CN201580561U - Carrier-based aircraft launching catapult - Google Patents
Carrier-based aircraft launching catapult Download PDFInfo
- Publication number
- CN201580561U CN201580561U CN200920253735XU CN200920253735U CN201580561U CN 201580561 U CN201580561 U CN 201580561U CN 200920253735X U CN200920253735X U CN 200920253735XU CN 200920253735 U CN200920253735 U CN 200920253735U CN 201580561 U CN201580561 U CN 201580561U
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- cylinder
- carrier
- coaster
- based aircraft
- pulley
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Abstract
The utility model relates to a carrier-based aircraft launching catapult which comprises an air cylinder, two sections of wire ropes for transmitting power, an accelerated pulley, a grooved rail for pulley running, a reversing pulley, a high pressure pipeline used for communicating the air cylinder with an air-entrapping system, and an air storing and entrapping mechanism; the carrier-based aircraft launching catapult is characterized in that four fixing pulleys are positioned at the four corners of a rectangle, the two ends of the air cylinder are connected through the wire ropes, one of the two sections of wire rope passes through the two fixing pulleys positioned in front of the air cylinder and is fixedly connected to the rear end of the accelerated pulley, and the other section of wire rope passes through the other two fixing pulleys positioned behind the air cylinder and is fixedly connected to the front end of the accelerated pulley. An air reservoir is pumped up through a high-pressure air pump, when the carrier-based aircraft launching catapult is used, the air cylinder is filled with high-pressure air current in the air reservoir, so that a piston is pushed to drive the wire ropes connected with the accelerated pulley to perform accelerated motion, so as to enable an aircraft on the accelerated pulley to reach the takeoff speed within the proper time.
Description
Technical field
The utility model relates to a kind of carrier-based aircraft launching catapult.
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 between the distance of 100 meters of less thaies flat-out acceleration to the speed more than 100 meter per seconds, make aircraft reach takeoff speed, airplane catapult is gone up to the air.But this mode needs the large-sized boiler of aircraft carrier that steam is provided, and just will consume a large amount of energy of aircraft carrier, makes the use cost of carrier-borne aircraft to 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., and structure is more complicated.Operation technique requires also complicated.
The utility model content
The purpose of this utility model just provides a kind of carrier-based aircraft launching catapult easy to use, simple in structure.To solve present steam catapult use cost height, complex structure, the problem that operation easier is big.
The technical scheme that realizes above-mentioned purpose is:
The carrier-based aircraft launching catapult 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 places, 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 launching catapult of making 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 drives steel rope by piston, and the pulling coaster quickens, and makes front-wheel be in supratrochlear aircraft and reaches takeoff speed running to steel rope with coaster before its place ahead pulley turns to.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 launching catapult 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 launching catapult 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 is connected by side opening in the end cap 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; Oppositely admission line is connected from cylinder body rear sidewall opening, and control cock 11 is installed, and is used to promote piston and turns back to reference position after the piston acting, 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 adding high pressure gas in air receiver all is communicated with air receiver 14.Determining 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 determined 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 is by being in road wheel 5 and the correspondence position above grooved rail 2 raceways and being in flower wheel 7 below the grooved rail raceway, constitutes road wheel and flower wheel and is clamped in version on the grooved rail raceway, and the upper and lower surface at raceway rolls respectively.The attaching parts 6 by 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 by inflation pump 13 to air receiver 14 in advance, when starting, opens by aircraft the by-pass valve control 15 in the pipeline, 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, allow intracavity gas drain.So that piston is when reruning, non-resistance in the chamber.
Claims (5)
1. carrier-based aircraft launching catapult, the two sections steel ropes (1) that comprise cylinder (18), transferring power, quicken 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 places, 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).
2. carrier-based aircraft launching catapult 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 launching catapult according to claim 1, it is characterized in that being connected with between cylinder body front portion and air receiver forward high pressure admission pipeline, be connected with the high back voltage admission line between cylinder body rear portion and air receiver, the cylinder body rear sidewall also has 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).
4. carrier-based aircraft launching catapult according to claim 1 is characterized in that installing a gascollecting cap cylinder (14) on the high pressure admission pipeline.
5. carrier-based aircraft launching catapult 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 |
|---|---|---|---|
| CN200920253735XU CN201580561U (en) | 2009-11-19 | 2009-11-19 | Carrier-based aircraft launching catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920253735XU CN201580561U (en) | 2009-11-19 | 2009-11-19 | Carrier-based aircraft launching catapult |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201580561U true CN201580561U (en) | 2010-09-15 |
Family
ID=42722556
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200920253735XU Expired - Fee Related CN201580561U (en) | 2009-11-19 | 2009-11-19 | Carrier-based aircraft launching catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201580561U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102120496A (en) * | 2010-10-22 | 2011-07-13 | 王先全 | Vacuum power catapult |
| CN102485596A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft catapult of aircraft carrier |
| CN102765486A (en) * | 2012-08-16 | 2012-11-07 | 刘光其 | Shipboard aircraft ejection device for aircraft carrier |
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN102951299A (en) * | 2012-12-05 | 2013-03-06 | 魏伯卿 | Multilevel-sleeve piston-type gravity hydraulic catapult for shipboard aircraft on aircraft carrier |
| CN103507964A (en) * | 2012-06-16 | 2014-01-15 | 姜汝诚 | Aircraft catapult-assisted take-off device and aircraft landing stopping device |
| CN103991554A (en) * | 2013-11-09 | 2014-08-20 | 游永康 | Compressed air catapult |
-
2009
- 2009-11-19 CN CN200920253735XU patent/CN201580561U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102485596A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft catapult of aircraft carrier |
| CN102120496A (en) * | 2010-10-22 | 2011-07-13 | 王先全 | Vacuum power catapult |
| CN103507964A (en) * | 2012-06-16 | 2014-01-15 | 姜汝诚 | Aircraft catapult-assisted take-off device and aircraft landing stopping device |
| CN103507964B (en) * | 2012-06-16 | 2016-09-07 | 姜汝诚 | Airplane catapult launching apparatus and aircraft landing arrester |
| CN102765486A (en) * | 2012-08-16 | 2012-11-07 | 刘光其 | Shipboard aircraft ejection device for aircraft carrier |
| CN102765486B (en) * | 2012-08-16 | 2015-02-25 | 刘光其 | Shipboard aircraft ejection device for aircraft carrier |
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN102951299A (en) * | 2012-12-05 | 2013-03-06 | 魏伯卿 | Multilevel-sleeve piston-type gravity hydraulic catapult for shipboard aircraft on aircraft carrier |
| CN103991554A (en) * | 2013-11-09 | 2014-08-20 | 游永康 | Compressed air catapult |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100915 Termination date: 20101119 |