CN103629290B - A kind of airplane buffer mutative damp spindle - Google Patents
A kind of airplane buffer mutative damp spindle Download PDFInfo
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- CN103629290B CN103629290B CN201310619237.3A CN201310619237A CN103629290B CN 103629290 B CN103629290 B CN 103629290B CN 201310619237 A CN201310619237 A CN 201310619237A CN 103629290 B CN103629290 B CN 103629290B
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Abstract
The invention belongs to airplane buffer technology, relate to a kind of airplane buffer mutative damp spindle.Airplane buffer mutative damp spindle of the present invention is cylindrical needle body, needle body outer surface offers the groove of some genesis analysis, and from the initial segment, needle body outer surface is provided with 4 grooves as control point vertically, wherein, section start section spindle sectional area parameter is 1.07f; First groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; Second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, and wherein, L is the structure stroke of buffer, and f is stand oil hole area when keeping normal load two peak values equal.Buffer mutative damp spindle of the present invention can eliminate the depressed area between normal load two peak values, and make load mild, make the merit discharge curve of buffer more full, efficiency factor is increased to 80%, far exceedes existing level, has significant technique effect.
Description
Technical field
The invention belongs to airplane buffer technology, relate to a kind of airplane buffer mutative damp spindle.
Background technique
For common compact airplane buffer damping device, the damping device of the single oilhole form of general employing, but it is on the low side for large aircraft buffer list oilhole damper efficiency, general employing spindle formula mutative damp device, spindle formula mutative damp device can improve buffer efficiency, but what kind of mutative damp coefficient can improve buffer efficiency to greatest extent, also furthers investigate.
Baby plane buffer adopts single oilhole damping device both at home and abroad at present, and damping parameter is a constant, normal load curve, has a depression, have impact on the absorption of buffer energy between two peak values, causes buffer efficiency not high.For the spindle formula damping device that large aircraft buffer mainly adopts, spindle lower end is fixed in piston rod, spindle is smooth taper cross section, spindle and plunger gap jointly form damping device and cross pasta and amass, and for this mutative damp apparatus structure form, mutative damp parameter curve is dull, fully can not improve the efficiency of mutative damp buffer, and during drop-test, mutative damp difficulty of parameter tuning, needs repeatedly to repair.
Summary of the invention
The object of the invention is: a kind of airplane buffer mutative damp spindle that can make full, the effective raising damping effect of merit discharge curve is provided.
Technological scheme of the present invention is: a kind of airplane buffer mutative damp spindle, and be cylindrical needle body, needle body outer surface offers the groove of some genesis analysis, and needle body leading portion depth of groove is greater than needle rear end depth of groove.
Described airplane buffer mutative damp spindle is from the initial segment, and needle body outer surface is provided with 4 grooves as control point vertically, and wherein, section start section spindle sectional area parameter is 1.07f; First groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; Second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, and wherein, L is the structure stroke of buffer, and f is stand oil hole area when keeping normal load two peak values equal.
Buffer structure stroke L is 70 ~ 90% of spindle length dimension.
1 ~ 2% of the piston rod cross section that stand oil hole area f is spindle institute installation place.
Advantage of the present invention is: machine buffer mutative damp spindle of the present invention is by offering the groove of particular arrangement and the degree of depth on needle body surface, the depressed area between normal load two peak values can be eliminated, make load mild, make the merit discharge curve of buffer more full, efficiency factor is increased to 80%, far exceed existing level, there is significant technique effect.
Accompanying drawing explanation
Fig. 1 is mutative damp spindle scheme of installation;
Fig. 2 is mutative damp spindle structural representation;
Fig. 3 is that the A-A of Fig. 2 cuts open figure;
Fig. 4 is mutative damp spindle groove control point schematic diagram;
Fig. 5 is mutative damp spindle using effect schematic diagram,
Wherein, 1-urceolus, 2-plunger, 3-spindle, 4-piston rod.
Embodiment
Below in conjunction with drawings and Examples, the present invention will be further described:
Refer to Fig. 1, it is the mounting structure schematic diagram of airplane buffer mutative damp spindle of the present invention.Airplane buffer mutative damp spindle of the present invention, it is inner that its lower end is arranged on piston rod 4, its upper end is inserted in plunger 2, common composition buffer damping device, when buffer compresses, piston rod 4 and spindle 3 quick insertion urceolus 1 inside, such piston rod inner fluid flows fast through spindle needle body just face groove, creates damping force.Airplane buffer mutative damp spindle of the present invention is cylindrical needle body.Refer to Fig. 2, needle body outer surface offers the groove of some genesis analysis; Described airplane buffer mutative damp spindle is from the initial segment, and needle body outer surface is provided with 4 vertically and sees Fig. 4 as the groove at control point, and for smooth linear connects between each control point.Wherein, section start section spindle sectional area parameter is 1.07f; First groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; Second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, and wherein, L is the structure stroke of buffer, and f is stand oil hole area when keeping normal load two peak values equal.Buffer structure stroke L is 70 ~ 90% of spindle length dimension.1 ~ 2% of the piston rod cross section that stand oil hole area f is spindle institute installation place.
Adopt airplane buffer mutative damp spindle of the present invention, the sunk area between two peak values that the normal load of determining damping oil hole can be occurred is filled and led up, and makes normal load become mild shape; Can be reduced the normal load of 5-10%, improve buffer absorption efficiency coefficient 5-10%.
In certain embodiment, spindle length is 550mm, buffer structure stroke 440mm, piston rod sectional area 23200mm
2, stand oil hole area f is 330mm
2, drop-test (rising without imitative) normal load peak value is reduced to 35T by 37.5T, and reduce 6.7%, normal load J curve effectJ is see Fig. 5, and buffer efficiency factor is increased to 80% by 75%.
Claims (3)
1. an airplane buffer mutative damp spindle, it is characterized in that, for cylindrical needle body, needle body outer surface offers the groove of some genesis analysis, needle body leading portion depth of groove is greater than needle rear end depth of groove, needle body lower end is arranged on piston rod inner, needle body upper end is inserted in plunger, common composition buffer damping device, when buffer compresses, piston rod and needle body quick insertion outer barrel, from the initial segment, needle body outer surface is provided with 4 grooves as control point vertically, and wherein, section start section spindle sectional area parameter is 1.07f; First groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; Second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, and wherein, L is the structure stroke of buffer, and f is stand oil hole area when keeping normal load two peak values equal.
2. airplane buffer mutative damp spindle according to claim 1, is characterized in that, buffer structure stroke L is 70 ~ 90% of spindle length dimension.
3. airplane buffer mutative damp spindle according to claim 2, is characterized in that, 1 ~ 2% of the piston rod cross section that stand oil hole area f is spindle institute installation place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310619237.3A CN103629290B (en) | 2013-11-27 | 2013-11-27 | A kind of airplane buffer mutative damp spindle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310619237.3A CN103629290B (en) | 2013-11-27 | 2013-11-27 | A kind of airplane buffer mutative damp spindle |
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| Publication Number | Publication Date |
|---|---|
| CN103629290A CN103629290A (en) | 2014-03-12 |
| CN103629290B true CN103629290B (en) | 2016-01-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310619237.3A Active CN103629290B (en) | 2013-11-27 | 2013-11-27 | A kind of airplane buffer mutative damp spindle |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106122349B (en) * | 2016-08-23 | 2018-06-01 | 中航飞机起落架有限责任公司 | A kind of fluid damping mechanism of buffer unit |
| CN111473083A (en) * | 2020-04-21 | 2020-07-31 | 中国商用飞机有限责任公司 | Damping device |
| CN112744362B (en) * | 2020-12-29 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Sensor-load mechanism-damper integrated device |
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| GB460361A (en) * | 1935-04-17 | 1937-01-18 | Bendix Aviat Corp | Improvements relating to shock absorbers |
| CN101293567A (en) * | 2008-06-24 | 2008-10-29 | 北京航空航天大学 | Overhang spindle bumper absorber for airliner undercart |
| CN102052422A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Nose landing gear bumper with high-pressure inflatable sudden-extension mechanism |
| CN102094926A (en) * | 2010-12-14 | 2011-06-15 | 南京航空航天大学 | Potential energy storage type protruding undercarriage buffer |
| CN102338186A (en) * | 2011-09-02 | 2012-02-01 | 北京航空航天大学 | Conical damping hole type buffer for undercarriage of passenger plane |
| CN102588484A (en) * | 2011-01-05 | 2012-07-18 | 上海市南洋模范中学 | Actuator cylinder for assisting in landing |
| CN203285899U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | Variable oilhole structure of undercarriage buffer |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130134000A1 (en) * | 2011-11-25 | 2013-05-30 | Messier-Dowty Inc. | Landing gear shock absorber metering using pivoting joint |
-
2013
- 2013-11-27 CN CN201310619237.3A patent/CN103629290B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB460361A (en) * | 1935-04-17 | 1937-01-18 | Bendix Aviat Corp | Improvements relating to shock absorbers |
| CN101293567A (en) * | 2008-06-24 | 2008-10-29 | 北京航空航天大学 | Overhang spindle bumper absorber for airliner undercart |
| CN102052422A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Nose landing gear bumper with high-pressure inflatable sudden-extension mechanism |
| CN102094926A (en) * | 2010-12-14 | 2011-06-15 | 南京航空航天大学 | Potential energy storage type protruding undercarriage buffer |
| CN102588484A (en) * | 2011-01-05 | 2012-07-18 | 上海市南洋模范中学 | Actuator cylinder for assisting in landing |
| CN102338186A (en) * | 2011-09-02 | 2012-02-01 | 北京航空航天大学 | Conical damping hole type buffer for undercarriage of passenger plane |
| CN203285899U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | Variable oilhole structure of undercarriage buffer |
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|---|---|
| CN103629290A (en) | 2014-03-12 |
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