Retractable chassis support aircraft |
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IPC classes for russian patent Retractable chassis support aircraft (RU 2183179):
  
 The shock absorber / 2182876
The invention relates to the field of engineering to the field of cushioning protection, machines and other objects, allowing a limited degree of mechanical loads
 Sealing the node pneumatic-hydraulic shock absorber cylinder and rod / 2167082
The invention relates to the field of engineering
 Sealing the node shock absorber / 2162047
The invention relates to the field of mechanical engineering
 Bearing skid chassis or skid the tail bearing (options) and cartridge device to it / 2144489
The invention relates to skid chassis or tail supports
 Double shock absorber / 2081031
The invention relates to shock absorbers chassis aircraft and can be used in the suspension systems of land and water transport
 The shock absorber chassis of the aircraft and the method of filling the hydraulic chamber of the shock absorber chassis of the aircraft / 2057687
The invention relates to aircraft and is intended for use as a shock absorber sessile aircraft /L. a./
 The shock absorber chassis of the aircraft / 2051073
The invention relates to aeronautical engineering, namely for a landing aircraft devices
 A hydropneumatic shock absorber / 2043946
The invention relates to aeronautical engineering, chassis shock absorber aircraft
 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.
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(57) Abstract: The invention relates to coupling devices for aircraft. Retractable chassis support aircraft includes a lever, a supporting wheel mounted on the fuselage, the cylinder housekeeping issue 4 locks retracted position 11 and a released position 12, the cavity C and D which are connected with the hydraulic system of the aircraft, and remote gatherplace the absorber 5, a housing 6 which is connected to the lever. In the housing 6 of the shock absorber 5 is slidably mounted one end of the rod 7. The other end of the rod 7 with the piston installed in the housing 10 of the cylinder 4. The cavity 9 in the rod 7 is filled with a gas and performs the function of the gas chamber of the shock absorber 5. The hydraulic cylinder equipped with a plunger 13, one end of which is rigidly fixed in the housing 10, and the other free end through a seal is installed in the cavity 9 can move and change the volume of the gas chamber of the shock absorber. The invention is directed to reduction of size and weight. 4 Il. The invention relates to aeronautical engineering, namely for a landing device for aircraft. Known retractable bearing chassis containing the lever with the wheel (or the fifth), semimoist which are connected with the hydraulic system of the aircraft with mechanical lock released position. In the retracted position of the chassis is held by the locked hydraulic pressure from the hydraulic system (pilot-operated check valve). The body of the shock absorber is connected with the lever, and a rod pivotally connected to a rod of the hydraulic cylinder housekeeping issue and link installed on the fuselage. (See "Guidelines for the technical operation of the helicopter MI-26. General view of the tail support (32.70.00) Fig. 1., developed by the Moscow helicopter plant. M. L. Mil (JSC cost center) in 1985). The presence of known construction joints and additional links required for folding and cleaning landing gear, increase the size and weight of the landing device. To eliminate these disadvantages in the known landing gear of the aircraft, containing the lever with the wheel, hinged to the fuselage, the cylinder housekeeping issue with the locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft and the remote gatherplace damper housing which is connected to the lever, and the rod with the rod of the hydraulic cylinder, the damper rod is made as a unit with the rod of the hydraulic cylinder, forming a cavity in which is located a gas chamber of the shock absorber, in addition, the hydraulic cylinder is equipped with the congestion. The implementation of the shock absorber rod and the rod of the hydraulic cylinder as a whole provides the location of the units in the support coaxially and sequentially one after another. In addition, compared with the known bearing design reduces the total stroke of the rod of the shock absorber S Amort. and cylinder S cyl., as the course of a single stock S stock is used first for production (harvesting) of the chassis, and then the same course S stem is used for absorption of normalized loads during landing of the aircraft. Execution units with a single stem allows to reduce the dimensions of support, excluding additional links and pivot nodes, to reduce its weight. Formed cavity in a single stock, within which they can move installed the plunger cylinder is charged with compressed gas and performs the function of the gas chamber of the shock absorber at planting and pre-owned aircraft. This design of the gas chamber allows for cleaning of the chassis by moving a single rod relative to the plunger to increase the charging pressure in the absorber, thus the accumulated energy of the gas used in the production of chassis. It also reduces haberma landing gear. In Fig. 2 - noobify gatherplace the shock absorber with hydraulic cylinder in the extended position the support. In Fig.3 - compressed gatherplace the shock absorber with hydraulic cylinder in the extended position the support. In Fig. 4 - noobify gatherplace the shock absorber with hydraulic cylinder in the retracted position of the support and the compressed gas chamber. Bearing chassis contains the lever 1, a supporting wheel 2 fixed to the fuselage (Fig. 1 not shown) by means of the hinge 3, the hydraulic cylinder housekeeping issue 4 and gatherplace the absorber 5 located coaxially and sequentially to the hydraulic cylinder 4. In the housing 6 of the shock absorber 5 is slidably mounted one end of the rod 7 in the cavity of which is placed a piston 8, the limiting hydraulic chamber of the absorber A. the Other end of the rod 7 with the piston installed in the housing 10 of the cylinder 4, forming the hydraulic chamber C and D associated with the hydraulic system of the aircraft. The cavity 9 in the rod 7 located above the piston 8, is filled through a charger gas and performs the function of the gas chamber "B" of the shock absorber 5. The cylinder 4 is provided with a collet locks retracted position 11 and a released position 12 and a plunger 13, one end of which is rigidly Zack the steps In" shock absorber 4, can move relative to the rod 7. On the mode of takeoff and landing rod 7 in a released position locked mechanical lock from moving relative to the housing 10 and the piston 13 of the hydraulic cylinder 4. Therefore, the impact energy takes the shock absorber 5 (see Fig.2, 3). When cleaning the landing gear in the recess of the fuselage is supplied hydraulic pressure system of the aircraft into the chamber With the cylinder 4. Showdown castle 12 released position and the moving rod 7 relative to the body 10 of the cylinder 4 to the setting of the castle retracted position 11. When the rod 7 remains stationary relative to the housing 6 of the shock absorber 5 and the plunger 13 of the hydraulic cylinder 4 moves within the cavity 9 of the gas chamber, reducing its volume and accumulating the energy of compressed gas used in the production of the chassis (see Fig.4). Minor in the production of landing gear hydraulic pressure supplied to the cavity "D" of the cylinder 4, opens the lock 11 and the shaft 7 under the action of the energy of compressed gas, is moved relative to the housing 10 to the setting of the castle 12 released position landing gear. The proposed design of the landing gear because of its compactness, the lack of an articulated connection of the STS, and provides high quality, stability and reliability of all its units. Retractable bearing chassis of the aircraft, containing the lever with the wheel, hinged to the fuselage, the cylinder housekeeping issue with the locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft, and remote gatherplace damper housing which is connected to the lever, and the rod - rod hydraulic cylinder, characterized in that the damper rod is made as a unit with the rod of the hydraulic cylinder, forming a cavity in which is located a gas chamber of the shock absorber, in addition, a hydraulic cylinder provided with a plunger mounted within the cavity for movement and changes in the volume of the gas chamber of the shock absorber.
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