CN2309284Y - Shock-absorbing leg for undercarriage - Google Patents
Shock-absorbing leg for undercarriage Download PDFInfo
- Publication number
- CN2309284Y CN2309284Y CN 97220365 CN97220365U CN2309284Y CN 2309284 Y CN2309284 Y CN 2309284Y CN 97220365 CN97220365 CN 97220365 CN 97220365 U CN97220365 U CN 97220365U CN 2309284 Y CN2309284 Y CN 2309284Y
- Authority
- CN
- China
- Prior art keywords
- pillar
- piston
- urceolus
- inner core
- undercarriage
- 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.)
- Expired - Fee Related
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- Fluid-Damping Devices (AREA)
Abstract
The utility model discloses a shock absorbing strut for the undercarriage of an airplane, which is telescopic. The outer cylinder of the shock absorbing strut is provided with a piston which can move up and down; the lower end of the piston is provided with the inner cylinder of the shock absorbing strut; a shock absorbing device is arranged between the piston and the shock absorbing strut; the top and the bottom of the outer cylinder of the shock absorbing strut are provided with two oil holes which are connected with a hydraulic control system. Since the utility model is telescopic, the lifting of the airplane is telescopic as required. Therefore, the utility model can expand the practical elevation range of the lifting of the airplane and is beneficial to the extended modification of a fuselage.
Description
The utility model relates to a kind of undercarriage, relates in particular to a kind of shock strut of undercarriage.
In the landing process, rear body easily contacted to earth present aircraft (the especially long aircraft of rear body) when the aircraft elevation angle was big, had limited the practical elevation coverage of landing of aircraft, had limited the lengthening remodeling of fuselage simultaneously.As the alighting gear that extends, then need increase its intensity, increased simultaneously and shut down height, cause inconveniences such as passenger and freight, maintenance, guarantee service.
The purpose of this utility model is to overcome the deficiencies in the prior art, can enlarge practical elevation coverage when a kind of takeoff and landing are provided, and is of value to the fuselage lengthening, and does not increase the novel undercarriage cushioning pillar of alighting gear entire length.
The purpose of this utility model is achieved in that analyzes existing undercarriage, and emphasis is transformed shock strut, and it is designed to the telescoping structure, and keeps damping effect.A kind of piston moving up and down of upper design in undercarriage cushioning pillar urceolus, the lower end is the pillar inner core, is provided with shock absorption device between piston and pillar inner core; Have two oilholes on the pillar urceolus and be connected, be provided with the pillar coupling assembling at the top of pillar urceolus with hydraulic control system.
The top of piston described in the utility model is provided with an oil gas and charges valve, communicates with damping, is provided with Fuel Bleed Valve in the lower end of pillar inner core, is provided with damping chamber oil gas and charges the hole on the pillar coupling assembling.
Upper/lower terminal is respectively equipped with bit card part and following bit card part in the urceolus described in the utility model.
Hydraulic control system described in the utility model can be made up of electromagnetic hydraulic pressure change-over valve, oil pipe, hydraulic power source, fuel tank etc.
Shock strut of the present utility model is a telescoping, and design has a kind of piston moving up and down in the shock strut urceolus, and the piston lower end is the pillar inner core, is provided with shock absorption device between piston and pillar inner core; Having two oilholes on the pillar urceolus is connected with hydraulic control system.Because the utility model is a telescoping, shock strut can stretch as required when takeoff and landing.Therefore, can enlarge the practical elevation coverage of takeoff and landing, and be of value to the lengthening remodeling of fuselage.
Reaching embodiment in conjunction with the accompanying drawings is further described the utility model:
Accompanying drawing 1, the utility model example structure scheme drawing;
Form by shock strut urceolus (4), piston (6), pillar inner core members such as (8) as accompanying drawing 1, the utility model.Piston (6) is arranged on the top in the pillar urceolus (4), and piston (6) lower end is pillar inner core (8), is provided with shock absorption device (7) between piston (6) and pillar inner core (8); Have two oilholes (14) (20) on the pillar urceolus (4) and be connected, be provided with pillar coupling assembling (1) at the top of pillar urceolus (4) with hydraulic control system.
The top of piston (6) is provided with an oil gas and charges valve (5), communicate with damping (7), be provided with corresponding Fuel Bleed Valve (12) and machine wheel carrier coupling assembling (15) in the lower end of pillar inner core (8), on pillar coupling assembling (1), be provided with damping chamber oil gas and charge hole (2).Its shock absorption device (7) is selected the conventional shock absorption device of prior art for use.
The interior upper/lower terminal of pillar urceolus (4) is respectively equipped with bit card part (3) and following bit card part (9).Bottom at following bit card part (9) is provided with sealing member (10), bottom (11).
The hydraulic control system of present embodiment is made up of electromagnetic hydraulic pressure change-over valve (15), hydraulic power source (16), fuel tank (17) etc.Top two interfaces of electromagnetic hydraulic pressure change-over valve (15) connect the upper oil hole (14) and the following oilhole (20) of pillar urceolus (4) respectively by oil pipe, electromagnetic hydraulic pressure change-over valve (15) bottom two interfaces connect hydraulic power source (16) and fuel tank (17) by oil pipe respectively.Two position switching valves (18), flow regulating valve (19) and check valve (21) are serially connected between the following oilhole (20) of fuel tank (17) and pillar urceolus (4).
When the needs shock strut extends, electromagnetic hydraulic pressure change-over valve (15) moves to right, the high pressure oil that is flowed out by hydraulic power source (16) is through electromagnetic hydraulic pressure change-over valve (15), enters pillar urceolus (4) epicoele by the upper oil hole (14) of pillar urceolus (4), promotes piston (6), pillar inner core (8) moves down.Simultaneously, the oil in pillar urceolus (4) cavity of resorption flows back to fuel tank (17) by following oilhole (20) through electromagnetic hydraulic pressure change-over valve (15).When moving near following bit card part (9), electromagnetic hydraulic pressure change-over valve (15) moves to left to meta and locks.
When the needs shock strut shortened: electromagnetic hydraulic pressure change-over valve (15) moved to left, the high pressure oil that is flowed out by hydraulic power source (16) is through electromagnetic hydraulic pressure change-over valve (15), following oilhole (20) by pillar urceolus (4) enters pillar urceolus (4) cavity of resorption, and promotion pillar inner core (8), piston move on (6).Oil in pillar urceolus (4) epicoele flows back to fuel tank (17) by last hydraulic fluid port (20) through electromagnetic hydraulic pressure change-over valve (15).At this moment, two position switching valves (18) are closed, and prevent that high pressure oil from refluxing.When piston (6) moved to bit card part (3), electromagnetic hydraulic pressure change-over valve (15) moved to right to meta and locks.Two position switching valves (18) are opened simultaneously, constitute damping state (being pillar inner core (8) elongation and the shortening of short travel).When pillar inner core (8) compressed, check valve (21) was opened, and flow regulating valve (19) and check valve (21) co-operation are the additional fluid of the cavity of resorption of pillar urceolus (4); When a column pressure reduced pillar inner core (8) elongation, check valve (21) was closed, and the rate of outflow of flow regulating valve (10) restriction pillar urceolus (4) cavity of resorption inner fluid has played the effect of damping.
Claims (3)
1, a kind of shock strut of undercarriage, form by pillar urceolus, pillar inner core, shock absorption device etc., it is characterized in that: pillar urceolus internal upper part is provided with piston, the piston lower end is the pillar inner core, between piston and pillar inner core, be provided with shock absorption device, have two oilholes on the pillar urceolus and be connected, be provided with the pillar coupling assembling at the top of pillar urceolus with hydraulic control system.
2, the shock strut of a kind of undercarriage according to claim 1, it is characterized in that: the top of described piston is provided with an oil gas and charges valve, communicate with damping, be provided with corresponding Fuel Bleed Valve in the lower end of pillar inner core, on the pillar coupling assembling, be provided with damping chamber oil gas and charge the hole.
3, the shock strut of a kind of undercarriage according to claim 1 is characterized in that: upper/lower terminal is respectively equipped with bit card part and following bit card part in the described pillar urceolus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97220365 CN2309284Y (en) | 1997-07-08 | 1997-07-08 | Shock-absorbing leg for undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97220365 CN2309284Y (en) | 1997-07-08 | 1997-07-08 | Shock-absorbing leg for undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2309284Y true CN2309284Y (en) | 1999-03-03 |
Family
ID=33936066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97220365 Expired - Fee Related CN2309284Y (en) | 1997-07-08 | 1997-07-08 | Shock-absorbing leg for undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2309284Y (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102374260A (en) * | 2010-07-21 | 2012-03-14 | 通用电气航空系统有限公司 | Compact shimmy damper for aircraft landing gear |
| CN103038538A (en) * | 2010-07-29 | 2013-04-10 | 梅西耶-道提股份有限公司 | Hydraulic shimmy damper for aircraft landing gear |
| CN101821162B (en) * | 2007-10-09 | 2013-06-05 | 梅西耶-道提有限公司 | Load detection in an aircraft landing gear |
| WO2016066094A1 (en) * | 2014-10-29 | 2016-05-06 | 中国商用飞机有限责任公司 | Buffering apparatus for landing gear buffering strut |
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and an unmanned aerial vehicle using the landing gear |
| CN107600457A (en) * | 2017-08-23 | 2018-01-19 | 中航飞机起落架有限责任公司 | Device and its application method are removed in a kind of jacking that middle experiment is returned for aircraft nose landing gear soon |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN108839789A (en) * | 2018-07-06 | 2018-11-20 | 安徽思源三轻智能制造有限公司 | Undercarriage |
| CN109606651A (en) * | 2018-12-07 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft strut formula undercarriage of controllable length |
| CN110015408A (en) * | 2018-01-09 | 2019-07-16 | 波音公司 | Equipment for shrinking undercarriage |
| CN110291007A (en) * | 2016-10-24 | 2019-09-27 | 福克起落装置有限公司 | The to maintain equipment of damper for undercarriage and the method for safeguarding this damper |
-
1997
- 1997-07-08 CN CN 97220365 patent/CN2309284Y/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101821162B (en) * | 2007-10-09 | 2013-06-05 | 梅西耶-道提有限公司 | Load detection in an aircraft landing gear |
| CN102374260A (en) * | 2010-07-21 | 2012-03-14 | 通用电气航空系统有限公司 | Compact shimmy damper for aircraft landing gear |
| CN103038538A (en) * | 2010-07-29 | 2013-04-10 | 梅西耶-道提股份有限公司 | Hydraulic shimmy damper for aircraft landing gear |
| CN103038538B (en) * | 2010-07-29 | 2015-01-07 | 梅西耶-道提股份有限公司 | Hydraulic shimmy damper for aircraft landing gear |
| WO2016066094A1 (en) * | 2014-10-29 | 2016-05-06 | 中国商用飞机有限责任公司 | Buffering apparatus for landing gear buffering strut |
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and an unmanned aerial vehicle using the landing gear |
| CN110291007A (en) * | 2016-10-24 | 2019-09-27 | 福克起落装置有限公司 | The to maintain equipment of damper for undercarriage and the method for safeguarding this damper |
| CN107600457B (en) * | 2017-08-23 | 2019-07-19 | 中航飞机起落架有限责任公司 | It is a kind of to remove device and its application method fastly for the middle jacking tested of aircraft nose landing gear time |
| CN107600457A (en) * | 2017-08-23 | 2018-01-19 | 中航飞机起落架有限责任公司 | Device and its application method are removed in a kind of jacking that middle experiment is returned for aircraft nose landing gear soon |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN108216589B (en) * | 2017-12-15 | 2021-09-14 | 中国航空工业集团公司成都飞机设计研究所 | Undercarriage pillar contraction mechanism |
| CN110015408A (en) * | 2018-01-09 | 2019-07-16 | 波音公司 | Equipment for shrinking undercarriage |
| CN110015408B (en) * | 2018-01-09 | 2023-05-16 | 波音公司 | Device for retracting landing gear |
| CN108839789A (en) * | 2018-07-06 | 2018-11-20 | 安徽思源三轻智能制造有限公司 | Undercarriage |
| CN109606651A (en) * | 2018-12-07 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft strut formula undercarriage of controllable length |
| CN109606651B (en) * | 2018-12-07 | 2021-12-31 | 江西洪都航空工业集团有限责任公司 | Aircraft strut landing gear of steerable length |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |