CN102954144B - Piston type reducing spring speed reduction device for catapult - Google Patents
Piston type reducing spring speed reduction device for catapult Download PDFInfo
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- CN102954144B CN102954144B CN201210515108.5A CN201210515108A CN102954144B CN 102954144 B CN102954144 B CN 102954144B CN 201210515108 A CN201210515108 A CN 201210515108A CN 102954144 B CN102954144 B CN 102954144B
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- piston
- spring
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- catapult
- ring
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Abstract
The invention relates to a piston type reducing spring speed reduction device for a catapult. The speed reduction device comprises a piston cylinder, a piston and a spring, wherein the spring is connected with the piston, and the outside of the piston is provided with three groups of piston rings different in sealing performance. The speed reduction device is characterized in that the spring is connected with the piston, a spring steel round steel strip forming the spring is gradually reduced from one end to the other end, and is coiled into a cylindrical spring with two same ends, the spring at the thick round steel strip end is connected with the piston, the spring at the thin round steel strip end is connected with an ejection plate, and the elastic strength of the spring is gradually increased from the thin end connected with the ejection plate to the thick end connected with the piston. Therefore, after a ship aircraft is launched by the catapult taking off the ship aircraft of an aircraft carrier, a bearing plate of the catapult for pushing the ship aircraft pushes against the ejection plate at high speed, the ejection plate is forwards pushed, the counteraction force of the spring on the bearing plate of the catapult is gradually increased, and then the impact on the bearing plate of the catapult is more stable.
Description
Technical field
The present invention relates to catapult piston-type variable diameter spring speed reducer, be applicable to the speed reducer after catapult transmitting that aircraft carrier-based aircraft takes off, belong to science and techniques of defence field.
Background technique
The catapult that aircraft carrier-based aircraft takes off is the proprietary technology of the U.S., although " Liaoning number " of China does not adopt catapult, but catapult takes off and can save a large amount of oil plants, thereby can not only strengthen the carrying capacity of carrier-borne aircraft, but also can increase the voyage of carrier-borne aircraft, therefore, the thinking of development shipborne aircraft catapult is forever there is no mistake; But carrier-based aircraft ejector is after launch carrier-borne aircraft, and it is also very important making the device that catapult slows down immediately, the present invention provides a kind of for the take off catapult speed reducer of use of ship aircraft carrier carrier-borne aircraft to the science and techniques of defence expert of China.
Summary of the invention
The object of this invention is to provide a kind of catapult piston-type variable diameter spring speed reducer simple in structure, multi-stage speed-reducing.
Piston-type variable diameter spring speed reducer for catapult, comprises a piston cylinder and a piston being enclosed within piston cylinder, and a spring being connected with piston, and three groups of different piston rings of sealability are also equipped with in piston outside; It is characterized in that:
1, the spring being connected with piston, the spring steel round steel bar of composition spring passes through and is tapered, and be curled into two helical spring of a size, the thick round bar end spring of helical spring is connected with piston, thin round bar end spring connects a top board, thereby make the tensile strength of this spring from the taper end of top board to the butt end being connected with piston, elastic force is grow gradually; Therefore after the catapult transmitting carrier-borne aircraft taking off at aircraft carrier-based aircraft, the catapult that promotes carrier-borne aircraft is puted forth effort after the coping of plate hight speed top, along with pushing top board forward, catapult is puted forth effort the suffered spring reaction power of plate and is also become gradually large, comparatively mild thereby the impact that makes catapult put forth effort plate becomes.
2, three groups of piston rings in piston outside, first group of piston ring at the bottom of the most close piston cylinder, poor with the sealing of piston cylinder, and make the sealing of first group of piston ring and piston cylinder can have certain gap to make piston being subject to spring at the bottom of piston cylinder when direction pushing, there is a certain amount of air penetration, the 3rd group of piston ring of close spring, best with the sealing of piston cylinder, second group of piston ring between first group of piston ring and the 3rd group of piston ring, and the sealing of piston cylinder also occupy between first group of piston ring and the 3rd group of piston ring, from first group of piston ring to second group of piston ring, again to the 3rd group of piston ring, their sealing makes piston be subject to pressing after active force from the top of spring by having differed from such structure, in direction moving process at the bottom of piston cylinder, first group of piston ring penetrates part air and enters between first group of piston ring and second group of piston ring, form an air cushioning ring, a small amount of air penetration of second group of piston ring enters between second group of piston ring and the 3rd group of piston ring, also form the air cushioning ring that second pressure is little compared with first air cushioning ring, it is comparatively mild that thereby the buffering that makes piston compression air becomes.
3, the spring being connected with piston can be also different by thickness and its spring force also different three springs be composed in series, the spring ring excircle of these three spring bendings is the same, and its serial fashion be by spring force by by force to a little less than be composed in series, the brute spring that spring force is the strongest is connected with piston, and the most weak soft power spring of spring force is connected with top board.
The present invention compared with prior art has the following advantages:
1, different because of the sealing of three groups of piston rings and piston cylinder inner side, when the direction that piston is beared down on one at the bottom of piston cylinder moves, automatically forming two gas densities is the different air cushioning ring of gas pressure, with the compressed stationarity of buffer air.
2, spring itself is made from top board end to the structure of strengthening gradually with its spring force of piston connecting end, so put forth effort plate hight speed top while being pressed onto spring when catapult, its suffered spring reaction power strengthens gradually, so shock-absorbing capacity is relatively good.
Brief description of the drawings
Fig. 1 is the axial section schematic diagram of the embodiment of the present invention;
Fig. 2 is three grades of spring generalized sections embodiment illustrated in fig. 1.
In Fig. 1-2: 1, piston cylinder 2, piston 3, first group of piston ring 4, second group of piston ring 5, the 3rd group of piston ring 6, spring piston connecting end 7, spring 8, spring top board connecting end 9, top board 10, brute spring 11, brute spring and middle power spring coupling plate 12, middle power spring 13, middle power spring and soft power spring coupling plate 14, soft power spring.
Embodiment
In the embodiment shown in Fig. 1-2: piston-type variable diameter spring speed reducer for catapult, comprise a piston cylinder 1 and a piston 2 being enclosed within piston cylinder 1, and a spring 7 being connected with piston 2, three groups of different piston rings of sealability are also equipped with in piston 2 outsides; It is characterized in that: the spring 7 being connected with piston 2, the spring steel round steel bar of composition spring 7 passes through and is tapered, and be curled into two helical spring of a size, the thick round bar end spring of helical spring is connected with piston 2, thin round bar end spring connects a top board 9, thereby make the tensile strength of this spring 7 from the taper end of top board 9 to the butt end being connected with piston 2, elastic force is grow gradually; Therefore after the catapult transmitting carrier-borne aircraft taking off at aircraft carrier-based aircraft, the catapult that promotes carrier-borne aircraft is puted forth effort after plate hight speed top coping 9, along with pushing top board 9 forward, catapult is puted forth effort the suffered spring of plate 7 reaction forces and is also become gradually large, comparatively mild thereby the impact that makes catapult put forth effort plate becomes.
Three groups of piston rings in piston 2 outsides, first group of piston ring 3 at 1 end of the most close piston cylinder, poor with the sealing of piston cylinder 1, and make first group of piston ring 3 and the sealing of piston cylinder 1 can have certain gap to make piston 2 in the time being subject to spring 7 and pushing to 1 end of piston cylinder direction, there is a certain amount of air penetration, the 3rd group of piston ring 5 of the most close spring 7, best with the sealing of piston cylinder 1, second group of piston ring 4 between first group of piston ring 3 and the 3rd group of piston ring 5, and the sealing of piston cylinder 1 also occupy between first group of piston ring 3 and the 3rd group of piston ring 5, from 3 to second groups of piston rings 4 of first group of piston ring, again to the 3rd group of piston ring 5, their sealing makes piston 2 be subject to pressing after active force from the top of spring 7 by having differed from such structure, in 1 end of piston cylinder direction moving process, first group of piston ring 3 penetrates part air and enters between first group of piston ring 3 and second group of piston ring 4, form an air cushioning ring, a small amount of air penetration of second group of piston ring 4 enters between second group of piston ring 4 and the 3rd group of piston ring 5, also form the air cushioning ring that second pressure is little compared with first air cushioning ring, thereby make the compressed-air actuated buffering of piston 2 become comparatively mild.
The spring 7 being connected with piston 2 can be also different by thickness and its spring force also different three springs 7 be composed in series, the spring ring excircle of these three spring 7 bendings is the same, and its serial fashion be by spring force by by force to a little less than be composed in series, the brute spring 10 that spring force is the strongest is connected with piston 2, and the most weak soft power spring 14 of spring force is connected with top board 9.
Claims (1)
1. piston-type variable diameter spring speed reducer for catapult, comprise a piston cylinder (1) and a piston (2) being enclosed within piston cylinder (1), and a spring (7) being connected with piston (2), three groups of different piston rings of sealability are also equipped with in piston (2) outside, it is characterized in that: the spring (7) being connected with piston (2), the spring steel round steel bar of composition spring (7) passes through and is tapered, and be curled into two helical spring of a size, the thick round bar end spring of helical spring is connected with piston (2), thin round bar end spring connects a top board (9), thereby make the tensile strength of this spring (7) from the taper end of top board (9) to the butt end being connected with piston (2), elastic force is grow gradually, therefore after the catapult transmitting carrier-borne aircraft taking off at aircraft carrier-based aircraft, the catapult that promotes carrier-borne aircraft is puted forth effort after plate hight speed top coping (9), along with pushing top board (9) forward, catapult is puted forth effort the suffered spring of plate (7) reaction force and is also become gradually large, comparatively mild thereby the impact that makes catapult put forth effort plate becomes, three groups of piston rings in piston (2) outside, first group of piston ring (3) at the most close piston cylinder (1) end, poor with the sealing of piston cylinder (1), and the sealing that makes first group of piston ring (3) and piston cylinder (1) can have certain gap to make piston (2) in the time being subject to spring (7) and pushing to piston cylinder (1) end direction, there is a certain amount of air penetration, the 3rd group of piston ring (5) of the most close spring (7), best with the sealing of piston cylinder (1), second group of piston ring (4) between first group of piston ring (3) and the 3rd group of piston ring (5), and the sealing of piston cylinder (1) also occupy between first group of piston ring (3) and the 3rd group of piston ring (5), from first group of piston ring (3) to second group of piston ring (4), again to the 3rd group of piston ring (5), their sealing makes piston (2) be subject to pressing after active force from the top of spring (7) by having differed from such structure, in piston cylinder (1) end direction moving process, first group of piston ring (3) penetrates part air and enters between first group of piston ring (3) and second group of piston ring (4), form an air cushioning ring, a small amount of air penetration of second group of piston ring (4) enters between second group of piston ring (4) and the 3rd group of piston ring (5), also form the air cushioning ring that second pressure is little compared with first air cushioning ring, thereby make the compressed-air actuated buffering of piston (2) become comparatively mild.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210515108.5A CN102954144B (en) | 2012-12-05 | 2012-12-05 | Piston type reducing spring speed reduction device for catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210515108.5A CN102954144B (en) | 2012-12-05 | 2012-12-05 | Piston type reducing spring speed reduction device for catapult |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102954144A CN102954144A (en) | 2013-03-06 |
| CN102954144B true CN102954144B (en) | 2014-08-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210515108.5A Expired - Fee Related CN102954144B (en) | 2012-12-05 | 2012-12-05 | Piston type reducing spring speed reduction device for catapult |
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| Country | Link |
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| CN (1) | CN102954144B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742028A (en) * | 2017-04-06 | 2017-05-31 | 重庆科技学院 | The apparatus and method of two-level spring joint ejection carrier-borne aircraft |
| CN107600458A (en) * | 2017-09-01 | 2018-01-19 | 西北工业大学 | Inertial load simulation test device and system |
| JP7328996B2 (en) | 2018-05-25 | 2023-08-17 | グラコ ミネソタ インコーポレーテッド | pneumatic surge suppressor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4318536A (en) * | 1979-02-23 | 1982-03-09 | Fritz Bauer & Sohne Ohg | Axially adjustable pneumatic spring |
| CN2334637Y (en) * | 1998-10-15 | 1999-08-25 | 张茂 | Collision-resistant device for moving carrier |
| CN2423140Y (en) * | 2000-05-30 | 2001-03-14 | 丁建新 | Motor vehicle vibration damper |
| EP1769176B1 (en) * | 2004-07-13 | 2007-12-19 | Trelleborg Sealing Solutions Germany GmbH | Seal arrangement |
| CN101210599A (en) * | 2006-12-31 | 2008-07-02 | 天津市锋麒减震器有限公司 | Motorcycle shock absorber |
| CN201382115Y (en) * | 2009-02-19 | 2010-01-13 | 山西太钢不锈钢股份有限公司 | Buffer device |
| CN202914617U (en) * | 2012-12-05 | 2013-05-01 | 魏伯卿 | Piston-type gradual force spring speed reducer for ejector speed reduction |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6049145A (en) * | 1983-08-25 | 1985-03-18 | Kayaba Ind Co Ltd | Suspension spring of hydraulic shock absorber |
-
2012
- 2012-12-05 CN CN201210515108.5A patent/CN102954144B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4318536A (en) * | 1979-02-23 | 1982-03-09 | Fritz Bauer & Sohne Ohg | Axially adjustable pneumatic spring |
| CN2334637Y (en) * | 1998-10-15 | 1999-08-25 | 张茂 | Collision-resistant device for moving carrier |
| CN2423140Y (en) * | 2000-05-30 | 2001-03-14 | 丁建新 | Motor vehicle vibration damper |
| EP1769176B1 (en) * | 2004-07-13 | 2007-12-19 | Trelleborg Sealing Solutions Germany GmbH | Seal arrangement |
| CN101210599A (en) * | 2006-12-31 | 2008-07-02 | 天津市锋麒减震器有限公司 | Motorcycle shock absorber |
| CN201382115Y (en) * | 2009-02-19 | 2010-01-13 | 山西太钢不锈钢股份有限公司 | Buffer device |
| CN202914617U (en) * | 2012-12-05 | 2013-05-01 | 魏伯卿 | Piston-type gradual force spring speed reducer for ejector speed reduction |
Non-Patent Citations (1)
| Title |
|---|
| JP昭60-49145A 1985.03.18 |
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| CN102954144A (en) | 2013-03-06 |
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