Drive cleaning and landing gear of the aircraft

IPC classes for russian patent Drive cleaning and landing gear of the aircraft (RU 2085445):

B64C25/10 - retractable, foldable, or the like

Another patents in same IPC classes:

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.

(57) Abstract:

Usage: the invention can be used for cleaning and release of the chassis in the creation of new and modernization of existing aircraft. The essence of the invention: drive contains the command lever to be mounted in the cockpit of the aircraft, and mechanical gear is mounted on the rack chassis. The command lever is mechanically connected to the input shaft of the gearbox. The actuator additionally introduced flat aerodynamic surface mounted on the front of the chassis between the axis of rotation of the rack and wheel chassis for rotation relative to the landing gear and the output shaft of the gearbox is mechanically connected with this aerodynamic surface. 2 Il.

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.

Known drive cleaning and landing gear of the aircraft, containing the command lever to be mounted in the cockpit of the aircraft, and mechanical gear is mounted on the front chassis, and the command lever is mechanically connected with the output of the Wales considerable muscular effort and much time to create a pilot at release and cleaning the chassis, that may distract the attention of the pilot and to degrade flight safety of the aircraft during production and cleaning of the chassis. Extension and retraction of the chassis is carried out by the muscular effort of the pilot, attached to the command lever. In flight of the aircraft occur inertial and aerodynamic forces acting on the struts and landing gear, and the friction force preventing the production and cleaning of the chassis.

The technical result of the invention is to reduce muscular effort and time of their creation by the pilot in the process of releasing and removing the chassis while maintaining low mass drive cleaning and release of the chassis.

This technical result is achieved that the drive cleaning and landing gear of the aircraft, containing the command lever to be mounted in the cockpit of the aircraft, and mechanical gear is mounted on the front chassis, and the command lever is mechanically connected to the input shaft of the gearbox, added flat aerodynamic surface mounted on the front of the chassis between the axis of rotation of the rack and wheel chassis for rotation relative to the landing gear and the output shaft of the gearbox is mechanically connected with this aeroce chassis; in Fig. 2 the proposed actuator in the retracted position of the landing gear.

Drive cleaning and release of the chassis (see Fig.1) contains the command lever 1 mounted in the cockpit and fixed to the leading roller 2 mounted on the axis 3 with a possibility of rotation relative to the airframe. Leading roller 2 by means of the cable 4 is mechanically connected to the slave roller 5 mounted on the shaft 6, which by means of bearings 7 is installed inside the axis 8 of the rack chassis for rotation about an axis 8 which is installed in the hull for rotation. On the shaft 6 is fixed bevel gear 9, which is engaged with the bevel gear 10, mounted on the shaft 11, is established by means of the bearings 12 of the rack 13 of the chassis for rotation relative to the rack 13, fastened to the axle 8. On the shaft 11 attached the leash 14, through which a fixed finger 15 is connected with an aerodynamic surface 16 that is installed on the rack 13 with the possibility of rotation relative to it. The rack 13 is set as the wheel 17 of the chassis for rotation relative to the rack 13. Gears 9 and 10 form a mechanical gearbox, input shaft which antov actuator in the initial state when released position of the rack 13 of the chassis shown in solid lines (see Fig.1). For cleaning chassis command lever 1 is translated in the position shown by the dotted line (see Fig.1). If this turns leading roller 2. Its rotation through the cable 4 is transmitted to the slave roller 5, the shaft 6 and the pinion gear 9. This also turns the gear 10, the shaft 11 and the lead 14. Through the finger 15, which fits into a hole on the end of the aerodynamic surface 16, this turns aerodynamic surface relative to the rack 13 in the position shown by the dotted line in Fig.1. This aerodynamic surface 16 becomes at an angle of attack relative to the velocity vector of the aircraft, resulting in an aerodynamic surface 16 creates a drag force defined by the expression

where S,C_ythe area of aerodynamic surface 16 and a derivative of angle of attack coefficient C_yof lifting force surface 16;
the density of air;
V the speed of the aircraft.

The power of Y_gshoulder 1 creates a moment M_g
M_gY_g1 (2)
with respect to an axis O_xthe rotation axis 8 of the rack chassis, under which the rack 13 of the chassis is rotated in the direction of cleaning up to retracted position.

The position of the element drive iodide in position, shown by the dotted line in Fig.2. If this turns leading roller 2, the driven roller 5, shaft 6, the gear 9, the gear 10, the shaft 11 (see Fig.1), the lead 14 and the aerodynamic surface 16, which in the rotation will occupy the position shown by the dotted line (see Fig.2). This aerodynamic surface 16 will be in the air stream at an angle of attack of a_inand it creates an aerodynamic force Y_in

which on the shoulder 1 creates a moment M_in
M_inY_in1 (4)
with respect to an axis O_xthe rotation axis 8 of the rack chassis. Under the action of this moment, hour 13 chassis is rotated in the output side of the chassis to the released position of the rack 13.

To assess the performance of the drive cleaning and landing gear were calculated with the following initial data: moment of inertia of the rack 13 with the wheel 17 and the aerodynamic surface 16 with respect to axis O_xthe rotation axis 8 is equal to I_x13 KGM; aerodynamic surface 16 is in terms of square shape with a side 0.2 m; C_y1,5; 1,22 KGM^-3; V=108 km / h^-1=30 MS^-1; l=0.6 m; a_g=_in= 0,3.
When these initial data on the basis of (1) and (3) received
Y_g=Y_in=Y=1,5410^-20,31,22 910²0,5=9, the 13 has the form

where is the angular acceleration of rotation of the rack 13.

Integrating equation (5) we obtain the change in the angle F_articleand the angular velocity of the rack 13 with time t:

Let for the coming of the rack 13 in the retracted position, required turn this rack 90^ofrom the released position. Then for cleaning chassis takes time t_n

and the angular velocity of the rack 13 at the time of joining her in the retracted position will be

The calculations show that the drive cleaning and landing gear at quite small sizes aerodynamic surface 16 provides cleaning and production of chassis for a relatively short time. By choosing an appropriate distance between the axis of rotation of the aerodynamic surface 16 relative to the rack 13 and the point of application of the aerodynamic force Y and the length of the command lever 1 can provide a reasonable effort to command the arm 1 to rotate at harvest and landing gear. While the ratio of transmission from the command lever 1 to the aerodynamic surface 16 can be considered close to 1 and the value of the required angle F_krrotate the command lever 1 will be approximately equal to the value of F_APangle turning parts, all specifications is viewed in the rotation speed of the pilot in command of the lever 1, equal to 54 degrees.c (C. 0,785 S.^-1), the time spent by the pilot in the operation of cleaning or release the chassis will be about 0.4 C. Thus, the proposed actuator allows the pilot to perform cleaning and release of the chassis when creating them a small muscular effort in a short time, and achieves the purpose of the invention.

Drive cleaning and landing gear of the aircraft, containing the command lever to be mounted in the cockpit of the aircraft, and mechanical gear is mounted on the front chassis, and the command lever is mechanically connected to the input shaft of the gearbox, characterized in that it additionally introduced flat aerodynamic surface mounted on the front of the chassis between the axis of rotation of the rack and wheel chassis for rotation relative to the landing gear and the output shaft of the gearbox is mechanically connected with this aerodynamic surface.