CN102336277A - Combined-type cylinder mandril ejector of carrier planes of aircraft carrier - Google Patents
Combined-type cylinder mandril ejector of carrier planes of aircraft carrier Download PDFInfo
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- CN102336277A CN102336277A CN2010102308324A CN201010230832A CN102336277A CN 102336277 A CN102336277 A CN 102336277A CN 2010102308324 A CN2010102308324 A CN 2010102308324A CN 201010230832 A CN201010230832 A CN 201010230832A CN 102336277 A CN102336277 A CN 102336277A
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- cylinder
- deceleration buffer
- tubular shape
- piston
- buffer piston
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Abstract
The invention relates to a combined-type cylinder mandril ejector of carrier planes of an aircraft carrier. The combined-type cylinder mandril ejector comprises an incompletely-opened tubular rail, a pneumatic ejector mandril (namely a primary deceleration buffer piston) and a composite cylinder formed by mutually sleeving at least two cylinders with different diameters; the open tube section of the incompletely-opened tubular rail is provided with an open groove; the composite cylinder is fixed on the incompletely-opened tubular rail through the outmost air cylinder; the composite cylinder is connected with a steam device; an ejection hook is arranged on the pneumatic ejector mandril (namely the primary deceleration buffer piston) in the composite cylinder; a secondary deceleration buffer piston is arranged in the incompletely-opened tube section of the incompletely-opened tubular rail; a cavity between the pneumatic ejector mandril (namely the primary deceleration buffer piston) and the secondary deceleration buffer piston is a primary energy-dissipation cylinder chamber; a cavity between the secondary deceleration buffer piston and the bottom of the incompletely-opened tubular rail is a secondary energy-dissipation cylinder chamber; and the bottom of the incompletely-opened tubular rail is provided with a reset air-compensating door. The combined type cylinder mandril ejector has the advantages of simple structure, low fault rate and high safety performance.
Description
Technical field
The present invention relates to a kind of ship-board aircraft ejector, especially relate to a kind of carrier ship-board aircraft combined type ejecting rod of cylinder ejector.
Background technology
The aircraft carrier of world today military power be a kind of be the large-scale water surface naval vessels of main operational weapon with carrier-borne aircraft.Show that according to pertinent data mostly the aircraft catapult of Great Britain and America's carrier-borne aircraft is the tubular steam catapult-launching gear of open type.In the process of launching,, be provided with the complicated movable sealing system of a nested structure especially for guaranteeing its power steam pressure.And be the steam pressure of opposing 20Mpa, the thickness that its opening steam pipe needs is well imagined.Existing ejector is complex structure not only, and fault rate is high, and safety performance is low.
Summary of the invention
The object of the present invention is to provide a kind of simple in structurely, fault rate is low, the carrier ship-board aircraft combined type ejecting rod of cylinder ejector that safety performance is high.
The present invention to technical scheme is: it comprises incomplete open tubular shape track, pneumaticly launches the Composite cylinder that push rod is held concurrently one-level deceleration buffer piston and is nested and formed by the cylinder of at least two different-diameters; Said incomplete open tubular shape track opening pipeline section is provided with open slot; Composite cylinder is fixed on the incomplete open tubular shape track through its outermost level cylinder; Composite cylinder is connected with steam unit; The pneumatic push rod one-level deceleration buffer piston of holding concurrently that launches is located in the Composite cylinder; The pneumatic push rod one-level deceleration buffer piston of holding concurrently that launches is provided with ejecting hook; Composite cylinder, pneumatic launch push rod hold concurrently one-level deceleration buffer piston, not exclusively open tubular shape track opening pipeline section and ejecting hook are formed sling movement portion; Not exclusively be provided with the double reduction damper piston in the not opening pipeline section of open tubular shape track, pneumatic to launch the cavity that push rod holds concurrently between one-level deceleration buffer piston and the double reduction damper piston be one-level energy dissipating cylinder chamber, and the cavity of double reduction damper piston between bottom incomplete open tubular shape track is secondary energy dissipating cylinder chamber; Not exclusively open tubular shape track bottom is provided with the tonifying Qi door that resets, and pneumatic hold concurrently one-level deceleration buffer piston, double reduction damper piston, one-level energy dissipating cylinder chamber, secondary energy dissipating cylinder chamber and the tonifying Qi door that resets of push rod that launch formed deceleration energy dissipating portion.
Said incomplete open tubular shape track and pneumatic launches push rod and holds concurrently and lubricating oil is housed in the space between the one-level deceleration buffer piston, and air feed is moved and penetrated the push rod lubricated usefulness of one-level deceleration buffer piston high-speed motion of holding concurrently.
Said secondary energy dissipating cylinder chamber inwall is provided with piston reset spring.
Also the deceleration buffer piston can be set between said double reduction damper piston and the incomplete open tubular shape track bottom.
Inventive principle of the present invention is a pascal's principle, and the mechanics formula that relates to has: F
1=ma, F
2=ps, a=(v
t-v
0)/t, in the formula, F
1Be motoricity, m is a moving-mass, and a is an acceleration of motion, F
2Be vapor pressure, p is a vapor pressure, and s is push rod steam area of thrust surface, v
tBe object of which movement end speed, v
0Be the object of which movement initial velocity, t is the time of object of which movement.
If: steam pressure p is that 10Mpa (is 100kgf/cm
2) (U.S. army's aircraft carrier steam catapult steam pressure is 20Mpa), launched object quality m
1Be 40 tons (the fully loaded bullet of U.S. army's carrier-borne aircraft " hornet " weight is the 35-37 ton), run duration t is 3 seconds (being 6 seconds between U.S. army's aircraft carrier block clearance time), the pneumatic push rod quality m that launches
2Be 20 tons, the pneumatic push rod diameter D that launches is a 500mm (radius R=250mm).
Then: the pneumatic push rod steam area of thrust surface s=π R that launches
2=1962.5 (cm
2);
Vapor pressure F
2=ps=100 * 1962.5=196250 (kgf)=196250 * 9.8=1923250 (N)
Vapor pressure F
2=motoricity F
1, F
1=ma=(m
1+ m
2) a,
A=F then
1/ m=F
1/ (m
1+ m
2)=F
2/ (m
1+ m
2)=1923250/ (40+20) * 10
3=32.05 (m/s
2)
v
t=at=32.05 * 3=96 (m/s)=345.6 (km/h) (annotating: consider the power taken off in the calculating)
The present invention is simple in structure, and is reasonable in design, cheap, practical, and fault rate is low, and safety performance is high, and maintenance cost is low, and is simple to operate.
Description of drawings
Fig. 1 is an embodiment of the invention structural representation;
Fig. 2 is the structural representation of incomplete open tubular shape track embodiment illustrated in fig. 1.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described further.
With reference to accompanying drawing; Present embodiment comprises incomplete open tubular shape track 3, pneumaticly launches the Composite cylinder 1 that push rod is held concurrently one-level deceleration buffer piston 2 and is nested and formed by the cylinder of four different-diameters; Said incomplete open tubular shape track 3 opening pipeline sections are provided with open slot 10; Composite cylinder 1 is fixed on the incomplete open tubular shape track 3 through its outermost level cylinder; Composite cylinder 1 is connected with the steam unit (not shown); The pneumatic push rod one-level deceleration buffer piston 2 of holding concurrently that launches is located in the Composite cylinder 1; The pneumatic push rod one-level deceleration buffer piston 2 of holding concurrently that launches is provided with ejecting hook 4, Composite cylinder 1, pneumatic launch push rod hold concurrently one-level deceleration buffer piston 2, not exclusively open tubular shape track 3 opening pipeline sections and ejecting hook 4 are formed sling movement portions, not exclusively are provided with double reduction damper piston 6 in the not opening pipeline section of open tubular shape track 3; It is pneumatic that to launch the cavity that push rod holds concurrently between one-level deceleration buffer piston 2 and the double reduction damper piston 6 be one-level energy dissipating cylinder chamber 7; Double reduction damper piston 6 and not exclusively the cavity between open tubular shape track 3 bottoms be secondary energy dissipating cylinder chamber 8, not exclusively open tubular shape track 3 bottoms are provided with the tonifying Qi door 9 that resets, pneumatic hold concurrently one-level deceleration buffer piston 2, double reduction damper piston 6, one-level energy dissipating cylinder chamber 7, secondary energy dissipating cylinder chamber 8 and the tonifying Qi door 9 that resets of push rod that launch formed deceleration energy dissipating portions.
Said incomplete open tubular shape track 3 and pneumatic launches push rod and holds concurrently and lubricating oil 11 is housed in the space between the one-level deceleration buffer piston 2, and air feed is moved and penetrated the push rod lubricated usefulness of one-level deceleration buffer piston 2 high-speed motions of holding concurrently.
Said secondary energy dissipating cylinder chamber 8 inwalls are provided with piston reset spring 12.
Also the deceleration buffer piston can be set between said double reduction damper piston 6 and incomplete open tubular shape track 3 bottoms.
The present invention is installed on below the airstrip, and airstrip is provided with and the open slot of the incomplete open tubular shape track 3 open sections ejecting hook movement slots at same perpendicular; Steam is from steam unit input Composite cylinder 1; Act on pneumatic push rod one-level deceleration buffer piston 2 inner end surfaces of holding concurrently that launch; Pneumatic the hold concurrently one-level deceleration buffer piston 2 of push rod that launches is made high-speed motion along incomplete open tubular shape track 3; Simultaneously, ejecting hook 4 is made high-speed motion through the ejecting hook movement slots towing aircraft on the airstrip; After aircraft reached takeoff speed, steam unit was closed steam supply, and discharged steam in the cylinder body.At this moment; Pneumatic the hold concurrently one-level deceleration buffer piston 2 of push rod that launches gets into the not opening pipeline section of incomplete open tubular shape track 3; The air of compression one-level energy dissipating cylinder chamber 7 drives 6 motions of double reduction damper piston simultaneously, the air in the compression secondary energy dissipating cylinder chamber 8; Launch the push rod one-level deceleration buffer piston 2 complete energy dissipatings of holding concurrently until pneumatic, accomplish pneumatic the hold concurrently energy dissipating brake snub of one-level deceleration buffer piston 2 of push rod that launches after the sling movement.
Claims (4)
1. carrier ship-board aircraft combined type ejecting rod of cylinder ejector; It is characterized in that; Comprise incomplete open tubular shape track, pneumaticly launch the Composite cylinder that push rod is held concurrently one-level deceleration buffer piston and is nested and formed by the cylinder of at least two different-diameters; Said incomplete open tubular shape track opening pipeline section is provided with open slot; Composite cylinder is fixed on the incomplete open tubular shape track through its outermost level cylinder; Composite cylinder is connected with steam unit, and the pneumatic push rod one-level deceleration buffer piston of holding concurrently that launches is located in the Composite cylinder, and the pneumatic push rod one-level deceleration buffer piston of holding concurrently that launches is provided with ejecting hook; Composite cylinder, pneumatic launch push rod hold concurrently one-level deceleration buffer piston, not exclusively open tubular shape track opening pipeline section and ejecting hook are formed sling movement portion; Not exclusively be provided with the double reduction damper piston in the not opening pipeline section of open tubular shape track, pneumatic to launch the cavity that push rod holds concurrently between one-level deceleration buffer piston and the double reduction damper piston be one-level energy dissipating cylinder chamber, and the cavity of double reduction damper piston between bottom incomplete open tubular shape track is secondary energy dissipating cylinder chamber; Not exclusively open tubular shape track bottom is provided with the tonifying Qi door that resets, and pneumatic hold concurrently one-level deceleration buffer piston, double reduction damper piston, one-level energy dissipating cylinder chamber, secondary energy dissipating cylinder chamber and the tonifying Qi door that resets of push rod that launch formed deceleration energy dissipating portion.
2. carrier ship-board aircraft combined type ejecting rod of cylinder ejector according to claim 1 is characterized in that, said incomplete open tubular shape track and pneumatic launches push rod and holds concurrently and lubricating oil is housed in the space between the one-level deceleration buffer piston.
3. carrier ship-board aircraft combined type ejecting rod of cylinder ejector according to claim 1 and 2 is characterized in that, said secondary energy dissipating cylinder chamber inwall is provided with piston reset spring.
4. carrier ship-board aircraft combined type ejecting rod of cylinder ejector according to claim 1 and 2 is characterized in that, is provided with the deceleration buffer piston between said double reduction damper piston and the incomplete open tubular shape track bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102308324A CN102336277B (en) | 2010-07-20 | 2010-07-20 | Combined-type cylinder mandril ejector of carrier planes of aircraft carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102308324A CN102336277B (en) | 2010-07-20 | 2010-07-20 | Combined-type cylinder mandril ejector of carrier planes of aircraft carrier |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102336277A true CN102336277A (en) | 2012-02-01 |
| CN102336277B CN102336277B (en) | 2013-12-04 |
Family
ID=45512301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102308324A Expired - Fee Related CN102336277B (en) | 2010-07-20 | 2010-07-20 | Combined-type cylinder mandril ejector of carrier planes of aircraft carrier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102336277B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109373811B (en) * | 2018-09-27 | 2021-02-09 | 北京空间机电研究所 | Multi-stage actuating ejection device adopting follow-up charging |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2855904Y (en) * | 2005-12-28 | 2007-01-10 | 高俊臣 | Steam ejection means for aircraft carrier |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN201089521Y (en) * | 2007-08-10 | 2008-07-23 | 霍方华 | Aircraft carrier shipboard aircraft steam catapult |
| US7472866B2 (en) * | 2006-11-15 | 2009-01-06 | The United States Of America As Represented By The Secretary Of The Navy | Deployment system and method for subsurface launched unmanned aerial vehicle |
| CN101712380A (en) * | 2009-06-03 | 2010-05-26 | 周辉林 | Aircraft carrier ejector |
| FR2939398A1 (en) * | 2008-12-09 | 2010-06-11 | Dcns | Moving load e.g. helicopter, handling securing device for use on e.g. deck of frigate, has guiding and retaining device cooperated with rails for integrating carriages with rails, and cable retaining unit fixed to load lashing point |
-
2010
- 2010-07-20 CN CN2010102308324A patent/CN102336277B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN2855904Y (en) * | 2005-12-28 | 2007-01-10 | 高俊臣 | Steam ejection means for aircraft carrier |
| US7472866B2 (en) * | 2006-11-15 | 2009-01-06 | The United States Of America As Represented By The Secretary Of The Navy | Deployment system and method for subsurface launched unmanned aerial vehicle |
| CN201089521Y (en) * | 2007-08-10 | 2008-07-23 | 霍方华 | Aircraft carrier shipboard aircraft steam catapult |
| FR2939398A1 (en) * | 2008-12-09 | 2010-06-11 | Dcns | Moving load e.g. helicopter, handling securing device for use on e.g. deck of frigate, has guiding and retaining device cooperated with rails for integrating carriages with rails, and cable retaining unit fixed to load lashing point |
| CN101712380A (en) * | 2009-06-03 | 2010-05-26 | 周辉林 | Aircraft carrier ejector |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
| CN102795347B (en) * | 2012-05-04 | 2016-08-03 | 银世德 | Two-tube spring ejector for aircraft carrier |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102336277B (en) | 2013-12-04 |
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