which put a roller mounted on the lever hook. Despite the fact that rolling friction is much less sliding friction (compared to other locks with latch) still have the possibility of jamming of the hook when opening or closing as a result of deformation structures in the harvesting and production of chassis. Additionally, the presence of the latches locks of similar design, which itself should be fixed by the action of the spring in position is an element of unreliability. Also known castle of the retracted landing gear Yak-42, comprising a housing consisting of two cheeks, a hook pivotally mounted between the jaws, a latch pivoted on the housing and pivotally connected to the hook by means of a spring cylinder, hydraulic cylinder, spring and lever for manual opening mechanism limit switches. (See The operation manual of the Yak-42, section 32.10.06, Fig.1, pages 1-2, 1982. publication of the Saratov aviation plant). Castle bulky, has a large mass (3,03 kg). The presence of design is sirvydas in the closed position of the hook spring cylinder reduces the reliability of the castle, because it is possible jamming of the sliding surfaces or the hook is released upon failure of the spring cylinder. Technical result achieved in the implementation of the invention is to improve reliability and reduce the weight of the structure of the castle. This technical result is achieved by the fact that the castle retracted position of the chassis, comprising a housing consisting of two connected between the cheeks, a hook pivotally mounted between the cheeks, power cylinder, the elastic element is equipped with a two-tier mechanism, the upper part of which is made in the form of two shoulders of the lever, hinged to the casing and pivotally connected to one arm, with the end of the elastic element, the other end of which is pivotally attached to the housing with the other arm, with the lower link of a two-tier mechanism, which other end pivotally connected to the hook, the lower link of the two-tier mechanism in the closed position cruch is with the adjacent shoulder of the upper link of the kinematic castle, in addition, on one shoulder top managers set the roller in contact with the piston rod of the power cylinder, and on the other shoulder done restrictive emphasis. The hinges on the lower level of the TLD is the s chassis; in Fig.2 is a kinematic diagram of the lock retracted position of the chassis. Castle retracted position of the chassis is a hydro-mechanical device. Its design is shown in Fig.1 in the closed position of the hook. The lock includes a housing consisting of two interconnected cheeks 1 (front cheek removed, the hook 2, pivotally mounted between the cheeks, the power cylinder 3, the elastic element 4, hinged at one end on the housing and consisting of a spring rod and a pivoting bearing, two-tier mechanism, the upper link 5 which is a two shoulders lever pivoted on the housing between the jaws and pivotally connected to one arm with the other end of the elastic element 4, the other arm, with the lower link mechanism 6, which is the other end pivotally connected to the hook 2. The lower link 6, in the closed position, the hook has with the adjacent shoulder of the upper link 5 of the deflection "C" (Fig.2), forming a kinematic castle. Cheeks 1 lock body are parallel and are connected by bolts, which at the same time still attach the power cylinder 3, and a bolt pivotally securing the hook 2. Cheeks 1 the body is a smart mouth "And" to sign pendant earrings Patsy each other by means of bolts passing through holes in these lugs when installing the lock on the frame. The hook 2 to ensure closure has a lever "B". On the shoulder of the upper link 5, connected to the lower link mechanism 6 is installed roller 7 in contact with the piston rod of the power cylinder 3, and on the other shoulder done restrictive emphasis "In" contact with the open position of the hook, with the reference area "G" housing of the power cylinder. On the axis of the lever 5 has a shank "D" with a groove for the drive mechanism of the limit switches. The case of the power cylinder 3 has fittings "E" and "F" for the main system cleaning-release chassis and fitting "And" emergency release system. Lock the retracted chassis operates as follows. Starting position:the landing gear down; the castle is open, the lever "B" of the hook 2 is located in the opening of the throat "And" cheeks 1 lock case (Fig.1 the position of the hook is shown by a thin line); the piston rod of the power cylinder is released and rests on the roller 7 of the upper link 5; the emphasis In the" upper link 5 is in contact with the base platform of the "G" housing of the power cylinder 3; fittings "E", "W" and "And" the case of the power cylinder is communicated with the drain line cleaning systems and landing gear. Lock under the action of mechanical pendant earrings landing gear. When submitting davanloo cylinder 3 castle is draining the working fluid. Ubinas, chassis support its hanging earring is included in the guide Zev "And" cheeks 1 lock, push the lever "B" of the hook 2 and rotates the hook, which, through the link 6 two-tier mechanism rotates the upper part (lever) 5. Spring elastic element 4 is compressed, the emphasis In the" upper link 5 moves away from the supporting point "G" housing of the power cylinder 3. Elastic element with shoulder top level are "dead position" (when the longitudinal axis of the lever arm and the elastic element are on the same line). Further, under the action of earrings landing gear and springs of the elastic element 4 upper part 5 continues to unfold 3 (and the time from the spring force increases instantly). Another lever arm 5 operates its roller 7 on the piston rod of the power cylinder during rotation and utaplivaet it into the housing of the power cylinder. By this time hanging earring landing gear fully engages and rests in mouth "And" cheeks 1, and the other lever arm 5 and the lower link mechanism 6 are "dead position", i.e. their longitudinal axis be on one line. Spring elastic element 4 puts them in this position, bring the rod of the power cylinder 4 until it stops inside the case. The hook 2 and, consequently, the lock is closed. Thus the longitudinal tx2"> Thus, the hook 2 is fixed in the closed position kinematically. It really is so because under the weight of the chassis earring support, acting on the hook 2 down, creates a moment, unwrapping it with respect to its hinge mounting clockwise. In the link 6 two-tier mechanism creates a compressive force due to the deflection of attempts to deploy the upper part (two shoulders lever) 5 counterclockwise. But the lever 5 abuts against the roller 7 in the piston rod of the power cylinder 3, which is recessed into the chassis until it stops. Under the influence of the weight of the landing gear is like "Samosata" hook lock. The opening of the lock occurs when the supply pressure of the working fluid into the socket "W" body of the power cylinder 3. The cylinder rod is retracted presses the roller 7 and rotates the upper link 5. The elastic element 4 is compressed, its longitudinal axis with the longitudinal axis of the shoulder of the upper link are "dead" position (when they lie on the same line), the emphasis In" the top link is the anchor space "G" housing of the power cylinder 3. The lower link 6 and the adjacent shoulder of the upper link 5 go through the "dead" position and release the hook 2 will cast the Assi. The castle is open. After the piston rod of the power cylinder has been fully opened access to the working fluid pressure of the main hydraulic system to the fitting "E" housing of the power cylinder 3 (by design of the cylinder) and then by pipeline to the cylinder cleaning-release chassis pressure alarm system is served in the socket And the power cylinder 3 and the hydraulic cylinder cleaning-release chassis. Castle opens in the same way. 1. Lock the retracted chassis, comprising a housing consisting of two interconnected cheeks, a hook pivotally mounted between the cheeks, a power cylinder, an elastic element, characterized in that it is equipped dusmanim mechanism, the upper part of which is made in the form of two shoulders of the lever, hinged to the casing and pivotally connected to one arm, with the end of the elastic element, the other end of which is pivotally attached to the housing and the other arm lower link dvuhzvennuju mechanism, which other end pivotally connected to the hook, the lower link dvuhzvennuju mechanism in the closed position, the hook is adjacent the shoulder of the upper link of the kinematic castle, in addition, on one shoulder top link is the first stop. 2. Castle under item 1, characterized in that the hinges on the lower level of dvuhzvennuju mechanism is made spherical.
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