Telescopic element with internal stop to be overcome

FIELD: mechanics.

SUBSTANCE: telescopic element includes cylinder where rod with piston is installed so that it can slide telescopically. The internal stop mechanism is overcome by exceeding the preset effort when rod leans against walls inside the cylinder in the direction of compression. The internal stop mechanism is provided with stopping item, which continues inside the said rode in the open hole and projects behind it. The stopping item is retained on rod by means of pin.

EFFECT: simple design.

4 cl, 1 dwg

 

The technical field to which the invention relates.

The invention relates to a telescopic element to overcome the internal focus

The level of technology

There are various telescopic elements, in which retracted position is determined by the internal focusing, for example, the device power drive or chassis shock absorber for an aircraft.

In the specific case of shock absorbers is often necessary to determine the focus, while reducing the length of the shock absorber, such as the shock absorbers are also used to hide the chassis, the internal focus determines the retracted position of the chassis.

However, in the case of a hard landing stroke defined by the emphasis, may be shorter than the stroke required for energy absorption during landing.

Known telescopic elements that have overcome emphasis. In particular, it is known to use parts of the fence that is located on the end of the shock absorber, the shock absorber rod rests against it when reaching the stop positions. When the rod is pressed with a force exceeding a preset threshold value, the item of emphasis is given, resulting in the rod receives an extra move beyond its retracted position.

However, such items of emphasis have a complex shape, which enables the removal is, and in connection with distributed production is very difficult to ensure compliance threshold value forming its outlet.

Disclosure of inventions

The purpose of the invention is to create a telescopic element with overcome emphasis of simple type.

To achieve this purpose, the invention provides a telescopic element containing the cylinder in which the piston rod is installed on the piston is installed with the possibility of a telescopic slide, with telescopic element includes means internal focus, overcome in excess of a predetermined effort, when the rod rests against the inside of the cylinder in the direction of reduction. In accordance with the invention, the means of internal focus contains the detail emphasis, continuing into the open hole on the inside of the stem and protruding from it, with the item of focus is kept on the stock studs.

Thus, when the rod abuts against the stop in the direction of reduction with a force greater than the threshold value of shear studs, the stud is released, and the detail emphasis is pushed into the hole of the stem, providing, thus, the possibility of additional movement of the rod in the direction of shortening. Force, leading to the shear stud, can be easily controlled, resulting in a force will be much better defined than is atalah stops of the prior art.

Brief description of drawings

These and other aspects of the invention will be more understandable only in the light of the attached drawing, which shows a view in section of the shock absorber in a specific embodiment of the invention, which embodies the function extension/retraction and which is shown in its extended position.

The implementation of the invention

Illustrated here, the invention is directed to a shock absorber used for the main chassis of the helicopter of this type, which contains a swinging beam, fixed hinge directly on the fuselage of the helicopter, with this shock absorber is designed for connection setup between the oscillating beam and the hinge point of the suspension on the fuselage.

The absorber contains the master cylinder 1, which has the rod 2 with the possibility of a telescopic slide. To this end, the rod 2 has a sealing piston 3, which slides inside the main cylinder 1 and which forms therein an annular chamber 4 (interrupted by rod 2) and non-interruptible chamber 5 filled with hydraulic fluid, forming a supply of hydraulic fluid. At the ends of the main cylinder 1 and the rod 2 is installed thrust 6, 7 to swivel strut from the fuselage at one end and swing beam chassis at the other end.

The shock absorber has the first auxiliary cylinder 10, rigidly mounted on the main cylinder, for example, as shown in the drawing, by means of fastening screws, with padded between the sealing gasket, closer to the target deadlift 6 of the main cylinder 1. The first auxiliary cylinder 10 continues in the direction essentially perpendicular to the longitudinal axis of the main cylinder 1. The first piston 11 is mounted for sliding seal in the first auxiliary cylinder 10 and divides the internal space in the first pneumatic chamber 12 filled with gas under pressure and the first chamber 13 with the liquid chamber connected with uninterrupted chamber 5 of the main cylinder 1 through the first element 14 of the throttle valve.

The shock absorber has a second auxiliary cylinder 20 rigidly mounted on the main cylinder, for example, as shown in the drawing, by means of fastening screws, with the installation between the sealing strip, in close proximity to the end of the deadlift 6 of the main cylinder 1. The second auxiliary cylinder 20 continues on the other side of the main cylinder 1, on substantially the same axis as the first auxiliary cylinder 10. The second piston 21 is mounted slidable seal within the second auxiliary cylinder 20 so that it divides the space inside the second pneumatic Cam is ru 22, filled with gas under pressure and a second chamber 23 with the liquid, which communicates with uninterrupted chamber 5 of the main cylinder 1 through the second element 24 of the throttle valve.

The elements 14 and 24 of the throttle valve is well known to experts in the field of technology, and therefore they are not described in detail here.

Connection for fluid flow between non-interruptible chamber 5 and the auxiliary cylinders 10 and 20 in this example is made as simple as possible, since the auxiliary cylinders directly communicate with uninterrupted camera 5 through the elements 14, 24 of the throttle valve located in the inlet holes in the auxiliary cylinders, eliminating the extra pipelines.

The first pneumatic chamber 12 is inflated to a first pressure, while the second pneumatic chamber 22 is inflated to a second pressure that is greater than the first pressure. Usually the first pneumatic chamber 12 is inflated to 20 bar, while the second pneumatic chamber 22 is pumped up to 80 bar.

During landing, the shock absorber operates in the following manner. Under the action of drive power from the swinging beams, which seeks to shorten the shock absorber, the piston rod 2 stalkivaetsja in the main cylinder 1, squeezing, thus, the hydraulic fluid contained in a non-interruptible chamber 5, the AK, that it flows through the first and second elements 14, 24 of the throttle valve, filling the first and second chambers 13, 23 hydraulic fluid, pushing back, thus, the first and second pistons 11, 21, which compresses the gas contained in the first and second pneumatic chambers 12, 22.

In normal conditions the annular chamber 4 is connected via a first controlled valve 30 with a supply of hydraulic fluid or hydraulic tank of the aircraft (not shown) is typically under pressure of approximately 5 bar, resulting in the annular chamber 4 is consistently filled with hydraulic fluid as the piston rod 2 is pushed inward, which eliminates cavitation.

When the helicopter takes off, the gas under pressure in the pneumatic chambers 12, 22, pushes back the hydraulic fluid contained in the chambers 13 and 23 for the fluid through the elements 14 and 24 of the throttle valve in the direction of uninterrupted camera 5, pushing, thus, the spindle 2 in the direction of its extended position. The hydraulic fluid contained in the annular chamber 4, is pushed back to the source of hydraulic fluid contained under pressure of the aircraft.

Because the pneumatic chamber, thus, are located next to the main cylinder, shock absorber in the result has a length l in extended position, which, in particular, is compact.

In a particular aspect of the invention, the shock absorber is designed so that it provides the possibility of retracting the swinging of the beam to reduce its aerodynamic drag during flight. With this purpose, a controlled reduction of the shock absorber is organized as follows. Hydraulic fluid under high pressure (usually 206 bar) is injected in the annular chamber 4 through the first controlled valve 30, causing the piston rod 2 is removed in the main cylinder 1. At the same time the second controlled valve 31 allows uninterrupted connection chamber 5 so that it communicates with the cylinder 40 so that the hydraulic fluid contained in a non-interruptible chamber 5 may be removed in the above-mentioned cylinder 40. Hydraulic fluid entering the cylinder 40, pushes back the piston 41 mounted slidable in the cylinder 40, which, in turn, pushes back the hydraulic fluid present under the piston 41 in the direction of the liquid source of the aircraft. You can see that the hydraulic fluid from the uninterrupted camera 5 is not mixed with the hydraulic fluid of the aircraft. When the rod 2 is adjacent to the terminal wall of the main cylinder 1, the first controlled valve 30 is closed so what Braz, what hydraulic fluid present in the annular chamber 4, is held, as captured in it that prevents the elongation of the shock absorber.

You can see that during such retraction, there is no pumping pneumatic chambers 12 and 22, because the pressure is higher than the pressure in the cylinder 40 (essentially the same as the pressure in the tank, that is, 5 bar), resulting in hydraulic fluid preferably enters the cylinder 40.

To secure repayment of the strut in its extended position sufficient to open the first controlled valve 30 for translating the annular chamber 4 in the state in which it communicates with the source of fluid of the aircraft, and at the same time to open a second controlled valve 31, when he was secreto essence, the same pressure is then present on both sides of the piston 3, and due to the difference in cross section between the annular chamber 4 and uninterrupted camera 5 spindle extends out, and the shock absorber is extended until such time as he shall return to the position shown in the drawing.

In accordance with the invention, the absorber is made with the possibility of additional elongation in the case of particularly hard landing. To this end, the rod 2 includes a hollow hole-facing side of the piston 3, while in the bore of the rod 2 is set to detail the 50 stops, so it is out of stock 2. Item 50 lock is held on the rod by means of studs 51. Item 50 focus has an end wall, and a sealing gasket 52 is located between the rod 2 and part 50 of emphasis, providing, thus, the isolation holes in stock from non-interruptible camera 5.

When the shock absorber is used to remove the chassis, item 50 stops adjacent to the target wall 53 of the main cylinder 1, determining the result stenothoe the position of the shock absorber. When the shock absorber is used to absorb shock when replanting, item 50 focus usually does not come into contact with the end 53 of the main cylinder 1. However, during some hard landings item 50 of emphasis not only can get in contact with end wall 53, but the energy that is required to absorb, may be such that such contact will not be sufficient to stop the contraction of the shock absorber. In accordance with the invention, the pin 51 is designed so that it is cut in case of exceeding a predetermined threshold value of force for the purpose, first of all, the absorption of the excess energy during landing due to the rupture of studs 51, and also to allow for more movement of the RAM 2 in the main cylinder 1 with additional pumping pneumatic chambers 12, 22, which also contributes to poglasheniju of the excess energy during landing.

When you break the studs during its cutoff part 50 of the stop is pushed in the direction towards the bottom part of the hole in the shaft 2, resulting in item 50 of the emphasis is no longer interacts with the sealing gasket 52. The hydraulic fluid contained in a non-interruptible chamber 5, then can (slowly) to flow between the element 52 of the stop and the wall of the bore in the piston rod 2, emerging through the outlet 54 located in the bottom part of the stem, thereby reducing the high pressure present in the absorber in the excess of his pumping.

You can see that in normal conditions the presence of the outlet 54 causes the risk messages annular chamber 4 with the external air. To exclude any of the air mixing with the hydraulic fluid of the aircraft between the cylinder 1 and the rod 2 has a seal floating piston 55 so that the flow of hydraulic fluid through the first controlled valve 30 is below the floating piston 55, while the air entering through the exhaust hole 54 may fill only the space between the floating piston 55 and piston 3 of the rod 2. There is no risk of contamination of the hydraulic fluid aircraft external air.

The invention is not limited to the above description, but on the contrary covers l the specific options within the volume, defined by the claims.

In particular, although the invention presented here in relation to the shock absorber used for the main chassis of the helicopter of this type, which includes a swinging beam, directly pivotally mounted on the fuselage of the helicopter, the damper hinge is mounted between the rocking beam and the hinge point of the suspension on the fuselage, the invention is not limited to a chassis of this type; for example, it can also be applied to the chassis of the direct type, in which the strut forms the main cylinder 1 and the wheel (s) mounted directly on the shaft 2.

Although the auxiliary cylinders is shown directly attached to the main cylinder, resulting in the elements of the throttle valve located in the inlet of the auxiliary cylinder, an auxiliary cylinder can be located in another place. For example, they can be mounted on the sides of the main cylinder parallel to it, while the auxiliary cylinders are connected to the main cylinder through connection for a fluid flow, for example, using rigid pipe. It is also possible to fasten the auxiliary cylinders in the wheel housing of the aircraft, but aircraft will be required to provide additional medium spans the VA connection. In such conditions it is necessary to provide connections for fluid flow from the flexible hose or hose, which is able to operate in conditions of the movements of the shock absorber relative to the hose. In all such cases it is preferable to position the elements of the throttle valve in the inlet connection for fluid flow, resulting in such compounds and auxiliary cylinders are not subjected to high pressure, expressed in non-interruptible chamber 5 during contraction of the shock absorber.

Although the present description relates to a shock absorber having two pneumatic chambers, of course, the invention can be used in shock absorbers, having at least one pneumatic chamber, or, on the contrary, having more than two pneumatic chambers.

Finally, although the specific location of the element 50 in the hole of the rod 2 with fixing it by using studs is illustrated here for a shock absorber, this arrangement, in General, applicable to any type of device made in the form of a telescopic cylinder.

1. Telescopic element containing the cylinder in which the piston rod is installed on the piston is installed with the possibility of a telescopic slide, with telescopic element includes means internal focus, overcome in excess of a predetermined effort, when he who rests in the inside of the cylinder in the direction of reduction, which means internal focus contains the detail emphasis, continuing into the open hole on the inside of the stem and protruding from it, with the item of focus is kept on the stock studs.

2. The element according to claim 1, in which the item of emphasis includes an end wall, and a sealing gasket is located between the stem and part of the focus for the isolation holes stem from non-interruptible camera telescopic element extending beyond the limits of the piston.

3. The element according to claim 2, in which the stem includes a communication hole in the rod with the surrounding air.

4. The element according to claim 2, in which the annular chamber telescopic element is a floating piston ongoing between the rod and the cylinder to separate the section of the ring chamber which communicates with the hydraulic circuit fluid from the section of the ring chamber, which continues between the floating piston and the piston rod.



 

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