CN203892441U - Oil needle and landing gear buffer with oil needle - Google Patents
Oil needle and landing gear buffer with oil needle Download PDFInfo
- Publication number
- CN203892441U CN203892441U CN201420188227.9U CN201420188227U CN203892441U CN 203892441 U CN203892441 U CN 203892441U CN 201420188227 U CN201420188227 U CN 201420188227U CN 203892441 U CN203892441 U CN 203892441U
- Authority
- CN
- China
- Prior art keywords
- piston
- urceolus
- plunger
- spindle
- piston rod
- 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 - Lifetime
Links
- 239000000872 buffer Substances 0.000 title claims abstract description 45
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 230000001681 protective effect Effects 0.000 abstract 1
- 238000001179 sorption measurement Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 239000007853 buffer solution Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Abstract
The utility model provides an oil needle and a landing gear buffer with the oil needle. The landing gear buffer includes an outer cylinder (1), a plunger (2), a piston rod (3), the oil needle (4), an anti-resistance valve (5), and a travelling piston (6), the travelling piston (6) is arranged at the upper part of the outer cylinder (1), the upper side of the travelling piston (6) is filled with oil (7), the plunger (2) of the outer cylinder (1) is fixedly connected in the outer cylinder (1) at the lower side of the travelling piston (6), the upper end of the piston rod (3) is connected with the plunger (2), the lower end of the piston rod (3) is connected with the outer cylinder (1), the anti-resistance valve (5) is arranged between the outer cylinder (1) and the piston rod (3), the oil needle (4) is arranged inside the piston rod (3), and the upper end of the oil needle (4) is connected with the plunger (2). The landing gear buffer provided meets the large-power adsorption requirement of vertical landing of an airplane, has a good protective effect on flight equipment, improves safety and comfortableness, and has great economic and social values.
Description
Technical field
The utility model relates to structural design and the application of spindle and undercarriage buffer, and a kind of spindle of large merit amount and undercarriage buffer with this spindle of being applicable to is provided especially.
Background technique
When aircraft landing, with respect to the impact on ground, and suffered collision while moving on uneven airport, is mainly born by undercarriage buffer system.Buffering essence be exactly the kinetic energy dissipation of aircraft in buffer system.Undercarriage buffer system is made up of tire and buffer two-part.The pattern of undercarriage buffer generally has: steel spring buffer, rubber spring buffer, air type buffer, fluid air type buffer and full fluid formula buffer.
The design of undercarriage buffer, the requirement that only merit amount is landinged impact in satisfied absorption is inadequate, and considers how more effective reduction taxing load is also a major issue.The application of two-chamber buffer, exactly in order to solve the problem that reduces taxing load.
At present, domestic undercarriage two-chamber buffer is all the buffers that adapt to little subsidence velocity, little merit amount, can not meet rapid sink rate.
Spindle, as undercarriage buffer, in undercarriage buffer working procedure, plays sizable effect, and people urgently wish to obtain a kind of spindle and undercarriage buffer that meets rapid sink rate.
Model utility content
The purpose of this utility model is to provide the good spindle of a kind of technique effect and the undercarriage buffer with this spindle.
Described spindle is arranged in undercarriage buffer, and spindle middle part is the tubular structure of hollow cavity 41, is provided with oil through 42 on the sidewall of described spindle.
Described undercarriage buffer is constructed as follows: urceolus 1, plunger 2, piston rod 3, spindle 4, anti-drag valve 5 and the piston 6 that moves about; The described piston 6 that moves about is positioned at urceolus 1 top, and piston 6 upsides that move about are filled with oil 7; The plunger 2 that forms urceolus 1 is fixedly connected in the urceolus 1 of piston 6 downsides that move about, piston rod 3 upper ends are connected with plunger 2, piston rod 3 lower ends are connected with urceolus 1, described anti-drag valve 5 is between urceolus 1 and piston rod 3, spindle 4 is positioned at piston rod 3 inside, and spindle 4 upper ends are connected with plunger 2, lower end is connected with piston rod 3; Described urceolus 1 under-filled has oil 7, and the height of oil 7 is higher than plunger 2 bottoms; Described buffer has two-stage air chamber, and the piston 6 that moves about forms high pressure air cavity with urceolus 1; Move about piston 6, plunger 2 and urceolus 1 forms low pressure air cavity.
The described piston 6 that moves about is specially semicircular structure; Load and good sealing effect, meet the requirement of large merit amount speed.
Described undercarriage buffer, referring to accompanying drawing 1, buffer has two-stage air chamber, forms high pressure air cavity, that is: the chamber that move about piston 6 and urceolus 1 form; Low pressure air cavity, that is: move about piston 6, plunger 2 and and the chamber that forms of urceolus 1; Main oil pocket, that is: the chamber that spindle 4, plunger 2 and piston rod 3 form; Oil back chamber.That is: the chamber that anti-drag valve 5, piston rod 3 and urceolus 1 form;
The cushion stroke that has increased buffer, reaches 600mm; Optimize initial stowing pressure and filling volume, and adopt the cavity spindle that is provided with oil through.
The large merit amount that described undercarriage buffer has solved VTOL aircraft requirement absorbs requirement, respond well to the protection of flight equipment, has improved Security and comfort level, has larger economy and social value.
Brief description of the drawings
Fig. 1 is undercarriage buffer structural representation;
Fig. 2 is the positive stroke work of undercarriage buffer schematic diagram;
Fig. 3 is undercarriage buffer revesal work schematic diagram;
Fig. 4 is spindle structural representation.
Embodiment
Embodiment 1
Described spindle is arranged in undercarriage buffer, and spindle middle part is the tubular structure of hollow cavity 41, is provided with oil through 42 on the sidewall of described spindle.
Described undercarriage buffer is constructed as follows: urceolus 1, plunger 2, piston rod 3, spindle 4, anti-drag valve 5 and the piston 6 that moves about; The described piston 6 that moves about is positioned at urceolus 1 top, and piston 6 upsides that move about are filled with oil 7; The plunger 2 that forms urceolus 1 is fixedly connected in the urceolus 1 of piston 6 downsides that move about, piston rod 3 upper ends are connected with plunger 2, piston rod 3 lower ends are connected with urceolus 1, described anti-drag valve 5 is between urceolus 1 and piston rod 3, spindle 4 is positioned at piston rod 3 inside, and spindle 4 upper ends are connected with plunger 2, lower end is connected with piston rod 3; Described urceolus 1 under-filled has oil 7, and the height of oil 7 is higher than plunger 2 bottoms; Described buffer has two-stage air chamber, and the piston 6 that moves about forms high pressure air cavity with urceolus 1; Move about piston 6, plunger 2 and urceolus 1 forms low pressure air cavity.
The described piston 6 that moves about is specially semicircular structure; Load and good sealing effect, meet the requirement of large merit amount speed.
Described undercarriage buffer, referring to accompanying drawing 1, buffer has two-stage air chamber, forms high pressure air cavity, that is: the chamber that move about piston 6 and urceolus 1 form; Low pressure air cavity, that is: move about piston 6, plunger 2 and and the chamber that forms of urceolus 1; Main oil pocket, that is: the chamber that spindle 4, plunger 2 and piston rod 3 form; Oil back chamber.That is: the chamber that anti-drag valve 5, piston rod 3 and urceolus 1 form;
The cushion stroke that has increased buffer, reaches 600mm; Optimize initial stowing pressure and filling volume, and adopt the cavity spindle that is provided with oil through.
The large merit amount that described undercarriage buffer has solved VTOL aircraft requirement absorbs requirement, respond well to the protection of flight equipment, has improved Security and comfort level, has larger economy and social value.
Claims (3)
1. a undercarriage buffer spindle, described spindle is arranged in undercarriage buffer, it is characterized in that: the tubular structure that described spindle middle part is hollow cavity (41), is provided with oil through (42) on the sidewall of described spindle.
2. with a undercarriage buffer for spindle as claimed in claim 1, it is characterized in that: described undercarriage buffer is constructed as follows: urceolus (1), plunger (2), piston rod (3), spindle (4), anti-drag valve (5) and the piston that moves about (6); The described piston that moves about (6) is positioned at urceolus (1) top, and the piston that moves about (6) upside is filled with oil (7); The plunger (2) that forms urceolus (1) is fixedly connected in the urceolus (1) of the piston that moves about (6) downside, piston rod (3) upper end is connected with plunger (2), piston rod (3) lower end is connected with urceolus (1), described anti-drag valve (5) is positioned between urceolus (1) and piston rod (3), spindle (4) is positioned at piston rod (3) inside, and spindle (4) upper end is connected with plunger (2), lower end is connected with piston rod (3); Described urceolus (1) under-filled has oil (7), and the height of oil (7) is higher than plunger (2) bottom; Described buffer has two-stage air chamber, and the piston that moves about (6) forms high pressure air cavity with urceolus (1); Piston (6), plunger (2) and urceolus (1) formation low pressure air cavity move about.
3. undercarriage buffer as claimed in claim 2, is characterized in that: described in the piston (6) that moves about be specially semicircular structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420188227.9U CN203892441U (en) | 2014-04-17 | 2014-04-17 | Oil needle and landing gear buffer with oil needle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420188227.9U CN203892441U (en) | 2014-04-17 | 2014-04-17 | Oil needle and landing gear buffer with oil needle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203892441U true CN203892441U (en) | 2014-10-22 |
Family
ID=51718849
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420188227.9U Expired - Lifetime CN203892441U (en) | 2014-04-17 | 2014-04-17 | Oil needle and landing gear buffer with oil needle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203892441U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106122349A (en) * | 2016-08-23 | 2016-11-16 | 中航飞机起落架有限责任公司 | A kind of fluid damping mechanism of buffer unit |
| CN108454834A (en) * | 2018-06-11 | 2018-08-28 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter buffer-type undercarriage |
| CN111536189A (en) * | 2020-04-22 | 2020-08-14 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111677809A (en) * | 2020-06-11 | 2020-09-18 | 南京航空航天大学 | Oil-gas separation type variable oil hole combined crash-resistant buffer |
-
2014
- 2014-04-17 CN CN201420188227.9U patent/CN203892441U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106122349A (en) * | 2016-08-23 | 2016-11-16 | 中航飞机起落架有限责任公司 | A kind of fluid damping mechanism of buffer unit |
| CN108454834A (en) * | 2018-06-11 | 2018-08-28 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter buffer-type undercarriage |
| CN108454834B (en) * | 2018-06-11 | 2023-05-16 | 中国人民解放军总参谋部第六十研究所 | Buffering type landing gear for unmanned helicopter |
| CN111536189A (en) * | 2020-04-22 | 2020-08-14 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111536189B (en) * | 2020-04-22 | 2022-04-22 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111677809A (en) * | 2020-06-11 | 2020-09-18 | 南京航空航天大学 | Oil-gas separation type variable oil hole combined crash-resistant buffer |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141022 |