CN101898636B - Energy-absorbing structure of crashworthy landing gear damper leg - Google Patents
Energy-absorbing structure of crashworthy landing gear damper leg Download PDFInfo
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- CN101898636B CN101898636B CN 201010229319 CN201010229319A CN101898636B CN 101898636 B CN101898636 B CN 101898636B CN 201010229319 CN201010229319 CN 201010229319 CN 201010229319 A CN201010229319 A CN 201010229319A CN 101898636 B CN101898636 B CN 101898636B
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Abstract
The invention provides an energy-absorbing structure of a crashworthy landing gear damper leg, comprising a piston rod, an oil chamber, a seal assembly, an oil needle, a blocking valve, an outer cylinder and an air cavity. The invention is characterized in that the energy-absorbing structure adopts the following one or two forms: (1) a bulge is arranged in the middle of the piston rod; and (2) the inner diameter at the back of the outer cylinder gradually decreases and is gradually less than the diameter of the piston rod. The structure has the following advantages: the structure is instead of the high-pressure working cavities in the traditional damper legs; when the helicopters normally take off and land or roughly land, the impact damper oil and gas cavity works; and when crash accidents happen, the impact damper oil and gas cavity firstly absorbs partial crash energy and the residual energy is absorbed by the outer cylinder after the outer cylinder is extruded and cut by the piston rod to deform, thus achieving the effect of crashworthy energy absorbing.
Description
Technical field
The present invention is a kind of energy-absorbing structure of crashworthy landing gear damper leg, belongs to the technical field of structures of product.
Background technology
Existing anti-crash alighting gear damper leg basically all is made up of an operating on low voltage chamber and a high-pressure working chamber; Wherein operating on low voltage chamber work when helicopter Normal Takeoff and Landing and rough the landing; Only work when helicopter crashes of high-pressure working chamber; All be filled with gas mixture in two epitrochoidal chambers; In daily use, all to check maintenance, shortcomings such as double working-chamber anti-crash alighting gear damper leg exists that complex structure, weight are big, manufacturability difference and working service cost height to two epitrochoidal chambers.
Summary of the invention
The present invention designs to the deficiency that exists in the above-mentioned prior art just a kind of energy-absorbing structure of crashworthy landing gear damper leg is provided, and its objective is provides a kind of simple in structure, in light weight, good manufacturability and the low energy-absorbing structure of crashworthy landing gear damper leg of working service cost to replace the high-pressure working chamber of only when the crash energy-absorbing, working in traditional anti-crash alighting gear damper leg.
The objective of the invention is to realize through following technical measures:
This kind energy-absorbing structure of crashworthy landing gear damper leg comprises piston rod, oil pocket, poted assemblies, spindle, retardance valve, urceolus and air cavity, it is characterized in that: one or both forms below this alighting gear damper leg endergonic structure adopts:
(1) is provided with convexity at the middle part of piston rod;
(2) internal diameter at urceolus rear portion dwindles gradually, more and more less than the diameter of piston rod.
The anterior internal diameter of urceolus is bigger than piston rod, and piston rod in this section can be free movable.When the wheel stand under load, the compression of buffering piston bar diminishes the piston rod cavity volume; Force hydraulic oil to gush on the cutoff port through the retardance valve at a high speed, produce frictional damping, kinetic energy is transformed into heat energy; Distribute through piston rod, urceolus, the gas in the energy disperser is compressed simultaneously again; The hard pressed gas of reversal of stroke (when piston rod 1 stretches out) expands, and forces piston rod to stretch out, and nitrogen pressure promotes hydraulic oil and flows into cavity of resorption through the aperture on the retardance valve, and the piston rod of energy disperser is stretched out lentamente.In piston rod up-and-down movement process, the fluid at high speed in the energy disperser flows through the damping hole on the retardance valve, produces retardance, aircraft landing kinetic energy is converted into heat energy dissipates.
Because there is a small embossment at the piston rod middle part; When alighting gear receives anti-crash load; The kick of piston rod moves to the timesharing of urceolus inner cavity, and the protruding of piston rod partly will push urceolus and it is deformed, and utilizes structural distortion to absorb the energy that produces when crashing.
In addition, the rear portion internal diameter of urceolus is littler than piston rod, and when alighting gear received anti-crash load, piston rod movement was to this part, and piston rod is anterior can to deform it by the extruding outer tube inner wall, utilizes structural distortion to absorb the energy that produces when crashing.
Advantage of the present invention is: the present invention replaces the high-pressure working chamber in traditional damper leg with anti-crash alighting gear energy disperser endergonic structure, when helicopter Normal Takeoff and Landing and rough the landing, is worked by energy disperser oil gas chamber; When the crash accident took place, earlier by energy disperser oil gas chamber absorption portion crash energy, dump energy utilized piston rod extruding, the distortion of cutting urceolus to absorb, and reaches the effect of anti-crash energy-absorbing.
Because the alighting gear energy disperser can be destroyed after the crash accident took place; High-pressure working chamber at alighting gear energy disperser in the life-cycle only can be worked once; When the crash accident equally only takes place in this endergonic structure work once, but the present invention with respect to high-pressure working chamber have simple in structure, weight is little, good manufacturability and working service low cost and other advantages.
Description of drawings
Fig. 1 is the present invention program's a theory structure scheme drawing;
Fig. 2 is the partial enlarged drawing at A place among Fig. 1
Fig. 3 is the partial enlarged drawing at B place among Fig. 1
The specific embodiment
Below will combine accompanying drawing and embodiment that the present invention is done to detail further:
Shown in accompanying drawing 1～3; This kind energy-absorbing structure of crashworthy landing gear damper leg; Comprise piston rod 1, oil pocket 3, poted assemblies 4, spindle 5, retardance valve 6, urceolus 7 and air cavity 8, it is characterized in that: this alighting gear damper leg endergonic structure adopts following two kinds of versions:
(1) is provided with protruding 2 at the middle part of piston rod 1;
(2) internal diameter at urceolus 7 rear portions 9 dwindles gradually, more and more less than the diameter of piston rod 1.
Endergonic structure working process of the present invention is: at helicopter normal landing state, through the work absorption helicopter landing energy of oil gas energy disperser; At helicopter crash state; When alighting gear receives anti-crash load; Small embossment 2 on the piston rod 1 moves to urceolus 7 inner cavity timesharing, and the protruding of piston rod 1 partly will push urceolus 7 and it is deformed, and utilizes structural distortion to absorb the energy that produces when crashing.Simultaneously, the inwall at the rear portion 9 of urceolus 7 can be pushed in the front portion of piston rod 1, and it is deformed, and utilizes structural distortion to absorb the energy that produces when crashing.
The effect of structure of the present invention is:
1) when the crash fault appears in helicopter, absorb helicopter crash energy, guarantee occupant's safety.2) normally take off at helicopter, when landing, the work through the oil gas energy disperser absorbs the helicopter landing energy.Anti-crash alighting gear energy disperser endergonic structure has solved the two-chamber buffer complex structure; Produce problem difficult in maintenance; A kind of simple in structure, in light weight, good manufacturability and the low anti-crash alighting gear energy disperser endergonic structure of working service cost are provided, can be applied on other anti-crash helicopter.
Claims (1)
1. energy-absorbing structure of crashworthy landing gear damper leg; Comprise piston rod (1), oil pocket (3), poted assemblies (4), spindle (5), retardance valve (6), urceolus (7) and air cavity (8), it is characterized in that: one or both forms below this alighting gear damper leg endergonic structure adopts:
(1) is provided with convexity (2) at the middle part of piston rod (1);
(2) internal diameter at urceolus (7) rear portion (9) dwindles gradually, more and more less than the diameter of piston rod (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010229319 CN101898636B (en) | 2010-07-19 | 2010-07-19 | Energy-absorbing structure of crashworthy landing gear damper leg |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010229319 CN101898636B (en) | 2010-07-19 | 2010-07-19 | Energy-absorbing structure of crashworthy landing gear damper leg |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101898636A CN101898636A (en) | 2010-12-01 |
| CN101898636B true CN101898636B (en) | 2012-12-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010229319 Expired - Fee Related CN101898636B (en) | 2010-07-19 | 2010-07-19 | Energy-absorbing structure of crashworthy landing gear damper leg |
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| CN (1) | CN101898636B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431645A (en) * | 2011-12-06 | 2012-05-02 | 李新民 | Anti-crash one-man helicopter |
| CN103231801A (en) * | 2013-04-24 | 2013-08-07 | 哈尔滨飞机工业集团有限责任公司 | Crash preventing undercarriage damping strut energy absorption structure |
| CN108058817B (en) * | 2017-12-03 | 2021-05-11 | 中国直升机设计研究所 | Undercarriage buffer |
| CN112413029B (en) * | 2020-10-13 | 2022-01-18 | 南京航空航天大学 | Buffering and collecting integrated crushing energy-absorbing type undercarriage crash-resistant buffer |
| CN112623202B (en) * | 2020-12-11 | 2023-06-23 | 哈尔滨飞机工业集团有限责任公司 | Landing gear buffer support column lubrication support and sealing dustproof device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4405119A (en) * | 1977-12-12 | 1983-09-20 | Messier-Hispano-Bugatti | Oleopneumatic suspension with variable throttle orifices, especially for aircraft landing gear |
| CN1323705A (en) * | 2001-06-28 | 2001-11-28 | 吴怡春 | Position-inducing shock eliminator |
| CN1726355A (en) * | 2002-12-12 | 2006-01-25 | 株式会社富国 | Damper |
-
2010
- 2010-07-19 CN CN 201010229319 patent/CN101898636B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4405119A (en) * | 1977-12-12 | 1983-09-20 | Messier-Hispano-Bugatti | Oleopneumatic suspension with variable throttle orifices, especially for aircraft landing gear |
| CN1323705A (en) * | 2001-06-28 | 2001-11-28 | 吴怡春 | Position-inducing shock eliminator |
| CN1726355A (en) * | 2002-12-12 | 2006-01-25 | 株式会社富国 | Damper |
Non-Patent Citations (1)
| Title |
|---|
| 杨嘉陵 吴卫华.武装直升机抗坠毁设计研究.《机械工程学报》.2001,第37卷(第5期),1-6. * |
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| CN101898636A (en) | 2010-12-01 |
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Granted publication date: 20121226 Termination date: 20170719 |