CN102954144A

CN102954144A - Piston type reducing spring speed reduction device for catapult

Info

Publication number: CN102954144A
Application number: CN2012105151085A
Authority: CN
Inventors: 魏伯卿
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-12-05
Filing date: 2012-12-05
Publication date: 2013-03-06
Anticipated expiration: 2032-12-05
Also published as: CN102954144B

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

Piston-type variable diameter spring speed reducer for catapult

Technical field

The present invention relates to piston-type variable diameter spring speed reducer for catapult, be applicable to the speed reducer after catapult emission that aircraft carrier-based aircraft takes off, belong to the 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 the launch carrier-borne aircraft, and the device that catapult is slowed down immediately is also very important, it is a kind of for the take off catapult speed reducer of use of ship aircraft carrier carrier-borne aircraft that the present invention is exactly that science and techniques of defence expert to China provides.

Summary of the invention

The purpose 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, comprise a piston cylinder and a piston be enclosed within piston cylinder, and a spring be connected with piston, and three groups of different piston rings of sealability also are equipped with in the piston outside; It is characterized in that:

1, the spring be connected with piston, its spring steel round steel bar that forms spring passes through and is tapered, and be curled into two helical spring of a size, its thick round bar end spring is connected with piston, thin round bar end spring connects a top board, thereby the tensile strength that makes this spring is from the taper end of top board to the butt end be connected with piston, and its elastic force is grow gradually; Therefore after the catapult emission carrier-borne aircraft taken off at aircraft carrier-based aircraft, after its catapult that promotes carrier-borne aircraft is puted forth effort plate hight speed top coping, 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 the piston outside, first group of piston ring at the bottom of the most close piston cylinder, poor with the sealing of piston cylinder, and can have certain gap to make piston being subject to spring at the bottom of piston cylinder during the direction pushing, a certain amount of air penetration is arranged; 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; After such structure makes piston be subject to pressing active force from the top of spring, in direction moving process at the bottom of piston cylinder, first group of piston ring penetrates the 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 than first air cushioning ring, thereby make the buffering of piston compression air become comparatively mild.

3, the spring be 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 inboard, when the direction that makes piston be 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 the 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.

The accompanying drawing explanation

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 be enclosed within piston cylinder 1, and a spring 7 be connected with piston 2, three groups of different piston rings of sealability also are equipped with in piston 2 outsides; It is characterized in that: the spring 7 be connected with piston 2, its spring steel round steel bar that forms spring 7 passes through and is tapered, and be curled into two helical spring of a size, its thick round bar end spring is connected with piston 2, thin round bar end spring connects a top board 9, thereby the tensile strength that makes this spring 7 is from the taper end of top board 9 to the butt end be connected with piston 2, and its elastic force is grow gradually; Therefore after the catapult emission carrier-borne aircraft taken off at aircraft carrier-based aircraft, after its catapult that promotes carrier-borne aircraft is puted forth effort 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 can have certain gap to make piston 2 when being subject to spring 7 and pushing to 1 end of piston cylinder direction, a certain amount of air penetration is arranged; 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; After such structure makes piston 2 be subject to pressing active force from the top of spring 7, in 1 end of piston cylinder direction moving process, first group of piston ring 3 penetrates the 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 than first air cushioning ring, thereby make the compressed-air actuated buffering of piston 2 become comparatively mild.

The spring 7 be 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. piston-type variable diameter spring speed reducer for catapult, comprise a piston cylinder (1) and a piston (2) be enclosed within piston cylinder (1), and a spring (7) be connected with piston (2), three groups of different piston rings of sealability also are equipped with in piston (2) outside; It is characterized in that: the spring (7) be connected with piston (2), its spring steel round steel bar that forms spring (7) passes through and is tapered, and be curled into two helical spring of a size, its thick round bar end spring is connected with piston (2), thin round bar end spring connects a top board (9), thereby the tensile strength that makes this spring (7) is from the taper end of top board (9) to the butt end be connected with piston (2), and its elastic force is grow gradually; Therefore after the catapult emission carrier-borne aircraft taken off at aircraft carrier-based aircraft, after its catapult that promotes carrier-borne aircraft is puted forth effort 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.

2. piston-type variable diameter spring speed reducer for catapult as claimed in claim 1, it is characterized in that: 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 can have certain gap to make piston (2) when being subject to spring (7) and pushing to piston cylinder (1) end direction, a certain amount of air penetration is arranged, 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), after such structure makes piston (2) be subject to pressing active force from the top of spring (7), in piston cylinder (1) end direction moving process, first group of piston ring (3) penetrates the 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 than first air cushioning ring, thereby make the compressed-air actuated buffering of piston (2) become comparatively mild.

3. piston-type variable diameter spring speed reducer for catapult as claimed in claim 1, it is characterized in that: the spring (7) be 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 that these three springs (7) are crooked 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 (10) is connected with piston (2), and the most weak soft power spring (14) of spring force is connected with top board (9).