Aircraft alighting gear shock absorber

FIELD: transport.

SUBSTANCE: invention relates to aircraft alighting gear shock absorber. Proposed shock absorber comprises two elements 1 and 2 telescoping to constrict inner chamber filled with working fluid and gas and divided into two chambers 7 and 8 by diaphragm 5. Said diaphragm comprises bypass opening 10 for working fluid to flow from one chamber into another. Bypass opening 10 has gas discharge hole 22 for gas to flow from one chamber into another when alighting gear is in operating conditions. Said hole 22 is displaced in height relative to bypass opening 10 and located above it when alighting gear is in operating conditions.

EFFECT: fast return of fluid into rated position corresponding to landing.

5 cl, 3 dwg

 

The technical field to which the invention relates.

The invention relates to a shock absorber landing chassis with quick bypass of fluid.

The level of technology

Dampers landing chassis contain different chambers separated the various walls or partitions with overflow holes. These chambers are filled with fluid and compressed gas. When the chassis is in the working position, the absorber, usually located essentially vertically, so by the difference in densities of the gas in the absorber at the top and working fluid at the bottom.

However, when the chassis is in the retracted position in the bottom compartment of the aircraft, the working fluid and the gas is gradually distributed in different chambers of the shock absorber, passing through the bypass holes. In particular, the gas is partially fills the chamber called oil chamber under the partition called the diaphragm, partition the inner space of the shock absorber. When the landing gear before landing transferred to the working position, the working fluid and the compressed gas is moved, gradually returning to its original state, passing through the bypass holes. However, this return to the initial state can be quite long, so it happens that flying is part lands, when the working fluid is not fully filled below the aperture of the oil chamber.

Disclosure of inventions

The objective of the invention is to provide a shock absorber, providing a rapid return fluid (oil or gas) in its normal position for landing, which is located under the diaphragm chamber filled with working fluid.

This problem is solved in the shock of the landing chassis of the aircraft, containing two elements telescopically installed slidable in each other and bounding an internal volume filled with the working liquid and gas and is divided into at least two chambers by a partition with at least one overflow opening through which the working fluid can move from one cell to another, in particular, during compression of the shock absorber. According to the invention in the partition has at least one hole for removal of gas, ensuring the transfer of gas from one chamber to another when the chassis is in the working position, the opening to the gas outlet is offset in height relative to the overflow drain and is above it in the working position of the chassis.

The working fluid, which remains above the partition and which should go under the wall under the action of the silts of gravity, maybe in this case pass through the bypass hole or through hole for exhaust gas. However, the pressure of the liquid at the level of the overflow drain exceeds the fluid pressure at the level of the holes for the exhaust gas due to the difference in height. Therefore, the liquid takes place mainly through the bypass hole, whereas under the wall of the gas takes place mainly through the hole for the exhaust gas. This specialization of holes provides a much faster bypass fluid, substantially reducing the time to return to the nominal position, in which the camera under the wall, filled only with fluid.

Brief description of drawings

Figure 1 shows a shock absorber landing gear nominal position of the landing, a view in section;

figure 2 shows the position of the fluid within the shock absorber shown in figure 1, immediately after the release of the chassis, look at the context;

figure 3 shows the diaphragm and the column, which is equipped with the shock absorber shown in figure 2 and 3, perspective view.

The implementation of the invention

As shown in figure 1, the shock absorber includes a stand 1, which is telescopically mounted slidable rod 2. Hour 1 and rod 2 limit of a primary volume 3 and the annular chamber 4, while their volume is changing when moving rod 2 in the casing 1

The partition or diaphragm 5, mounted on the plunger tube 6, divides the main volume 3 into two chambers: an oil chamber 7 under the diaphragm 5, and a limited stock 2, and the air chamber 8 located above the diaphragm 5.

The inner space of the shock absorber is filled with fluid (shown by horizontal strokes) and gas (shown by dots). The working fluid fills the oil chamber 7, an annular chamber 4 and a part of the air chamber 8. The rest of the air chamber 8 is filled with a compressed gas.

During compression of the shock absorber portion of the working fluid flows through the bypass holes 10 in the diaphragm 5 from the oil chamber 7 to the air chamber 8. At the same time, the working fluid passes through the bypass holes 11 in the rod 2 from the air chamber 8 in the annular chamber 4.

With the expansion of the shock absorber place back move. For this purpose, the bypass holes 10 and 11 is closed by the valves 12 and 13, limiting their diameter and regulating the rate of expansion of the shock absorber.

According to the invention the diaphragm 5 are hollow column 20, in this case, the center serving up to the air chamber 8 (when the chassis is in position and ready for landing, as shown in the drawing). Column 20 is significantly to the air chamber 8 and at its upper end C is Kanivets wall 21 with a hole 22 for removal of gas, the section which is less than the cross section of the bypass holes.

As shown in figure 3, the diaphragm 5 has a Central internal thread 30, which is screwed into the lower threaded end 23 of the column 20. In this case, the column 20 contains an annular shoulder 24 to hold the valve 12 between the annular shoulder 24 and the socket 31 of the diaphragm 5, between which the valve 12 is moved vertically under the action of flow of the working fluid passing through the bypass holes 10.

Next, with reference to figure 2 will be described the operation of the device.

Figure 2 shows a state of shock immediately after the release of the chassis. Chassis is in the retracted position at an angle, typically comprising from 80 to 110, sometimes within a few hours, and fluids (oil or gas) in time to be distributed throughout the absorber, the gas is above the working fluid. During the release of the chassis under the diaphragm 5, the gas remains in the oil chamber 7 and it will take some time before he returned to the air chamber 8.

In this case, between the bypass holes 10 and the opening 22 for exhaust gas, there is a height difference h, therefore, the fluid pressure at the level of the overflow holes 10 slightly above the pressure level of the hole 22 for removal of the gas.

This small pressure difference promotes the flow of the working liquid is t through the bypass holes 10, what causes gas to pass mainly through the hole 22 for removal of the gas. The tests showed that the time of bypass fluid and gas is considerably reduced compared to the shock absorber, not containing offset adjustment holes for exhaust gas, while the gain in time can be up to several minutes.

Preferably the height of the column count so that the hole for the exhaust gas remained immersed in the working fluid, even when it completely fills the oil chamber 7, as shown in figure 1.

The present invention is not limited to the above option, but encompasses all variants that are not beyond the scope of the protection defined by the claims.

In particular, although it was stated that the partition is equipped with a column, is the aperture of the absorber column in accordance with the invention, it is possible to equip any other partition, such as partition between the air chamber 8 and the annular chamber 4.

Of course, you can perform several holes for exhaust gas in one or more columns. Shown in the figures, the location of the column in the center is not required and the column can be positioned elsewhere on the partition.

Finally, although shown separately made and installed to the of PMC, you can, of course, similarly, to perform a partition of the column in the form of a single part with at least one opening for venting gas, offset in height in such a way as to be above the overflow hole or overflow holes when the landing chassis is in the released position. In the case of execution of the two parts can also set a column on the wall using any known means, for example by welding or connection with the nut.

1. The shock of the landing chassis of the aircraft, containing two elements (1, 2), telescopically installed slidable in each other and bounding an internal volume filled with the working liquid and gas and is divided into at least two chambers (7, 8) partition (5) with at least one overflow opening (10)through which the working fluid can move from one cell to another, in particular, during compression of the shock absorber, characterized in that the dividing wall (5) has at least one hole for exhaust gas ensuring the transfer of gas from one chamber to another when the chassis is in the working position, the opening to the gas outlet is offset in height relative to the overflow drain and is above it in the working position of the chassis.

2. Amortize the PRS according to claim 1, characterized in that the hole for the exhaust gas is made at the upper end of the hollow column (20), located on the wall and communicated with the chamber (7)located under the partition (5).

3. The shock absorber according to claim 2, characterized in that column is no partition (5) and contains an annular shoulder (24)holding the movable valve (12)that communicates with an overflow opening (10) of the partition (5).

4. The shock absorber according to claim 3, characterized in that the column is connected to the wall by threaded connection.

5. The shock absorber according to claim 1, characterized in that the hole for the gas outlet is at such a height to remain immersed in the working fluid, even when located under the baffle chamber is completely filled with the working fluid.



 

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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.

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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

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FIELD: transport.

SUBSTANCE: invention relates to aircraft alighting gear shock absorber. Proposed shock absorber comprises two elements 1 and 2 telescoping to constrict inner chamber filled with working fluid and gas and divided into two chambers 7 and 8 by diaphragm 5. Said diaphragm comprises bypass opening 10 for working fluid to flow from one chamber into another. Bypass opening 10 has gas discharge hole 22 for gas to flow from one chamber into another when alighting gear is in operating conditions. Said hole 22 is displaced in height relative to bypass opening 10 and located above it when alighting gear is in operating conditions.

EFFECT: fast return of fluid into rated position corresponding to landing.

5 cl, 3 dwg

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