Aircraft retractable undercarriage strut

FIELD: transport.

SUBSTANCE: 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.

EFFECT: reduced quantity of assembly units for attachment to AC due to execution of combined aggregate - shock-absorber - hoist, reduced structural dimensions and weight.

4 cl, 5 dwg

The invention relates to a landing device for aircraft, in particular to the design features retractable landing gear.

The prior art retractable chassis support aircraft (hereinafter - LA), containing the lever with the wheel, hinged to the fuselage, cylinder cleaning-release collet locks released and retracted, the cavity of which is connected with the hydraulic system of the aircraft by means of hydraulic locks, and remote gatherplace damper housing which is pivotally connected with the lever. In the damper casing movably mounted one end of the rod. The other end of the rod with a piston is installed in the housing of the hydraulic cylinder. The stem cavity filled with gas and performs the function of the gas chamber of the shock absorber. The hydraulic cylinder equipped with a plunger, one end of which is rigidly fixed in the housing, and the other, free end, by means of seals installed in the cavity of the piston rod can move and change the volume of the gas chamber of the shock absorber (patent RF №2183179, IPC B64C 25/10, B64C 25/58, publ. 10.06.2002).

In a known construction for cleaning-release chassis uses two-way hydraulic cylinder including a housing, the piston forming two hydraulic chambers associated with the hydraulic system LA through hidrotambo and the plunger. In addition, the stem hydration the RA is the shock absorber rod, therefore, it is exposed to significant stress during operation of the shock absorber, which causes the need for installation in hydraulic collet locks, prevents movement of the rod relative to the housing cylinder during landing and landing runway of the aircraft. This leads to an increase in the weight and size of the landing gear.

Also known retractable bearing chassis LA-containing arm with a wheel, hinged to the fuselage, remote gatherplace the shock absorber cylinder housekeeping issue, the stem of which is made stepwise, and the cylinder has a locking valve cut (RF patent No. 2245823, IPC B64C 25/22 from 07.04.2003, publ. 10.02.2005). In the known design is the emphasis of the rod at the maximum compression of the shock absorber that allows to compress the shock absorber is a rough landing more than the calculated damping stroke. For compression of the shock absorber on the harvesting process by hydraulic aircraft will require considerable effort caused by the nonlinear increase efforts on the shock absorber from its course, and as a consequence separating piston and the lift will have a significant size and weight.

This technical solution is adopted as a prototype for the claimed invention.

The present invention is the task - to create a combined unit that provides cleaning the poles production is from the hydraulic system of the aircraft, depreciation loadings in the released position, regardless of the hydraulic system of the aircraft.

The task underlying the present invention is solved in that in a retractable 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 gatherplace the shock absorber, one end of which is pivotally connected to the lever, and the other with the fuselage, the hydraulic cylinder and shock absorber made of articulated rods of the hydraulic cylinder and shock absorber is installed coaxially with the possibility of reciprocating movement relative to each other and the formation of cavities, one of which is a gas chamber, and the other liquid chamber, and the hydraulic cylinder is equipped with a cumulative cavity with separating piston and a mechanical lock, the elements of which are made with the possibility of fixing the separating piston in the extended position and into contact with the lock retracted position.

In addition, the separating piston is made with the possibility of formation of two hydraulic chambers, one of which is connected with the hydraulic system of the aircraft, and the other is a hydraulic chamber of the shock absorber.

In addition, castle FM the data provision is made in the form of crackers elements.

In addition, a mechanical lock consists of rings and piston on the outer surface of which is placed associated screw connection spring-loaded language and emphasis.

Technical result achieved in the implementation of the present invention is to expand the functionality of landing gear of the aircraft, and this bearing chassis requires a minimum number of nodes connected to LA due to the fact that depreciation and hydraulically are combined aggregate - shock-absorber-lift, while the internal layout of the latter allows you to place the landing gear into the smallest possible size while reducing the weight of the latter.

Perform hydraulic cylinder and shock absorber articulated and installation of the rod of the hydraulic cylinder and shock absorber coaxial with the possibility of reciprocating movement relative to each other, as well as the supply cylinder cumulative cavity with a dividing piston and additional lock allow for these movements as at depreciation and while cleaning-release support, allowing lengthwise dimension of the proposed design is much smaller.

These characteristics are essential and interrelated with the formation of stable essential prize is akov, sufficient to obtain the technical result.

The comparative analysis of proposed technical solutions to identified analogues of the prior art from which the invention not obvious to a person skilled in the field of landing device for aircraft, has shown that it is not known, and given opportunities for industrial mass production retractable landing gear for aircraft, the conclusion can be made about its compliance with the criteria of patentability.

The present invention is illustrated with a specific example of implementation of the proposed retractable landing gear for aircraft, which demonstrates the ability to obtain the technical result. Allowed various modifications and improvements that are not beyond the scope of the invention defined by the attached claims.

Presents a variant of the invention is described hereinafter based on the drawings, where:

- Fig.1 is a diagram of a retractable landing gear LA;

- Fig.2 shows a General view of the shock absorber-lift in neobiota state;

- Fig.3 shows a General view of the shock absorber lift, compressed at full stroke and amortization;

- Fig.4 shows a General view of the shock absorber lift in the retracted position;

- Fig.5 shows the opening of the lock removed on the ogene.

Graphic materials relevant structural elements of a retractable landing gear LA is indicated by the following positions:

1 - wheel;

2 - lever;

3 - shock absorber-lift;

4 - stock;

5 - cylinder;

6 - fixed Buchs;

7 - mobile (floating) Buchs;

8 - crumbs;

9 - separating piston;

10 is a piston lock;

11 - language;

12 - snap ring;

13 - emphasis;

14 - the piston;

15 - spring;

16 - stock;

17 - cumulative Luggage;

18 - gas (nitrogen) Luggage;

19 - liquid chamber;

20 - liquid chamber;

21 - liquid chamber;

22 - charging fitting;

23 - jellied tube;

24 - fitting issue;

25 - fitting;

26 - the fitting of the lock.

Retractable chassis support aircraft contains the lever 2 with the wheel 1, 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 gatherplace damper (shock absorber-lift) 3, one end of which is pivotally connected to the lever 2 and the other with the fuselage. The proposed design of the unit is combined and acts as a shock absorber and lift due to the coupling of the hydraulic cylinder and shock absorber and install a rod coaxial with the possibility of reciprocating what about moving relative to each other and the formation of cavities, one of which is a gas chamber 18, and the other liquid chamber, and the cylinder is equipped with a cumulative oral camera 17 with a dividing piston 9 and a mechanical lock, the elements of which are made with the possibility of fixing the separating piston in the extended position and into contact with the lock retracted position (crackers 8). Gas (nitrogen) camera 18 is formed by the inner surfaces of the stops 13 and piston 14, the charging chamber 18 is made through the charging socket 22. Liquid chamber 19 formed by the inner surfaces of the cylinder 5, the dividing piston 9 and the floating panel Jack 7, the fill chamber 19 is made through the filler tube 23. The camera 20 is connected to the hydraulic system LA through the nozzle cleaning 25, formed by the inner surfaces of the cylinder 5, a floating panel Jack 7 and 6 panel Jack. The camera 21 is connected to the hydraulic system LA through the fitting of the lock 26, formed by the inner surfaces of the cylinder and piston 10 a mechanical lock.

In this regard, his work is possible in two modes: shock absorber and lift, in each mode of operation of the components involved are stock 4 cylinder 5, Buchs 6, the piston 14, the piston rod 16 or items such as Buchs 7, crackers 8, the tongue 11, the spring 15, the stop 13, the ring 12, the separator piston 9, the piston 10 a mechanical lock.

Shock-lift 3 consists of a rod 4 that is installed in C is lindre 5 using a fixed axle boxes 6 and overlays, located on the rod, and the rod 16 within which moves a piston 14, which separates the gas chamber 18 from the liquid chamber 19. Hold the rod in the retracted position is accomplished by crackers 8 and parts mechanical lock: language 11, the spring 15, the stop 13, spring ring 12 and the piston 10, with the tongue 11 and the stop 13 are connected by a threaded connection and spring-loaded by a spring 15. Changing the internal volume of the absorber-lift 3 when cleaning bearings is due to the movement of the separating piston 9. When the shock absorber is lift 3-mode shock absorber separating piston 9 is at the castle, which is based on the ring 12.

Retractable chassis support aircraft operates as follows.

The operation mode of the shock absorber

In this mode, the separating piston 9 is in its extreme position and secured with a spring ring 12, which is locked by the tongue 11 (which is structurally designed as a sleeve with a chamfer, and is used for the lock in the absence of pressure in the hydraulic system) under the action of the spring 15. The spring ring 12 is slit and in the absence of external loads is compressed to a position where its outer diameter is less than the reciprocal of the internal diameter of the separating piston 9. Language 11, under the action of the spring 15, always tries to decompress reginae ring 12, however, this is prevented by the separating piston 9. Once the groove is made on the inner surface of the separating piston 9 will coincide with spring ring 12, the latter under the action of the spring 15 is dispersed and fixed in a language 11. When the movement of the movable rod Bush 7 is pressed against the stationary buochs 6 pressure in the absorber. When the absorption of the work of the damper is moving rod 4 within the cylinder 5 and the piston 14 within the shaft 16, which is structurally designed in the form of a pipe, the inner surface of which moves the piston 14, causing compression of the gas chamber 18. When the compression of the damper to the full stroke of the rod 4 becomes the focus, which is structurally skirt dividing piston 9.

The unit is in the mode of lift

When cleaning the landing gear in the LA gondola, the hydraulic pressure is supplied into the chamber 21 through the fitting of the lock 26, moves the piston 10 a mechanical lock (structurally, the piston 10 is made in the form of a body of rotation, with one side containing a skirt with seals, and on the other thread) and language 11 (structurally, the piston 10 and the tongue 11 are connected by a thread and when the pressure on the piston 10 of the castle is moving both elements, as a whole), while the compressed spring 15, is released and compressed spring ring 12. Under tastieristico internal pressure in the absorber separating piston 9 begins to move in the direction of increasing the cavity of the shock absorber, displacing from the camera 17, the liquid in the hydraulic system of the AIRCRAFT, which after opening the lock of the piston by means of the electrohydraulic valve chamber 17 through the nozzle 24 issue connected with the drain line of the hydraulic system. Into the chamber 20 through the nozzle cleaning is pressure from the hydraulic system, floating Buchs 7 under the action of pressure in the chamber 20 will begin to move in the direction of compression of the shock absorber together with the rod 4 to the position until the crumbs 8 will not fall into the groove of the lock retracted and will not lock the retracted position in the following sequence: crackers 8, located on the rod 4, which is mixed under pressure in the chamber 20, at the end of the rod abuts the tongue 11, compressing the spring 15 to the position until the crumbs 8 will not fall into the groove of the castle, made on the cylinder 5, then the tongue 11 under the action of the spring 15 will move under crackers 8 and will close the lock.

The proposed layout of the retractable support and shock absorber-lift chassis allows you to reduce the size and weight of support due to the fact that the internal elements of the shock absorber lift, such as the stem 4 and the cylinder of the shock absorber 5, participate in the work of depreciation and while cleaning-release support. The change of the course of cleaning and working depreciation (stroke when cleaning bearings exceeds the stroke of the shock absorber-lift prirate depreciation) in the absorber-lift is due to the movement of the separating piston 9 and changes the internal volume of the chambers of the shock absorber, resulting in greatly reduced longitudinal dimension of the absorber-lift.

Sample offer retractable landing gear LA was developed on the basis of a detailed experimental investigation of the design and process of its work.

Manufacturer offer retractable landing gear LA does not require the development of new equipment and retrofitting of existing facilities, and the used tools are widely used in the aviation industry, which confirms the possibility of practical implementation and achievement of the technical result.

1. 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 gatherplace the shock absorber, one end of which is pivotally connected to the lever, and the other with the fuselage, characterized in that the hydraulic cylinder and shock absorber made of articulated rods of the hydraulic cylinder and shock absorber is installed coaxially with the possibility of reciprocating movement relative to each other and the formation of cavities, one of which is a gas chamber, and the other liquid chamber, when this cylinder is equipped with a cumulative cavity with section who sustained fashion piston and a mechanical lock, items which are executed with the fixing of the separating piston in the extended position and into contact with the lock retracted position.

2. Reliance on p. 1, characterized in that the separating piston is arranged to form the two hydraulic chambers, one of which is connected with the hydraulic system of the aircraft, and the other is a hydraulic chamber of the shock absorber.

3. Reliance on p. 1, characterized in that the lock removed provisions made in the form of crackers elements.

4. Reliance on p. 1, characterized in that the mechanical lock consists of rings and piston on the outer surface of which is placed associated screw connection spring-loaded language and emphasis.