CN100586794C - Overhang spindle bumper absorber for airliner undercart - Google Patents
Overhang spindle bumper absorber for airliner undercart Download PDFInfo
- Publication number
- CN100586794C CN100586794C CN200810115496A CN200810115496A CN100586794C CN 100586794 C CN100586794 C CN 100586794C CN 200810115496 A CN200810115496 A CN 200810115496A CN 200810115496 A CN200810115496 A CN 200810115496A CN 100586794 C CN100586794 C CN 100586794C
- Authority
- CN
- China
- Prior art keywords
- pressurized strut
- damping
- chamber
- air chamber
- spindle
- 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
Links
Images
Landscapes
- Fluid-Damping Devices (AREA)
Abstract
The invention discloses an overhanging oil needle bumper used for a large aerobus landing gear. The main structure of the overhanging oil needle bumper comprises an upper actuation cylinder, a lower actuation cylinder, a low pressure air chamber, a high pressure air chamber, a compression damping chamber, an oil needle, a damping platform, a damping hole and an inflation hole; the top end of the upper actuation cylinder is connected with the oil needle by screw thread, namely, the oil needle overhangs in the upper actuation cylinder; the internal bottom of the lower actuation cylinder is provided with the low pressure air chamber and the high pressure air chamber which are separated from each other by a movable piston; the lower part of the lower actuation cylinder is provided with the inflation hole, by which two inflation pipelines are led out and respectively connected with the high pressure air chamber and the lower pressure air chamber; the two pipelines are internally provided with two check valves respectively, so as to control the inflation operation. The overhanging oil needle bumper can simplify the arrangement of the inflation hole and lead the inflation to the high pressure air chamber and the lower pressure air chamber to be more convenient. As the dual air chambers are arranged at the lower part of the bumper at the same time, the reaction force generated by the bumper has progressive characteristic when the bumper bears the environmental pressure. Furthermore, the overhanging oil needle bumper has faster pressure transmission and more remarkable damping effect compared with the traditional dual air chamber structures.
Description
Technical field
The invention belongs to the aviation machine technical field, be specifically related to a kind of large-scale seating plane alighting gear shock absorber.
Background technology
May often use simple hole as damping hole on flivver, this design can obtain 85% efficient, along with the increase of aircraft size, particularly airliner, needs the damping hole of a variation usually.When shock absorber began to compress, damping speed was slowly, so, need damping hole to diminish to increase efficient.When near dead position, damping speed increases, and damping hole need further reduce, because damping speed approaches zero.
Be applied at present that the spindles that adopt change oil speed more on the transport plane energy disperser of airliner, because this method is fairly simple, more reliable, do not need repairing, and it is so complicated unlike hydraulic valve, the diameter that only need revise spindle when carrying out drop-test a little just can obtain best damping hole, but adopts the design of spindle how spindle to be placed in the energy disperser lower end at present.
Bicavate energy disperser commonly used as shown in Figure 1,1 is last pressurized strut among the figure; 2 is pressurized strut down; 3 compression damping chambeies (be equivalent to first air chamber and also claim low-pressure chamber); 4 spindles; 5 rebound damping chambeies; 6 pistons; 7 damping holes; 8 second air chambers (plenum chamber); 13 air-filled pores.The energy disperser of this routine has two air chambers, does not have the first independent air chamber in the energy disperser of routine, generally compression damping chamber 3 is regarded as at first compressed first air chamber, and this is comparatively common in the oil gas shock absorber of routine.Second air chamber 8 is in piston rod, the lower end of piston 6, filling pressure is higher in second air chamber 8, to guarantee aircraft sliding race on coarse runway, when the ground bump stroke reaches certain numerical value, start working, thereby reduce the load peaks that aircraft is crossed hillock or pit.The bicavate oil gas energy disperser of this routine is because the compression damping chamber 3 and second air chamber 8 lay respectively at the top and bottom of energy disperser, promptly be arranged in pressurized strut 1 and following pressurized strut 2, to need two air intake valves to two air chamber inflations, this will process two air-filled pores 13 on the energy disperser outer wall, this can cause stress concentration to influence the intensity of alighting gear to a certain extent, and the intensity of alighting gear is vital to whole aircraft safety.Two other air chamber separates the two ends up and down that are positioned at energy disperser, and in the moment of alighting gear landing, energy disperser is subjected to external pressure, and to make the counter-force that the time spent produces discontinuous, makes the passenger feel uncomfortable when taking.We have carried out transforming again to oil gas formula buffer structure based on this, make every effort to overcome these drawbacks.
Summary of the invention
The object of the invention provides a kind of overhang spindle bumper absorber for airliner undercart, exactly in order to solve the drawback of conventional buffer, the bicavate buffer structure is improved, and the agent structure of energy disperser of the present invention is similar with traditional shock absorber, comprises equally: go up pressurized strut; Following pressurized strut; Low-pressure chamber; Plenum chamber; The compression damping chamber; Spindle; The damping platform; Damping hole; Air-filled pore.But the present invention is at the last pressurized strut roof spindle that is threaded, and this spindle is hung by the feet in last pressurized strut, and spindle adopts equally and becomes the diameter design, and oil is changed by the area of oilhole, thereby has reached the purpose of restriction oil speed.Be provided with a location convex at following pressurized strut inner bottom part, this location convex is fixed in down in the pressurized strut, also be provided with low, plenum chamber at following pressurized strut inner bottom part, be provided with down isolation piston between low, the plenum chamber, be provided with a damping platform on following pressurized strut top, is provided with a damping hole in the middle of the damping platform, this damping hole is relative with spindle, and between damping platform and following isolation piston, fixedly be provided with isolation piston on the convex; Last pressurized strut inwall and following pressurized strut outer wall form the rebound damping chamber, last pressurized strut, spindle, damping platform and last isolation piston have been formed the compression damping chamber, form low-pressure chamber between last isolation piston and the following isolation piston, constituted plenum chamber between following isolation piston and the following pressurized strut.With the location convex following isolation piston is positioned between plenum chamber and the low-pressure chamber, the location convex is disposable casting with following pressurized strut, and purpose is at the difference of pressure that guarantees under the situation of dead load effect between the high and low pressure air chamber.An air-filled pore is arranged on down on the outer wall of pressurized strut bottom, leads to the high and low pressure air chamber respectively by two gas ductings, and a unidirectional charging valve is installed respectively in two pipelines.
Energy disperser of the present invention pressurized strut up and down adopts disposable casting, and piston and barrel contact portion seal with seal ring.
The invention has the advantages that:
(1) two air chambers all design below, can simplify the air-filled pore setting, make high and low pressure air chamber is inflated convenient easy to operate.
(2) two air chambers below the time, change the riding position of spindle, avoided the change of air chamber volume to produce effectively and disturbed to spindle and to oilhole restriction oil speed.
(3) the two air chamber energy dispersers of Chang Gui oil gas are placed in the two ends of energy disperser respectively with two air chambers, and the present invention is installed on the energy disperser bottom simultaneously with two air chambers, make energy disperser have cumulative property being subjected to ambient pressure to make the counter-force that the time spent produces.And faster with respect to traditional two air chamber design pressure transmission, damping effect is outstanding.
Description of drawings
Fig. 1 is a traditional double cavate energy disperser scheme drawing;
Fig. 2 is the planar structure scheme drawing of energy disperser of the present invention;
Fig. 3 is the 3D scheme drawing of energy disperser of the present invention;
Fig. 4 is an air-filled pore structural representation among the present invention.
Wherein: the last pressurized strut of 1-; Pressurized strut under the 2-; 3-compression damping chamber; The 4-spindle; 5-rebound damping chamber; The 7-damping hole; The 8-plenum chamber; The last isolation piston of 9-; Isolation piston under the 10-; 11-locatees convex; 12-low-pressure chamber; The 13-air-filled pore; The 14-one-way cock; 15-damping platform.
The specific embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention resets the riding position of conventional buffer air chamber and spindle.As shown in Figure 2, at first low-pressure chamber 12 is compressed when energy disperser is subjected to ambient pressure, the pressure of low-pressure chamber 12 increases thereupon, when pressure increases to plenum chamber 8 air pressure identical the time, plenum chamber 8 begins to be compressed, two compressed while oil gas of air chamber are pressed into damping hole 7, become the diameters design because spindle 4 adopts, thus when the compressed while spindle 4 of energy disperser can time changing damping hole 7 area.
The agent structure of energy disperser of the present invention is arranged on the bottom of energy disperser with high pressure, two air chambers of low pressure 8,12 as shown in Figure 3, is separated by isolation piston 10 down between the 2 air chambers, 13 pairs of two air chambers of an air-filled pore is set in the centre of two air chambers puts on the air.Detail can be as shown in Figure 4, promptly descend on the pressurized strut 2 bottom outer walls to be provided with an air-filled pore 13 in the bottom of energy disperser, draw two gas ductings by air-filled pore 13 and be connected with plenum chamber 8 and low-pressure chamber 12 respectively, control charge operation by two one-way cocks 14 in two pipelines.Two air chambers are installed on the energy disperser bottom, and low-pressure chamber 12 separates with compression damping chamber 3 by last isolation piston 9, and as shown in Figure 3, spindle 4 is installed on the roof of pressurized strut 1, and uses the screw thread captive joint.Spindle 4 same employings become diameter structure, and oil is changed by the area of damping hole 7, thereby have reached the effect of restriction oil speed.
Disposable casting is adopted in the upper and lower pressurized strut 1,2 of energy disperser of the present invention, and upper and lower isolation piston 9,10 and barrel contact portion seal with seal ring, and last pressurized strut 1 inwall and following pressurized strut 2 outer walls form rebound damping chamber 5, as Fig. 2; Last pressurized strut 1, spindle 4, damping platform 15 and last isolation piston 9 have been formed compression damping chamber 3; Formed low-pressure chamber 12 between last isolation piston 9 and the following isolation piston 10; Constituted plenum chamber 8 between following isolation piston 10 and the following pressurized strut 2; Position by 11 pairs of following isolation pistons 10 of location convex between plenum chamber 8 and the low-pressure chamber 12, location convex 11 is fixed in the pressurized strut 2 down and disposable with it casting, and purpose is at the difference of pressure of keeping under the situation of dead load effect between the high and low pressure air chamber 8,12.A unique air-filled pore 13 is arranged between plenum chamber 8 and the low-pressure chamber 12, leads to high and low pressure air chamber 8,12 respectively by two gas ductings, and a unidirectional charging valve 14 is installed respectively in two pipelines, and control is to two air chamber inflations.Separate by location convex 11 between the high and low pressure air chamber 8,12.
Claims (2)
1, overhang spindle bumper absorber for airliner undercart, its agent structure comprises: go up pressurized strut, following pressurized strut, low-pressure chamber, plenum chamber, the compression damping chamber, spindle, the damping platform, damping hole, air-filled pore, it is characterized in that, at the last pressurized strut roof spindle that is threaded, this spindle is hung by the feet in last pressurized strut, be provided with a location convex at following pressurized strut inner bottom part, this location convex is fixed in down in the pressurized strut, also be provided with low at following pressurized strut inner bottom part, plenum chamber, low, be provided with down isolation piston between the plenum chamber, be provided with a damping platform on following pressurized strut top, be provided with a damping hole in the middle of the damping platform, this damping hole is relative with spindle, and between damping platform and following isolation piston, fixedly be provided with isolation piston on the convex; Last pressurized strut inwall and following pressurized strut outer wall form the rebound damping chamber, last pressurized strut, spindle, damping platform and last isolation piston have been formed the compression damping chamber, form low-pressure chamber between last isolation piston and the following isolation piston, constituted plenum chamber between following isolation piston and the following pressurized strut; An air-filled pore is arranged on down on the outer wall of pressurized strut bottom, leads to the high and low pressure air chamber respectively by two gas ductings, and a unidirectional charging valve is installed respectively in two pipelines.
2, overhang spindle bumper absorber for airliner undercart according to claim 1 is characterized in that, the location convex is disposable casting spare with following pressurized strut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810115496A CN100586794C (en) | 2008-06-24 | 2008-06-24 | Overhang spindle bumper absorber for airliner undercart |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810115496A CN100586794C (en) | 2008-06-24 | 2008-06-24 | Overhang spindle bumper absorber for airliner undercart |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101293567A CN101293567A (en) | 2008-10-29 |
| CN100586794C true CN100586794C (en) | 2010-02-03 |
Family
ID=40064182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810115496A Expired - Fee Related CN100586794C (en) | 2008-06-24 | 2008-06-24 | Overhang spindle bumper absorber for airliner undercart |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100586794C (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094926B (en) * | 2010-12-14 | 2012-05-30 | 南京航空航天大学 | Potential energy storage type protruding undercarriage buffer |
| CN102338186B (en) * | 2011-09-02 | 2013-10-09 | 北京航空航天大学 | Conical damping hole type buffer for undercarriage of passenger plane |
| CN103195858B (en) * | 2013-04-15 | 2015-04-22 | 沈阳航空航天大学 | Magnetorheological buffering unit structure based on impact load and control method thereof |
| CN103466085B (en) * | 2013-07-24 | 2015-12-23 | 宁波大学 | A kind of self-adaptive hydraulic many feelers regulating control keeping falling object from high altitude to balance |
| CN103629290B (en) * | 2013-11-27 | 2016-01-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane buffer mutative damp spindle |
| CN104443369A (en) * | 2014-10-29 | 2015-03-25 | 中国商用飞机有限责任公司 | Buffer device of landing gear buffer strut |
| CN105715733A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Magnetorheological buffer of undercarriage |
| ES2796000T3 (en) * | 2017-04-20 | 2020-11-25 | Safran Landing Systems Uk Ltd | Aircraft landing gear shock absorber strut |
| CN109229346B (en) * | 2018-08-28 | 2020-05-26 | 北京航空航天大学 | Buffer suitable for miniature unmanned vehicles oil gas shock attenuation formula undercarriage |
| CN109296691B (en) * | 2018-11-09 | 2021-02-26 | 中国直升机设计研究所 | Double-cavity buffer |
| CN111332798B (en) * | 2020-05-20 | 2020-09-29 | 山东万物生机械技术有限公司 | Building glass conveying device capable of turning and working method thereof |
| CN113264185B (en) * | 2021-07-20 | 2022-04-01 | 江苏南瓯物联网科技有限公司 | Range finding aircraft |
-
2008
- 2008-06-24 CN CN200810115496A patent/CN100586794C/en not_active Expired - Fee Related
Non-Patent Citations (4)
| Title |
|---|
| 飞机支柱式起落架落震仿真及缓冲器优化分析. 蔺越国，程家林，黎泽金，冯振宇，卢翔.飞机设计，第27卷第4期. 2007 |
| 飞机支柱式起落架落震仿真及缓冲器优化分析. 蔺越国，程家林，黎泽金，冯振宇，卢翔.飞机设计，第27卷第4期. 2007 * |
| 飞机起落架缓冲器数学模型研究. 隋福成，陆华.飞行器设计，第2期. 2001 |
| 飞机起落架缓冲器数学模型研究. 隋福成，陆华.飞行器设计，第2期. 2001 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101293567A (en) | 2008-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100586794C (en) | Overhang spindle bumper absorber for airliner undercart | |
| CN102338186B (en) | Conical damping hole type buffer for undercarriage of passenger plane | |
| CN100478251C (en) | Two-stage series connection two-chamber buffer | |
| CN111609073B (en) | Aircraft landing gear buffer | |
| CN102720795A (en) | Hydro-pneumatic spring for amphibious vehicles and hydraulic regulating device for hydro-pneumatic spring for amphibious vehicle | |
| CN104791407A (en) | Passive hydraulic damping device | |
| CN100427793C (en) | Oil-gas spring | |
| CN106286674A (en) | A kind of autonomous retractable landing gear buffer | |
| CN203836056U (en) | Buffer for helicopter | |
| CN105020316A (en) | Undercarriage buffer | |
| CN202402547U (en) | Stretched buffer | |
| CN105626738A (en) | Aircraft undercarriage mixed damping method | |
| CN103640694B (en) | A kind of buffering off-load arrester hook hook arm | |
| CN103671008A (en) | Quaternary ultrahigh pressure inflator | |
| CN105864344A (en) | Damping shock absorber for hydraulic interconnection suspension | |
| CN105179551A (en) | Single-piston-rod double-cylinder-barrel hydro-pneumatic spring cylinder | |
| CN204677668U (en) | A kind of passive passive type hydraulic damping device | |
| CN207848084U (en) | A kind of compression spring self-resetting oil cylinder of heavy load and limited lifting space | |
| CN114110081B (en) | Helicopter landing gear buffer | |
| CN206175550U (en) | Undercarriage shock strut oiling device | |
| CN205136220U (en) | Nonoculture is with two piston -cylinder actuating mechanism | |
| CN215409920U (en) | Integrated two-stage pressure hydraulic air spring | |
| CN109606651B (en) | Aircraft strut landing gear of steerable length | |
| CN203656031U (en) | Shock absorber with defoaming bottom valve | |
| CN201982569U (en) | Auxiliary landing actuator cylinder |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100203 Termination date: 20120624 |