CN102485596A - Aircraft catapult of aircraft carrier - Google Patents
Aircraft catapult of aircraft carrier Download PDFInfo
- Publication number
- CN102485596A CN102485596A CN2009102182376A CN200910218237A CN102485596A CN 102485596 A CN102485596 A CN 102485596A CN 2009102182376 A CN2009102182376 A CN 2009102182376A CN 200910218237 A CN200910218237 A CN 200910218237A CN 102485596 A CN102485596 A CN 102485596A
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- cylinder
- coaster
- aircraft
- pulley
- carrier
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Abstract
The invention discloses an aircraft catapult of an aircraft carrier. The aircraft catapult comprises a cylinder, two steel wire ropes for transferring power, an acceleration pulley, a grooved rail for the pulley to run, a reverse pulley, a high-pressure pipeline for communicating the cylinder with an air filling system, and an air storing and filling mechanism, and is characterized in that four fixed pulleys are located at four corners of a rectangle; the two ends of a cylinder piston are connected by a steel wire rope; and one steel wire rope goes around the two fixed pulleys in front of the cylinder and is fixedly connected with the rear end of the pulley, and the other steel wire rope goes around the other two fixed pulleys behind the cylinder and is fixedly connected with the front end of the pulley. The high-pressure air pump pumps in an air storage tank; and when in use, the air storage tank fills high-pressure airflow into the cylinder, and the high-pressure airflow pushes the piston to drive the steel wire ropes connected with the pulley to perform accelerated motion so that an aircraft on the pulley can obtain the take-off speed in proper time.
Description
Technical field
The present invention relates to a kind of carrier-based aircraft ejector.
Background technology
The most ripe ejector of taking off that uses on the aircraft carrier is exactly a steam catapult; Be that the employing high pressure steam is a power; Thrust by the generation of steam engine piston; Drive reciprocal car flat-out acceleration between the distance of 100 meters of less thaies and make aircraft reach takeoff speed, airplane catapult is gone up to the air to the speed more than 100 meter per seconds.But this mode needs the large-sized boiler of aircraft carrier that steam is provided, and the mass energy that just will consume aircraft carrier makes the use cost of carrier-borne aircraft increase., steam catapult is a steam reciprocating engine that stroke is very long, partly is made up of emission coefficient, steam unit, tow rope clamping system, lubricated and control system etc., structure is complicacy more.Operation technique requires also complicated.
Summary of the invention
The object of the invention just provides a kind of carrier-based aircraft ejector easy to use, simple in structure.Use height, complex structure, the problem that operation easier is big to solve present steam catapult.
The technical scheme that realizes above-mentioned purpose is:
The carrier-based aircraft ejector comprises two sections steel ropes of cylinder, transferring power, quickens coaster, grooved rail, angle pulley and the pressure duct that cylinder is communicated with refueling system, gas storage and the aerating mechanism of coaster operation; It is characterized in that four fixed pulleys are in rectangular four jiaos of disposal; The two ends of cylinder piston connect with steel rope; One section steel rope is walked around two fixed pulleys that are in cylinder the place ahead; Be fixed in the rear end of coaster, another section steel rope is walked around two fixed pulleys in addition at cylinder rear, is fixed in the front end of coaster.
Coaster is installed on the elongated slot rail, and two pairs of set of wheels being made up of the wheel of getting on or off the bus are clamped between grooved rail raceway wall.Have the multiple tracks circumferential groove on the cylinder of cylinder piston, seal ring is installed in the groove, to guarantee the sealing property between piston and cylinder chamber wall.Be connected with forward high pressure admission pipeline between cylinder body front portion and air receiver; Be connected with the high back voltage admission line between cylinder body rear portion and air receiver; The cylinder body rear sidewall also has the gas discharge outlet after the acting apart from the rear side housing medial surface size place bigger than piston length, the rear side housing of cylinder body is connected with the gas outlet pipe road.A gascollecting cap cylinder is installed on the high pressure admission pipeline.Gascollecting cap cylinder and inflation pump are by the aerating pipeline connection, and inflation pump is connected with the work drive motor mechanical axis.The end cap seal at cylinder two ends is affixed firmly.Steel cable and cylinder front end cover central outlet place oil sealing sliding block joint.
The carrier-based aircraft ejector of processing like this, it is not only simple in structure to replace high pressure steam with high pressure gas, and energy savings.Use high-pressure pump and motor, to the air receiver aerating.Coaster drives aircraft and quickens, and its operation leans on piston to drive steel rope, and the pulling coaster quickens, and makes front-wheel be in supratrochlear aircraft and before its place ahead pulley turns to, reaches takeoff speed running to steel rope with coaster.Make the airplane catapult lift-off.
So, carrier-based aircraft launching catapult simple in structure, energy savings, processing ease.
Description of drawings
Fig. 1 is a carrier-based aircraft ejector structure principle chart;
Fig. 2 is the structural relation scheme drawing between coaster wheel and grooved rail.
The specific embodiment
Below in conjunction with accompanying drawing,, technical scheme is further specified as an embodiment.
With reference to Fig. 1,2, the cylinder 18 of carrier-based aircraft ejector be one microscler, its length will make acceleration distance of its pulling coaster 3 operation reach the rate request that aircraft 4 takes off.Cylinder inner cavity requires to make the mutual vapor tight high smooth degree in piston 17 two ends of operation therein; The end cap at cylinder two ends combines with cylinder body firmly; Seal air tightly, steel rope 1 penetrates in the chamber affixed with piston 17 two ends from the cylinder two ends, and 20 on the oil sealing of itself and cylinder front end cover 19 requires air tight.Forward high pressure admission pipeline 16 leans on the end cap inside to connect from the anterior sidewall of cylinder body, and control cock 15 is installed, and is used to feed the high pressure gas that make the piston acting; Reverse admission line is connected from cylinder body rear sidewall opening, and control cock 11 is installed, and after the piston acting, is used to promote piston and turns back to reference position, in order to acting once more.The gas discharge outlet 8 that the cylinder body rear sidewall also has after the acting apart from the rear side housing 9 medial surfaces size place bigger than piston length is equipped with control cock; Rear end of the cylinder block covers the intracavity gas escape route 10 that 9 place's openings are equipped with valve control, the gas of discharging in the cylinder with the high pressure gas that guarantees after the acting.Opening is installed the compression indicator 22 of gaseous tension in the observation chamber between cylinder side wall and inner chamber.Open control cock 15, air receiver 14 mesohigh gases promptly are pressed in the cylinder chamber fast, promote piston 17 and move rapidly, drive steel rope 1 pulling coaster 3 and make accelerated movement.Front-wheel is in supratrochlear aircraft 4 and obtains identical acceleration/accel, and is through to the speed of taking off and requiring.High pressure inflation pump 13 and work drive motor 12 thereof are installed in the opposite side of air receiver, and promptly the reverse admission line of forward high pressure admission pipeline, cylinder operation primary piston return and the inflation pump pipeline of in air receiver, adding high pressure gas all is communicated with air receiver 14.Confirming of the distance that four fixed pulleys are 21 is in supratrochlear aircraft operation acceleration distance and reaches takeoff speed and require to set making.Thereby also confirmed the length of steel rope 1.
The grooved rail 2 of coaster operation is the shape of cutting open from the I-shape intermediate vertical, is in the below of coaster wheel, and the distance between two rails is the wheelbase between one group of wheel of coaster, and the wheel of coaster is smoothly contacted with the raceway on grooved rail top.The wheel of coaster constitutes road wheel and is clamped in the version on the grooved rail raceway with flower wheel by being in road wheel 5 and the correspondence position above grooved rail 2 raceways and being in the flower wheel 7 below the grooved rail raceway, respectively in the upper and lower surface rolling of raceway.The attaching parts 6 through its outside fixes as one between two-wheeled up and down, and attaching parts and the two-wheel turning cylinder is affixed up and down.
Steel rope is divided into two sections, and is affixed with cylinder piston 17 two ends and coaster 3 two ends respectively, wherein also walks around to be in four fixed pulleys 21 of four jiaos, contacts with each fixed pulley pivoting friction.
During operation, make piston 17 in the cylinder be in the front end of cylinder inner cavity, when needs help-fly machine took off, aircraft nose wheel dropped on coaster 3 tail plane and starts.Charge into enough high pressure gas through inflation pump 13 to air receiver 14 in advance;, opens by aircraft the by-pass valve control 15 in the pipeline when starting; High pressure gas are rushed in cylinder 18; With piston 17 working direction implementation in the chamber rapidly, the steel rope 1 that connects piston drives the coaster 3 instant ahead runnings that quicken, and makes aircraft reach takeoff speed.After piston 17 actings, gas discharge outlet 8 just is in after piston 17 working direction, promotes outside the gas mouth discharge from then on cylinder of piston operation.After the acting air scavenge; Open the valve 11 on the high back voltage admission line; Close the valve 10 on the gas outlet pipe road on gas discharge outlet 8 and the rear side housing 9 simultaneously, feed high pressure gas, piston 17 is returned to reference position; Open the valve 10 on the bleeder line on gas discharge outlet 8 and the rear side housing again, let intracavity gas drain.So that piston is when reruning, non-resistance in the chamber.
Claims (4)
1. carrier-based aircraft ejector comprises and two sections steel ropes (1) of cylinder (18), transferring power quickens coaster (3), grooved rail (2), angle pulley (21) and the pressure duct that cylinder (18) is communicated with refueling system, gas storage and the aerating mechanism of coaster operation; It is characterized in that four fixed pulleys (21) are in rectangular four jiaos of disposal; The two ends of cylinder piston (17) connect with steel rope; One section steel rope is walked around two fixed pulleys (21) that are in cylinder (18) the place ahead; Be fixed in the rear end of coaster (3), another section steel rope is walked around two fixed pulleys (21) in addition at cylinder (18) rear, is fixed in the front end of coaster (3); Be connected with forward high pressure admission pipeline between cylinder body front portion and air receiver; Be connected with the high back voltage admission line between cylinder body rear portion and air receiver; The cylinder body rear sidewall also has the gas discharge outlet (8) after the acting apart from rear side housing (9) medial surface than the big size place of piston (17) length, the rear side housing of cylinder body (9) is connected with gas outlet pipe road (10).
2. carrier-based aircraft ejector according to claim 1 is characterized in that coaster (3) is installed on the elongated slot rail (2), and two pairs of set of wheels being made up of wheel (5,7) up and down are clamped between grooved rail (2) raceway wall.
3. carrier-based aircraft ejector according to claim 1 is characterized in that on the high pressure admission pipeline, installing a gascollecting cap cylinder (14).
4. carrier-based aircraft ejector according to claim 1 is characterized in that steel rope (1) and cylinder front end cover (19) central outlet place oil sealing (20) sliding block joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102182376A CN102485596A (en) | 2009-11-24 | 2009-11-24 | Aircraft catapult of aircraft carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102182376A CN102485596A (en) | 2009-11-24 | 2009-11-24 | Aircraft catapult of aircraft carrier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102485596A true CN102485596A (en) | 2012-06-06 |
Family
ID=46151174
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009102182376A Pending CN102485596A (en) | 2009-11-24 | 2009-11-24 | Aircraft catapult of aircraft carrier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102485596A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648687A (en) * | 2013-11-19 | 2015-05-27 | 张文星 | Elastic force source of aircraft carrier air pressure electromagnetic catapult |
| CN105438496A (en) * | 2015-12-01 | 2016-03-30 | 裘尧云 | Ejection arresting gear |
| CN108216671A (en) * | 2018-01-26 | 2018-06-29 | 白景魁 | A kind of boosting of aircraft carrier slides jump formula takeoff method |
| CN108482700A (en) * | 2018-03-07 | 2018-09-04 | 燕山大学 | A kind of pneumatic ejection system of unmanned plane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190909608A (en) * | 1908-08-20 | 1909-10-21 | James Means | Improvements in Apparatus for Launching Flying Machines. |
| CN1146414A (en) * | 1994-09-05 | 1997-04-02 | 朱炎 | Airplane catapult and recovery system |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN101054115A (en) * | 2007-04-25 | 2007-10-17 | 张�杰 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
| CN101301933A (en) * | 2007-05-11 | 2008-11-12 | 尚德敏 | Water ejector of aircraft carrier |
| CN201580561U (en) * | 2009-11-19 | 2010-09-15 | 刘华 | Carrier-based aircraft launching catapult |
-
2009
- 2009-11-24 CN CN2009102182376A patent/CN102485596A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190909608A (en) * | 1908-08-20 | 1909-10-21 | James Means | Improvements in Apparatus for Launching Flying Machines. |
| CN1146414A (en) * | 1994-09-05 | 1997-04-02 | 朱炎 | Airplane catapult and recovery system |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN101054115A (en) * | 2007-04-25 | 2007-10-17 | 张�杰 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
| CN101301933A (en) * | 2007-05-11 | 2008-11-12 | 尚德敏 | Water ejector of aircraft carrier |
| CN201580561U (en) * | 2009-11-19 | 2010-09-15 | 刘华 | Carrier-based aircraft launching catapult |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648687A (en) * | 2013-11-19 | 2015-05-27 | 张文星 | Elastic force source of aircraft carrier air pressure electromagnetic catapult |
| CN105438496A (en) * | 2015-12-01 | 2016-03-30 | 裘尧云 | Ejection arresting gear |
| CN108216671A (en) * | 2018-01-26 | 2018-06-29 | 白景魁 | A kind of boosting of aircraft carrier slides jump formula takeoff method |
| CN108482700A (en) * | 2018-03-07 | 2018-09-04 | 燕山大学 | A kind of pneumatic ejection system of unmanned plane |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120606 |