CN101186235A - Ejector with enclosed cylinder structure - Google Patents
Ejector with enclosed cylinder structure Download PDFInfo
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- CN101186235A CN101186235A CNA2006101526452A CN200610152645A CN101186235A CN 101186235 A CN101186235 A CN 101186235A CN A2006101526452 A CNA2006101526452 A CN A2006101526452A CN 200610152645 A CN200610152645 A CN 200610152645A CN 101186235 A CN101186235 A CN 101186235A
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Abstract
The invention discloses an enclosed cylinder structure catapult, mainly consisting of an ejection cylinder, a piston, a cylinder head, a telescopic sealing device, a high-strength steel cable and a reciprocating vehicle; wherein, the ejection cylinder is in enclosed pipe-shaped structure consisting of a plurality of cylinder sections which are connected with flanges; a cylinder head is arranged at the starting end of the ejection cylinder where an air inlet valve and a steel cable hole is arranged; the telescopic sealing device consists of sleeves telescopically sleeved together from small internal diameter to large internal diameter; the head end of the most-inner sleeve is arranged on the piston and the tail end of the most-outer sleeve extends out of the cylinder through the steel cable hole on the cylinder head. One end of the high strength steel cable passes through the telescopic sealing device and is connected with the piston in the cylinder by the steel cable hole in the cylinder head; the other end of the high strength steel cable is connected with the reciprocating vehicle; the invention adopts the enclosed cylinder, the high strength steel cable and the telescopic sealing device, etc., therefore, the invention has the advantages of high strength, light structural weight, simple sealing, high reliability and low production cost.
Description
Technical field
The present invention relates to the air cylinder structure catapult technique, particularly a kind of ejector with enclosed cylinder structure.
Background technology
The air cylinder structure ejector is used for fixing the wing aircraft and launches, and it is accelerated to more than the takeoff speed from quiescence.At present, practical in the world, failure-free, high-octane ejector only have Americanized steam catapult.Steam catapult can reach the kinetic energy that high pressure steam can be converted to heavily loaded fixed-wing aircraft.
Every steam catapult is provided with the left and right cylinder that launches of the parallel installation of two rows.Every row launches cylinder and is made up of the cylinder that launches that flange connects the more piece two ends.Launching the joint number of cylinder is determined by the total length of steam catapult.
What steam catapult adopted is open cylinder.Launch cylinder and on casing wall, hold, along the longitudinal fluting from initiating terminal to end.It is fan-shaped cylinder cover that the top of groove is provided with cross-sectional plane, and cylinder cover is used to prevent to launch cylinder inner high voltage steam pressure radial scatter as pressing plate sealing together.Certain space is left with the upper limb that launches the fluting of cylinder in the cylinder cover below, is used to install the cylinder sealing band of being made by ductile metal, prevents that high pressure steam from leaking from launch cylinder.
Left and right two rows launch respectively the piston component that is parallel to each other in the cylinder.The top of left and right piston component is fastened and is connected to tie-beam and sealing band guide piece.Tie-beam is to connect left and right piston component by the fluting that launches on the cylinder, travels forward along fluting with piston.The propelling thrust that high pressure steam acts on the piston is to be delivered to reciprocal car and aircraft by the tie-beam between the left and right piston.When moving in piston component is launching cylinder, the sealing band guides earlier lifts sealing band, and after the piston tie-beam passed through under the sealing band, the sealing band guides made sealing band be returned on the sealing band seat again.In ejection process, can reduce the leakage of steam like this during piston-advance.
Tie-beam between the left and right piston links to each other with reciprocal car, and back and forth the frame of pulling of car is meshed with piston ejector ram, ejector piston on the aircraft nose-gear.In ejection process, along launching the proal piston of cylinder, by tie-beam and reciprocal car towed flight device.
There is following defective in existing steam catapult:
1, to launch cylinder structure weight big for open type, poor reliability.It is very big that open type is launched the hoop-stress that cylinder work the time bears, as cylinder diameter be 457mm launch cylinder under the effect of 70bar steam, every meter cylinder side direction spreading power reaches 3150KN, makes to launch cylinder and can produce bigger outer bulging deformation at opening part.For guaranteeing that cylinder has enough structural strengths, the open type cylinder must have enough big structural weight; In addition, open type is launched cylinder along slotting on the whole cylinder length, when being used for piston and sliding in cylinder, allows the bar (or beam) that connects piston transmit propelling thrust by fluting.In order to make stress balance, have to adopt open cylinder double, that be arranged in parallel, thereby increased structural weight, reduced reliability.
2, open type is launched cylinder sealing difficulty, poor stability.Because open type is launched cylinder and is slotted on whole cylinder length, exist the effect of high voltage power gas radial pressure at the fluting place, make cylinder produce bigger distortion, thereby need guarantee the seal request that open cylinder is the most basic with very difficult static seal technology.Particularly the tie-beam between the left and right piston component is by launching the cylinder fluting, and when the sealing band that backs down the cylinder fluting travelled forward, the dynamic seal of cylinder openings was higher to the requirement of packing technique;
Summary of the invention
The purpose of this invention is to provide a kind of new air cylinder structure catapult-launching gear, this device hermetically-sealed construction is simple, safe and reliable, in light weight.
Therefore the present invention proposes a kind of ejector with enclosed cylinder structure.This ejector is formed by launching cylinder, piston, cylinder head, telescopic sealing arrangement, high strength cable wire and reciprocal car.The described cylinder that launches is closed tubular structure, is made up of the more piece cylinder, is connected with flange by this, has lubricating oil cloth oilhole on the inwall of cylinder launching, and is used to inject lubricating oil, to reduce friction drag between piston and the cylinder wall; Described cylinder head is placed in the described cylinder initiating terminal that launches, and it is provided with air inlet valve and cable wire hole; Telescopic sealing arrangement is made of ascending, the telescopic sleeve pipe that connects together of more piece internal diameter, and innermost layer sleeve pipe head end is fixedly linked by flange and piston, and outermost layer sleeve pipe tail end stretches out cylinder by the cable wire hole on the cylinder head; High strength cable wire one end is by the cable wire hole on the cylinder head, and the piston in passing telescopic sealing arrangement and launching cylinder links to each other, and the other end joins with reciprocal car, and cable wire can not touch the power gas that launches of High Temperature High Pressure under the protection of sleeve pipe.Described telescopic sealing arrangement sleeve pipe head ends at different levels are provided with flange, are provided with external bushing on the tail end periphery, except that first order sleeve pipe, are provided with inner covering, side seal and annual spring in the head end pipe.
In order to suppress telescopic sealing arrangement sleeve pipe and cable wire sagging and swaying because of gravity, in launching cylinder, below the telescopic sealing arrangement, be provided with to be extended down to from cylinder head and launch the fixing guide carriage of cylinder tail end, the flange cylindrical of sleeve pipe can be limited in sliding in the guide carriage.Under the constraint of guide carriage, sleeve pipe and cable wire can not produce serious sagging and swaying.The gland packing letter that is complementary with the guide carriage shape of cross section is housed on the piston, during piston advances forward, the friction pair of piston and guide carriage can keep good sealing, and the non-power face to piston during from then on the high temperature and high pressure gas that acts on the piston power face can not seal is leaked.
When piston launched cylinder in the promotion lower edge of launching power gas and travels forward, piston drags reciprocal car by the high strength cable wire and aircraft travels forward together.Simultaneously, the sleeve pipe of fastening the telescopic sealing arrangement innermost layer that is connected together with piston also travels forward with piston.When the tail end of innermost layer sleeve pipe arrived the head end of the second joint sleeve pipe, the lining of its tail end contacted with the annual spring of the second joint sleeve pipe head end, and buffering drives the second joint sleeve pipe and travels forward.Along with piston constantly travels forward, the second joint sleeve pipe drives the 3rd joint sleeve pipe and stretches out forward successively, and the 3rd joint sleeve pipe drives the 4th joint sleeve pipe and stretches out forward, finishes until launching stroke.At this moment, aircraft has reached takeoff speed and has broken away from reciprocal car, and stop motion after piston then slows down under the inhibition of the energy disperser that launches the cylinder tail end stops after outermost sleeve pipe tail end also arrives at cylinder head.When resetting, back and forth car begins to reset by the sleeve pipe that cable wire drags piston and innermost layer, when the sleeve pipe of innermost layer was fully retracted in the second joint sleeve pipe, the flange of innermost layer sleeve pipe head end contacted with the head end flange of the second joint sleeve pipe, drove the second joint sleeve pipe and retracted in the 3rd joint sleeve pipe; Sleeve pipe bounces back successively, turns back to the initiating terminal that launches in the cylinder until piston.
Compared with prior art the present invention has following characteristics:
1, the present invention is a not opening of closed type structure air cylinder structure, the shape of cross section symmetry, and the primary member inwall is the osed top face of cylinder, thereby the intensity height, lightweight construction, productive costs is low, the reliability height, hermetically-sealed construction is simple.
2, the present invention adopts cable wire to connect piston and reciprocal car, and ejector and the sliding formula flying-off deck that jumps are combined, and improves the take-off weight of aircraft;
3, the present invention adopts the closed type structure cylinder, can be by increasing cylinder bore diameter, and ejection force is increased by the proportionate relationship of cylinder bore diameter square, thereby adopt single cylinder to meet the demands, and then can reduce framing member.
Description of drawings
Fig. 1 is an enclosed cylinder ejector initial position scheme drawing of the present invention;
Fig. 2 is an enclosed cylinder ejector ejection process scheme drawing of the present invention;
Fig. 3 is a telescopic schematic diagram of sealing device of the present invention;
Fig. 4 is analog bracket of the present invention and Sealed casing pipe cross section structure scheme drawing.
Among the figure: 10. launch cylinder, 12. cylinder heads, 13. air inlet valves, 14. the cylinder head sealing arrangement, 14-1. seal ring, 20. pistons, 21. piston ring, 30. high strength cable wires, 50. guide carriages (cylinder interior branch), 51. guide carriage (the outer part of cylinder), 52. piston packing compression gland, 60. telescopic sealing arrangements, 61 (61-1). first order sleeve pipe, 62 (62-1). second stage sleeve pipe, 63 (63-1). third stage sleeve pipe, 64 (64-1). fourth stage sleeve pipe.
The specific embodiment
Below in conjunction with accompanying drawing and the specific embodiment the present invention is done and to describe in further detail.With reference to Fig. 1, the present invention is used to launch aircraft, mainly forms by launching cylinder 10, cylinder head 12, piston 20, high strength cable wire 30 and telescopic sealing arrangement 60.Wherein launch cylinder 10, cylinder head 12, piston 20 and telescopic sealing arrangement 60 and constitute a fully enclosed space.Launch power gas through launch control cock, air inlet valve 13 is spurted into and is launched cylinder 10, acts on the piston 20, promote piston 20 and advance.The core that connects the high strength cable wire 30 of piston 20 and reciprocal car is a steel wire.The intensity of this cable wire can reach 1970 ~ 2170MPa, far above steel structure intensity, can reach 4 as the minimum breaking force of the cable wire of diameter 60mm, and 000KN approximately is 4 times of the maximum ejection force 220klbs of existing steam catapult.
With reference to Fig. 1,2, the not opening of cylinder 10 that launches of the present invention is the osed top tubular structure, and thin wall thickness just can bear the high pressure of power gas.Usually adopt single cylinder to satisfy and launch requirement, launch the ejector that cylinder bore is 650mm, launch the air cylinder structure ejector with regard to the C-17-1 type open type that alternative two row's cylinder diameters with identical ejection force are 457mm as single closed type structure.The single-unit cylinder can adopt welded tube technology to make blank, and two ends are welded flange, and the length of every displacements of cylinders just is decided to be 6 meters, is easy to make and processing.Two displacements of cylinders connect with hydraulic bolt, and concentric concavo-convex shoulder is respectively arranged on the two connecting flange end faces, guarantee that two displacements of cylinders connect fast and accurate centering.On the length direction that launches cylinder 10, equidistant, edge circumferentially has lubricating oil cloth oilhole, is used to inject lubricating oil, to reduce piston 20 and to launch friction drag between the cylinder wall.Multiple-sealed ring 21 is housed on the piston 20, and wherein, preceding 2 ~ 3 roads that contact with power gas near piston are compression ring, and 1 ~ 2 road, back is an oil ring.Be processed with the one seat hole on the piston 20, after being used for cable wire 30 and passing piston 20, it becomes the one seat hole on Y joint and the piston 20 to connect.Also be provided with perforate (groove) on the piston 20, the cross sectional shape of hole (groove) and the shape of cross section picture of analog bracket 50 adapt to, and there is gland packing letter case at the two ends of hole (groove), in high temperature resistant filler is arranged, be used for the sealing between piston 20 and the analog bracket 50.
With reference to Fig. 3, telescopic sealing arrangement 60 is connected together by the ascending casing pipe sleeve of more piece diameter and constitutes.Sleeve pipes at different levels comprise 61-1,62-1,63-1,64-1, and head end is provided with flange, comprise 61-2,62-2,63-2 and 64-2, and first order sleeve pipe 61-1 head end is captiveed joint with piston 20 by flange 61-2.Except that first order sleeve pipe, be provided with inner covering and side seal 62-3,63-3,64-3 in the head end of all the other sleeve pipes at different levels, head end has annual spring 62-4,63-4 and the 64-4 of spacing shoulder, the bump that produces when being respectively applied for rigid contact of head end of the external bushing of the mutual slip, sealing property and the buffering previous stage sleeve pipe tail end that guarantee between the sleeve pipes at different levels and back one-level sleeve pipe.Be provided with external bushing 61-6,62-6,63-6,64-6 on the periphery of sleeve pipe tail ends at different levels, be used for sliding mutually between the sleeve pipes at different levels neutralizing.The inner covering sealing of the external bushing of sleeve pipe tail end and next stage sleeve pipe head end, between sleeve pipe, form air cushion, can be used for sleeve pipes at different levels under the affecting of previous stage sleeve pipe, stretch out forward lentamente successively, avoid the mutual rigid contact of sleeve pipes at different levels and produce the bump of strong row.Also be provided with cable wire rope pad 61-5,62-5,63-5,64-5 in the tail end of sleeve pipes at different levels, be used to hold cable wire, be located at the center of sleeve pipe and do not produce friction with the sleeve pipe inner edge.The High molecular material that the available friction coefficient of rope pad is little, hardness is high is made.The length difference of sleeve pipes at different levels, back one-level sleeve pipe outline is longer than the previous stage sleeve pipe.Like this, the previous stage sleeve pipe is when retraction, and its tail end can not run into the rope pad of back one-level sleeve pipe.Sleeve pipes at different levels can be made with high-temperature alloy steel, and its cylindrical is coated with effectively insulating coating.
With reference to Fig. 4, launch in the cylinder 10, below telescopic sealing arrangement, be provided with fixing guide carriage 50 from cylinder head to launching the cylinder tail end, guide carriage 50 is fixed on and launches in the cylinder 10, and casing flange cylindrical 62-2,63-2 and the 64-2 of telescopic sealing arrangement are limited in this guide carriage.
Claims (3)
1. an ejector with enclosed cylinder structure comprises and launches cylinder, piston, cylinder head, attaching parts and reciprocal car, and it is characterized in that: the described cylinder that launches is closed tubular structure, is made up of the more piece cylinder; Cylinder head is placed in the described initiating terminal that launches cylinder, and it is provided with air inlet valve and cable wire hole; Described attaching parts is a high strength cable wire, and the one end links to each other with piston in launching cylinder by the cable wire hole on the cylinder head, and the other end joins with reciprocal car; This ejector also comprises a telescopic sealing arrangement, the sleeve pipe that it is ascending by the more piece internal diameter, telescopically connects together constitutes, innermost layer sleeve pipe head end is placed on the piston that launches in the cylinder, the outermost layer tube ends is stretched out by the cable wire hole on the cylinder head and is launched cylinder, and the high strength cable wire is placed in one.
2. ejector according to claim 1, it is characterized in that: described telescopic sealing arrangement sleeve pipe head ends at different levels are provided with flange, the tail end pipe is outside equipped with external bushing, is provided with inner covering, side seal and annual spring in the sleeve pipe head end pipe of the second stage.
3. ejector according to claim 1 is characterized in that: the below of described telescopic sealing arrangement is provided with fixing guide carriage, and the casing flange cylindrical of telescopic sealing arrangement is limited in the guide carriage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2006101526452A CN101186235A (en) | 2006-09-26 | 2006-09-26 | Ejector with enclosed cylinder structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2006101526452A CN101186235A (en) | 2006-09-26 | 2006-09-26 | Ejector with enclosed cylinder structure |
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| Publication Number | Publication Date |
|---|---|
| CN101186235A true CN101186235A (en) | 2008-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2006101526452A Pending CN101186235A (en) | 2006-09-26 | 2006-09-26 | Ejector with enclosed cylinder structure |
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| CN (1) | CN101186235A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009132527A1 (en) * | 2008-04-28 | 2009-11-05 | Li Guang | Full-floating steam-powered compression catapult |
| CN101973403A (en) * | 2010-08-30 | 2011-02-16 | 李广 | Suspension uni-directional/bi-directional steam catapult |
| CN102343981A (en) * | 2010-07-30 | 2012-02-08 | 杨建东 | Steam power catapult of aircraft carrier plane |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
| CN102951299A (en) * | 2012-12-05 | 2013-03-06 | 魏伯卿 | Multilevel-sleeve piston-type gravity hydraulic catapult for shipboard aircraft on aircraft carrier |
| CN103010476A (en) * | 2012-12-05 | 2013-04-03 | 魏伯卿 | Sleeve type piston tube for ejector of aircraft carrier |
| CN103991554A (en) * | 2013-11-09 | 2014-08-20 | 游永康 | Compressed air catapult |
| CN105605976A (en) * | 2015-12-21 | 2016-05-25 | 北京航天益森风洞工程技术有限公司 | Gas catapulting device |
| CN106742024A (en) * | 2015-11-23 | 2017-05-31 | 孙建军 | Aircraft carrier telescoping cylinder electromagnetism rail steam ejection device |
| CN111721160A (en) * | 2020-06-29 | 2020-09-29 | 北京理工大学 | Inter-ring buffer for multi-stage cylinder ejection launching device |
-
2006
- 2006-09-26 CN CNA2006101526452A patent/CN101186235A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009132527A1 (en) * | 2008-04-28 | 2009-11-05 | Li Guang | Full-floating steam-powered compression catapult |
| CN102343981A (en) * | 2010-07-30 | 2012-02-08 | 杨建东 | Steam power catapult of aircraft carrier plane |
| CN101973403A (en) * | 2010-08-30 | 2011-02-16 | 李广 | Suspension uni-directional/bi-directional steam catapult |
| CN101973403B (en) * | 2010-08-30 | 2012-11-21 | 李广 | Suspension uni-directional/bi-directional steam catapult |
| CN102795347B (en) * | 2012-05-04 | 2016-08-03 | 银世德 | Two-tube spring ejector for aircraft carrier |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
| CN102700721B (en) * | 2012-05-04 | 2015-04-29 | 银世德 | Combined catapult for aircraft carrier |
| CN102951299A (en) * | 2012-12-05 | 2013-03-06 | 魏伯卿 | Multilevel-sleeve piston-type gravity hydraulic catapult for shipboard aircraft on aircraft carrier |
| CN103010476A (en) * | 2012-12-05 | 2013-04-03 | 魏伯卿 | Sleeve type piston tube for ejector of aircraft carrier |
| CN103991554A (en) * | 2013-11-09 | 2014-08-20 | 游永康 | Compressed air catapult |
| CN106742024A (en) * | 2015-11-23 | 2017-05-31 | 孙建军 | Aircraft carrier telescoping cylinder electromagnetism rail steam ejection device |
| CN106742024B (en) * | 2015-11-23 | 2021-03-12 | 孙建军 | Electric magnetic track steam catapult for telescopic cylinder of aircraft carrier |
| CN105605976A (en) * | 2015-12-21 | 2016-05-25 | 北京航天益森风洞工程技术有限公司 | Gas catapulting device |
| CN105605976B (en) * | 2015-12-21 | 2017-06-27 | 北京航天益森风洞工程技术有限公司 | Gas catapult-launching gear |
| CN111721160A (en) * | 2020-06-29 | 2020-09-29 | 北京理工大学 | Inter-ring buffer for multi-stage cylinder ejection launching device |
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Open date: 20080528 |