CN102384210B - Aircraft shock absorber with double seal arrangement - Google Patents
Aircraft shock absorber with double seal arrangement Download PDFInfo
- Publication number
- CN102384210B CN102384210B CN201110224547.6A CN201110224547A CN102384210B CN 102384210 B CN102384210 B CN 102384210B CN 201110224547 A CN201110224547 A CN 201110224547A CN 102384210 B CN102384210 B CN 102384210B
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- CN
- China
- Prior art keywords
- seal arrangement
- shock absorber
- sealing device
- component
- aircraft shock
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/60—Oleo legs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/3207—Constructional features
- F16F9/3235—Constructional features of cylinders
- F16F9/325—Constructional features of cylinders for attachment of valve units
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/36—Special sealings, including sealings or guides for piston-rods
- F16F9/369—Sealings for elements other than pistons or piston rods, e.g. valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/43—Filling or drainage arrangements, e.g. for supply of gas
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The present invention relates to a kind of aircraft shock absorber with double seal arrangement, it has at least two tubular components, wherein, described first component has the room with liquid filling in its inside, and wherein, described second component is arranged to, can move in described first component along common longitudinal axis, wherein, described vibration damper has at least two seal arrangements in series arranged along the direction of described common longitudinal axis and at least one bypass line by changing valve cut out between the outer surface and the internal surface of described first component of described second component, described bypass line connects described with the room of liquid filling and the gap between described seal arrangement.
Description
Technical field
The present invention relates to a kind of aircraft shock absorber with double seal arrangement.In the nose landing gear that such vibration damper is such as arranged on aircraft and main landing gear.
Background technique
Known a series of aircraft shock absorber with double seal arrangement in the prior art.DE102004031995A1 illustrates the vibration damper of a type, it comprises and has with the hydraulic damping device of the form of the room of liquid filling and gas spring, accommodate throttle element movably in the chamber, described throttle element moves along with vibration damper motion.
Fig. 1 illustrates the cross section through another aircraft shock absorber with double seal arrangement of the prior art.Described vibration damper has and is formed for the upper end 2 of the tie point of airframe and the lower end 3 that is connected directly or indirectly with wheel shaft.Described vibration damper 1 comprises the outer tube 10 surrounding oil pocket 4.Interior pipe 20 is arranged in described outer tube 10 with one heart, and can move along the longitudinal axis of described vibration damper.When interior pipe 20 or being positioned at other component on pipe or changing in the motion being positioned at other component on pipe of oil pocket in interior pipe 20, realize buffering.
Between described outer tube 10 and described interior pipe 20, there is seal element 30, described seal element is by oil pocket and ambient environment.Described seal element and other comparable seal element in the prior art have according to the backup seal system for the tactical rule SAEARP4912 of SAE (Society of Automotive Engineers) standard of aircraft.
Summary of the invention
The object of the invention is, provide a kind of and there is the seal element of improvement and the aircraft shock absorber with double seal arrangement of spare seal member.
According to the present invention, described object is achieved by a kind of aircraft shock absorber with double seal arrangement.Draw favourable form of implementation in the following description.
Correspondingly, aircraft shock absorber with double seal arrangement is provided with at least two tubular components.First component limit or encirclement are with the room of liquid filling, and second component is arranged to, can in described first component or with the indoor moving of liquid filling.Described second component can move along the common longitudinal axis of two components.According to the present invention, vibration damper have between the outer surface and the internal surface of the first component of second component at least two seal arrangements in series arranged along common longitudinal axis and at least one by changing valve close for being arranged in the bypass line of the hydraulic fluid of the room of liquid filling, described bypass line connects with the room of liquid filling and the gap between seal arrangement, described aircraft shock absorber with double seal arrangement has in addition fills pipeline and/or the liquid-filling valve irrelevant with described changing valve, described filling pipeline is independently used with the position of described changing valve, and independently operate described liquid-filling valve with the position of described changing valve.
In one form, that component is configured to arrange with one heart and be circular when needing or be essentially circular pipe, wherein, the first pipe has than the outer diameter of the second pipe or the slightly large inner diameter of outer perimeter or interior girth.In described form of implementation, the common longitudinal axis of two components is limited by the longitudinal axis of described pipe.
In one form, bypass line is reversibly closed by changing valve.
Liquid is preferably hydraulic fluid, such as hydraulic oil.
In one form, according to the vibration damper that aircraft shock absorber with double seal arrangement of the present invention is for nose landing gear.It is the vibration damper for main landing gear in another form of implementation.
In one form, first or second component of aircraft shock absorber with double seal arrangement are applicable to indirectly or directly be connected with the wheel shaft of aircraft with being given for, and another component is applicable to indirectly or directly be connected with airframe with being given for accordingly.
In one form, the seal arrangement that the direction that vibration damper has the common longitudinal axis in just in time two edges between the outer surface and the internal surface of the first component of second component is in series arranged and/or just what a bypass line of closing by changing valve.
In a preferred form of implementation, the first and/or second seal arrangement is arranged in the gap between the outer surface of second component and the internal surface of the first component, and fully surrounds second component.At this, the first and/or second seal arrangement is preferably fully sealed in the gap between the outer surface of second component and the internal surface of second component.
In another preferred form of implementation, the first and/or second seal arrangement be configured to can around the outer surface of second component or fully around the seal ring of the internal surface of the first component.
In one form, the first and/or second seal arrangement arranges or is fixed on the outer surface of second component.In another form of implementation, the first and/or second seal arrangement arranges or is fixed on the internal surface of the first component.
In one form, two seal arrangements are equivalent seal arrangement.Preferably, two sealing device structures are formed in the same manner.
In one form, when bypass line is opened, outer sealing device is by pressure-loaded.The bypass line opened means the position of having opened of changing valve, makes liquid by described bypass line from flowing into the gap between seal arrangement with the room of liquid filling and can refluxing.In described form of implementation, pressure-loaded is by being achieved from the room of liquid filling and the liquid in gap that comes between self-seal device.
In one form, when bypass line is opened, inner sealing device is pressure balanced.In this article, pressure balance means, described seal arrangement is not be loaded with by liquid applied pressure on side.This can cause thus, is equivalent to the pressure acted on by the gap between seal arrangement by the pressure acted directly on inner sealing device with the room of liquid filling.In described form of implementation, when bypass line is opened, fluid pressure extends to gap from the room being full of hydraulic pressure.
Outer sealing device can be regarded as lower sealing device, and described seal arrangement is compared with another inner sealing device, and the direction along common longitudinal axis is arranged to, and deviates from the head with the room of liquid filling or second component further away from each other.Inner sealing device can be regarded as lower sealing device, and described seal arrangement, compared with another seal arrangement, is arranged to along common longitudinal axis, towards with the room of liquid filling or be positioned at second component head near.From two seal arrangements in working order, the position of that is having installed under state aboard obtain another definition.When the first component indirectly or to be directly connected with airframe and second component and wheel shaft indirectly or be directly connected, inner sealing device is upper sealing device, and outer sealing device is lower sealing device.
In one form, in the buttoned-up situation of bypass line, inner sealing device is by pressure-loaded.In described form of implementation, in the buttoned-up situation of bypass line, do not extending in the gap between seal arrangement with the fluid pressure in the room of liquid filling.Therefore, inner sealing device in side by with the room on-load pressure of liquid filling.
In form of implementation, in the buttoned-up situation of bypass line, outer sealing device is not by pressure-loaded.In described form of implementation, therefore described outer sealing device by means of only the gap between seal arrangement, and is connected with hydraulic fluid by bypass line.Therefore, by closing described bypass line, pressure can be recalled from outer sealing device.
In one form, inner sealing device is secondary seal arrangement or backup seal device, and outer sealing device bears main sealing device.
In one form, when aircraft shock absorber with double seal arrangement normally works, namely in described aircraft shock absorber with double seal arrangement, two damping devices are intact, and described bypass line is opened.Inner sealing device is pressure balanced, and does not perform sealing function.Outer sealing device bears described function completely.If outer sealing device blow-by, so recall pressure by the changing valve be closed in bypass line from outer sealing device.So, described inner sealing device that is intact, that be not loaded so far bears sealing function, until outer sealing device is keeped in repair or changes.
Also can imagine within the scope of this invention, inner sealing device is used as main sealing device, and outer sealing device is used as backup seal device.So, in normal work, bypass line or changing valve are closed, and total hydraulic pressure is on inner sealing device.If described inner sealing device blow-by, so can open hydraulic pipe line, therefore described inner sealing device is able to pressure balance.So, outer backup seal device bears sealing function.
In one form, bypass line and changing valve are arranged in external member or on external member.Described changing valve can be found out by the outer surface of aircraft shock absorber with double seal arrangement or tap into.Preferably, the position of changing valve can externally go out.For this reason, position mark that is coloured or landform can be established, such as indentation.
In one form, changing valve is placed on the valve shell on the outer surface being arranged on the first component.In described form of implementation, preferably also extending in described shell at least partially of bypass line.
Changing valve preferably includes valve pocket, operative pin and valve slider.In one form, changing valve can by the TO of commercial standard (CS) and cut out.At this preferably, described changing valve preferably has the interface for the hexagon wrench of commercial standard (CS), inner hexagon spanner and similar instrument on operative pin.
In addition, in another form of implementation, aircraft shock absorber with double seal arrangement according to the present invention has fills pipeline and/or preferred and that changing valve is irrelevant liquid-filling valve.At this, described liquid-filling valve and/or filling pipeline are used for emptying and fill with the room of liquid filling, and such as by replacing hydraulic medium or change, the fluid pressure in room safeguards shock strut.
In one form, liquid-filling valve is arranged on the valve shell identical with changing valve.In one form, described liquid-filling valve and/or fill pipeline and changing valve and/or bypass line is element of construction.
In one form, independently use filling pipeline with the position of changing valve, and/or independently handle liquid-filling valve with the position of changing valve.In other words, in described form of implementation, filling pipeline and/or liquid-filling valve under the state activated of changing valve, also under the unactivated state of changing valve, namely can work under the state of the opening and closing of bypass line.
In another form of implementation, at least one partial response of bypass line is at least one part of filling pipeline.Another part of bypass line and/or another part of filling pipeline, preferably another part of two pipelines extends respectively separated from each other.Bypass line and filling pipeline lead in common part and are preferably configured to T-shaped.Common part preferably include bypass line from changing valve towards with the part of the room of liquid filling, or in other words, at changing valve with the part between the room of liquid filling.
In one form, at least one part area of filling pipeline extends in the inside of changing valve, extends if possible in the inside of the operative pin of changing valve.In another form of implementation, bypass line and the filling pipeline intercommunication on the seat of changing valve.In this article, valve seat is interpreted as upper/lower positions, and on described position, bypass line is closed by changing valve.
Accompanying drawing explanation
Other details of the present invention and advantage is elaborated by means of embodiment illustrated in the accompanying drawings.Accompanying drawing illustrates:
Fig. 1 illustrates the longitudinal section through aircraft shock absorber with double seal arrangement of the prior art;
Fig. 2 illustrates the longitudinal section in the region related to the present invention according to aircraft shock absorber with double seal arrangement of the present invention be passed on the position of having opened of changing valve;
Fig. 3 illustrates the longitudinal section in the region related to the present invention according to aircraft shock absorber with double seal arrangement of the present invention be passed on the buttoned-up position of changing valve;
Fig. 4 illustrates the external view in the region related to the present invention according to aircraft shock absorber with double seal arrangement of the present invention.
Embodiment
Fig. 2 schematically illustrates the longitudinal section in the region related to the present invention according to aircraft shock absorber with double seal arrangement of the present invention be passed on the position of having opened of changing valve.In addition, shown region comprises the part of the first component 10, the part of second component 20, two seal arrangements 31 and 32, bypass line 5, gap between seal arrangement 6 and changing valve 60.
It is circular pipe that described second component 20 is configured to cross section, and is arranged in the first component 10 with one heart, and it is circular pipe that described first component 10 is configured to cross section equally.Component 10 and 20 has the common longitudinal axis (not shown in FIG.) vertically extended.First component 10 limits or surrounds the room 4 with liquid filling.The unshowned in the drawings position of bypass line 5 is led to described with in the room 4 of liquid filling.
In order to be sealed in the contact area between interior pipe 20 and outer tube 10, described aircraft shock absorber with double seal arrangement has two seal rings 31 and 32.Inner seal ring 32 is the second backup seal device, and outer seal ring 31 is main sealing device.The gap 6 extended in the inner circumferential of pipe 10 is there is between seal ring 31 and 32.Described gap is directly contacted with the room 4 with liquid filling by bypass line 5.
In addition, there is the valve shell 50 comprising changing valve 60.Described valve comprises valve pocket 55, valve slider 63, torsional stop device 64 and operative pin 61.Valve slider 63 is movably received within valve pocket 55.A part for bypass line 5 extends in valve shell 50.
Valve on the position of having opened shown in Figure 2.On the position of having opened of changing valve, liquid can arrive the second portion 5a of bypass line from the first portion 5b of bypass line in the clear, and therefore arrives the gap 6 between seal arrangement 31 and 32 from the room 4 of liquid filling in the clear.Described position is equivalent to the normal work of the aircraft shock absorber with double seal arrangement illustrated.
In normal work, in gap 6, there is the pressure identical with in the room 4 of liquid filling.Therefore, there is identical fluid pressure in the both sides of inner sealing device 32.Described inner sealing device is pressure balanced, and does not bear with the sealing function between the room 4 of liquid filling and the outside of aircraft shock absorber with double seal arrangement.Described sealing function is born by outer sealing device 31 completely, described outer sealing device from gap 6 in side by pressure-loaded.
In addition, there is liquid-filling valve 70 shown in figure 2, described liquid-filling valve is arranged on described valve shell 50 equally.The filling pipeline 75 of reversibly being closed by described liquid-filling valve 70 extends through valve shell 50, valve pocket 55 and valve slider 63, and leads in bypass line 5 at valve seat 65 place.From described valve seat 65, the first portion 5b of bypass line forms the part of filling pipeline 75 simultaneously.
Liquid-filling valve 70 on buttoned-up position shown in the drawings.When liquid-filling valve 70 is opened, from room 4, take out liquid by pipeline 75, or liquid is injected described room 4.
Fig. 3 schematically illustrates the longitudinal section in the region identical with Fig. 2 through aircraft shock absorber with double seal arrangement according to the present invention, but, be on the buttoned-up position of changing valve.
Due to bypass line 5 closing, with the disconnecting between the room 4 of liquid filling and the gap 6 between seal arrangement 31 and 32 in the region of valve seat.Therefore, room 6 and outer seal ring 31 are no longer by pressure-loaded.Therefore, inner seal ring 32 directly loads fluid pressure by room 4 on side, and is no longer pressure balanced, because no longer there is pressure in described gap 6.Sealing function is born by inner sealing device 31 completely.Described position is equivalent to the standby operation of the aircraft shock absorber with double seal arrangement illustrated.
In normal work (Fig. 2), total pressure acts on outer seal ring 31, and inner seal ring 32 is pressure balanced, and is not worn.Now, if outer seal ring 31 blow-by, so can close described valve 60 (Fig. 3), therefore, backup seal device 32 fully can bear sealing function, until main sealing device 31 is replaced.
The filling illustrated by means of liquid-filling valve 70 and the composition graphs 2 of filling pipeline 75 of room 4 or air emptying function also remain unchanged in standby operation.Fluid pipeline 75 is on the buttoned-up position of valve 60, and on the position of having opened of also valve 60, at valve seat 65, place is led in the first portion of bypass line 5b, and opens towards with the passage of the room 4 of liquid filling when liquid-filling valve is opened.
Fig. 4 illustrates the external view of the part in figs 2 and 3 shown in the longitudinal section of aircraft shock absorber with double seal arrangement according to the present invention.Valve shell 50 and the first component 10 are tightened.Valve pocket 55 and the valve 60 with operative pin 61 load in described valve shell 50.In addition, valve shell 50 installs liquid-filling valve 70.
Described changing valve 60 has the head with outer-hexagonal on operative pin 61, and described head is screwed in valve pocket by rotating clockwise.Be screwed into by described, valve slider can forward (Fig. 3) on buttoned-up position to.
Described operative pin 61 has mark 62 in entering in region of valve pocket 55, and by described mark, the position of valve is from outer.
Described changing valve 60 has the head with outer-hexagonal equally.
Claims (11)
1. an aircraft shock absorber with double seal arrangement, have at least two tubular components, wherein, the first component has the room with liquid filling in its inside, and wherein, second component is arranged to, and can move along common longitudinal axis in described first component,
It is characterized in that, described vibration damper has at least two seal arrangements in series arranged along the direction of described common longitudinal axis and at least one bypass line can cut out by changing valve between the outer surface and the internal surface of described first component of described second component, described bypass line connects described with the room of liquid filling and the gap between described seal arrangement
Wherein, described aircraft shock absorber with double seal arrangement has in addition fills pipeline and/or the liquid-filling valve irrelevant with described changing valve,
Wherein, independently use described filling pipeline with the position of described changing valve, and independently operate described liquid-filling valve with the position of described changing valve.
2. aircraft shock absorber with double seal arrangement as claimed in claim 1, wherein, two seal arrangements are arranged in the gap between the outer surface of described second component and the internal surface of described first component, and fully surround second component.
3. aircraft shock absorber with double seal arrangement as claimed in claim 2, wherein, described seal arrangement is configured to seal ring.
4. aircraft shock absorber with double seal arrangement as claimed any one in claims 1 to 3, wherein, described seal arrangement is equivalent seal arrangement.
5. aircraft shock absorber with double seal arrangement as claimed in claim 4, wherein, described seal arrangement is the seal arrangement that structure is identical.
6. aircraft shock absorber with double seal arrangement as claimed any one in claims 1 to 3, wherein, one of described seal arrangement is inner sealing device, and another of described seal arrangement is outer sealing device, and wherein, when bypass line is opened, described outer sealing device is by pressure-loaded, and/or described inner sealing device is pressure balanced.
7. aircraft shock absorber with double seal arrangement as claimed any one in claims 1 to 3, wherein, one of described seal arrangement is inner sealing device, and another of described seal arrangement is outer sealing device, and wherein, in the buttoned-up situation of bypass line, described inner sealing device is by pressure-loaded, and/or described outer sealing device is not by pressure-loaded.
8. aircraft shock absorber with double seal arrangement as claimed any one in claims 1 to 3, wherein, one of described seal arrangement is inner sealing device, and another of described seal arrangement is outer sealing device, and wherein, described outer sealing device is used as main sealing device in the normal work of aircraft shock absorber with double seal arrangement, and described inner sealing device is used as backup seal device.
9. aircraft shock absorber with double seal arrangement as claimed any one in claims 1 to 3, wherein, described bypass line and described changing valve are arranged in described first component or are arranged on described first component.
10. aircraft shock absorber with double seal arrangement as claimed in claim 1, wherein, described liquid-filling valve and/or described filling pipeline and described changing valve are configured to element of construction.
11. aircraft shock absorber with double seal arrangements as described in claim 1 or 10, wherein, at least one first portion of described bypass line and at least one first portion of described filling pipeline mate mutually, and wherein, the second portion of described bypass line and/or the second portion of described filling pipeline extend apart from each other.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102010032546.5 | 2010-07-29 | ||
| DE102010032546A DE102010032546A1 (en) | 2010-07-29 | 2010-07-29 | aircraft shock absorber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102384210A CN102384210A (en) | 2012-03-21 |
| CN102384210B true CN102384210B (en) | 2015-12-09 |
Family
ID=44676253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110224547.6A Active CN102384210B (en) | 2010-07-29 | 2011-07-29 | Aircraft shock absorber with double seal arrangement |
Country Status (4)
| Country | Link |
|---|---|
| CN (1) | CN102384210B (en) |
| DE (1) | DE102010032546A1 (en) |
| FR (1) | FR2963319B1 (en) |
| GB (1) | GB2482414B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DK2886231T4 (en) | 2013-12-17 | 2021-03-01 | Mn Coil Servicecenter Gmbh | Method for manufacturing a body part |
| CA2849148C (en) | 2014-04-16 | 2016-01-12 | Spp Canada Aircraft, Inc. | Aircraft shock absorber redundant seal assembly |
| DE202020106080U1 (en) | 2020-10-23 | 2022-01-25 | Liebherr-Aerospace Lindenberg Gmbh | Shock absorber with switching valve |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3514114A (en) * | 1967-11-09 | 1970-05-26 | John C Monahan | Multiple sealing means |
| GB2170294A (en) * | 1984-12-08 | 1986-07-30 | Automotive Products Plc | Shock absorber |
| US4924975A (en) * | 1988-03-09 | 1990-05-15 | Messier-Hispano-Bugatti | Shock absorber with improved dynamic sealing |
| US5310139A (en) * | 1992-01-07 | 1994-05-10 | Messier-Bugatti | Shock absorber for aircraft landing gear |
| CN1164213A (en) * | 1994-11-18 | 1997-11-05 | 联合工艺公司 | Crashworthy landing gear for aircraft |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE702160C (en) * | 1935-12-25 | 1941-01-31 | E H Dr Phil H C Ernst Heinkel | |
| GB537686A (en) * | 1939-12-23 | 1941-07-02 | Bendix Aviat Corp | Improvements in or relating to shock absorbers |
| US3300202A (en) * | 1965-02-03 | 1967-01-24 | Caterpillar Tractor Co | Vehicle suspension strut |
| FR1473847A (en) * | 1965-05-03 | 1967-03-24 | Improvements to suspension devices | |
| DE1630738A1 (en) * | 1967-11-16 | 1971-08-12 | Langen & Co | Hydraulic cylinder, especially for struts or vibration dampers of vehicles with level control |
| IT969356B (en) * | 1971-10-01 | 1974-03-30 | Kaller S | LOCKING DEVICE |
| DE7422901U (en) * | 1974-07-05 | 1974-10-31 | Stabilus Gmbh | Gas spring with oil cushion seal |
| SE404414B (en) * | 1977-02-25 | 1978-10-02 | Alfa Laval Ab | DEVICE FOR DISHING A FIRST SEAL RING AND A SPACE NEARLY NEXT THE SEAL RING |
| CA2028468A1 (en) * | 1990-10-24 | 1992-04-25 | Ronald F. Barlow | Hydraulic shock absorber |
| DE102004031995B4 (en) | 2004-07-01 | 2008-11-06 | Liebherr-Aerospace Lindenberg Gmbh | aircraft shock absorber |
| FR2946720B1 (en) * | 2009-06-12 | 2011-06-10 | Messier Dowty Sa | DAMPER AND LIGHTER EQUIPPED WITH SUCH DAMPER. |
-
2010
- 2010-07-29 DE DE102010032546A patent/DE102010032546A1/en active Pending
-
2011
- 2011-07-27 FR FR1156856A patent/FR2963319B1/en active Active
- 2011-07-27 GB GB1112914.5A patent/GB2482414B/en active Active
- 2011-07-29 CN CN201110224547.6A patent/CN102384210B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3514114A (en) * | 1967-11-09 | 1970-05-26 | John C Monahan | Multiple sealing means |
| GB2170294A (en) * | 1984-12-08 | 1986-07-30 | Automotive Products Plc | Shock absorber |
| US4924975A (en) * | 1988-03-09 | 1990-05-15 | Messier-Hispano-Bugatti | Shock absorber with improved dynamic sealing |
| US5310139A (en) * | 1992-01-07 | 1994-05-10 | Messier-Bugatti | Shock absorber for aircraft landing gear |
| CN1164213A (en) * | 1994-11-18 | 1997-11-05 | 联合工艺公司 | Crashworthy landing gear for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2963319A1 (en) | 2012-02-03 |
| GB201112914D0 (en) | 2011-09-14 |
| GB2482414B (en) | 2017-05-03 |
| DE102010032546A1 (en) | 2012-02-02 |
| FR2963319B1 (en) | 2016-07-22 |
| GB2482414A (en) | 2012-02-01 |
| CN102384210A (en) | 2012-03-21 |
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