Stand of aviation chassis |
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IPC classes for russian patent Stand of aviation chassis (RU 2360835):
 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
 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: transportation. SUBSTANCE: 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. EFFECT: reduced volume occupied by stand in fuselage. 2 dwg
The invention relates to the field of aviation design chassis. The well-known scheme of the chassis [1], it has a trunnion through which are passed to the operating load on the return part of the aircraft structure. These pins are used as elements, a rotation around which the production and cleaning of the chassis, and hence the axle landing gear must be continuously in contact with the response of the power parts of the airframe. A shortcoming of this scheme is the need to build the plane in which the recess for the landing gear in the retracted position is located in strict accordance with the response parts of the airframe in contact with the pins of the chassis, while the location of mates clearly defined reasons, the weight of the aircraft. The invention is aimed at reducing the volume occupied by the counter in the fuselage, in the absence of contact between the response of the power parts of the landing gear and airframe. This is achieved by the fact that the chassis design is introduced guide installed on the carriage and pads, angled, providing braking under the action of the loadings on the traverse, while the carriage is pivotally connected with a rack chassis. 1 shows a chassis, side view; figure 2 is the same, rear view. The chassis consists of the rack 1. To stop the e 1 pivotally mounted hydraulic cylinder 2 and the strut 3, other end connected to the airframe. In the upper part of the stand 1 hinged carriage 4 having the ability to move along the guide 5. Guide 5, which provides the desired trajectory output pads 6 of the contact zone with the response parts of the airframe, installed in the fuselage. Pad 6 attached to traverse the rack 1. Chassis works as follows: when cleaning the chassis, the piston rod of the hydraulic cylinder 2, coracias, causes rotation of the rack 1 around the axis of the hinge fastening with strut 3 and the carriage 4, which in turn performs translational motion along the rail 5, while the contact pads 6 disengage from the mating parts of the airframe. Sources of information 1. Retractable chassis No. 102322 from 11.06.67, France. Hour aviation chassis containing cylinder, strut and yoke, characterized in that the traverse is installed pads deployed at an angle, providing a braking under the action of loadings, and for the trajectory housekeeping issue of the chassis in the Central upper part of the stand is fixed to the carriage.
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