CN201784808U - Launching catapult for carrier-based aircraft - Google Patents
Launching catapult for carrier-based aircraft Download PDFInfo
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- CN201784808U CN201784808U CN2010202315111U CN201020231511U CN201784808U CN 201784808 U CN201784808 U CN 201784808U CN 2010202315111 U CN2010202315111 U CN 2010202315111U CN 201020231511 U CN201020231511 U CN 201020231511U CN 201784808 U CN201784808 U CN 201784808U
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- drag rope
- traction
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- traction sheave
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Abstract
The utility model relates to a launching catapult for a carrier-based aircraft on an aircraft carrier, which has the following structure: a traction rope is sheathed between a front traction wheel and a rear traction wheel, a traction sliding block is arranged on the traction rope, the front traction wheel is connected with a front driving mechanism, and the rear traction wheel is connected with a rear driving mechanism; rotating energy storage machines are respectively arranged in the front driving mechanism and the rear driving mechanism; and a tensioning wheel is arranged below the lower rotary section of the traction rope, and a tensioning wheel driving mechanism for controlling the vertical movement of the tensioning wheel is arranged at the lower part of the tensioning wheel. In the utility model, the efficiency is improved by more than one time compared with that of a steam launching catapult, and the launching period is shortened by one time without increasing the input energy. The launching catapult has the following advantages: the structure is simple, the cost is far less than that of the steam launching catapult, the power can be adjusted freely, small-sized aircrafts can be launched, and the using demand is met.
Description
Technical field
The utility model relates to the deck facility on a kind of aircraft carrier, specifically a kind of catapults.
Background technology
The mode of taking off of carrier-borne aircraft is to use the steam catapult catapult-assisted take-off on the aircraft carrier now, and steam catapult has a lot of shortcomings, the one, and complex structure, cost height; The 2nd, itself is very high to material, technological requirement; The 3rd, wasteful, efficient is low (generally having only 4-6%); The 4th, system complex, operating personal is many, and maintenance load is big; The 5th, because it is big to launch power, so need to consume a large amount of fresh water; The 6th, the cycle of launching is long; The 7th, power is difficult for adjusting, and blimp (as unmanned plane) is launched in inconvenience.
Summary of the invention
The purpose of this utility model just provides a kind of catapults, to overcome the deficiency that existing catapult-launching gear exists, improves and launches power, satisfies and uses needs.
The utility model is achieved in that a kind of catapults, between preceding traction sheave and back traction sheave, be socketed with drag rope, be provided with the traction slide block on drag rope, described preceding traction sheave and front driving mechanism join, and described back traction sheave and rear drive mechanism join; In described front driving mechanism and described rear drive mechanism, be respectively equipped with the rotation function memory device; Below the turning down section of described drag rope, be provided with tension wheel, be provided with the tension wheel driver train that the described tension wheel of control moves up and down in the bottom of described tension wheel.
Described front driving mechanism is that the termination at main drive shaft has forerunner's motivation, and the other end connects preceding traction sheave by friction clutch; On described friction clutch, be connected to clutch actuator; Described rotation function memory device is installed on the described main drive shaft.
Periphery at described friction clutch is provided with apparatus for cooling clutch.
Described rotation function memory device is a weighting distribution wheel.
The bottom surface of meander sections is provided with traction slide block slide rail on described drag rope, is provided with traction slide block return actuating device on the turning down section of described drag rope.
The turning down section of meander sections and/or described drag rope is provided with the drag rope brake actuator on described drag rope.
The utility model is simple in structure, and technology maturation is not high to material, technological requirement, and easy to maintenance; Efficient can reach more than 12%, compares with steam catapult, and efficient is enhanced about more than once; Under the situation that does not strengthen intake, the cycle of launching can shorten more than one times.This ejector total weight is no more than 300 tons, and it makes simple, and cost is much smaller than steam catapult.Horsepower output of the present utility model can be adjusted arbitrarily, so can launch blimp (as unmanned plane), has satisfied the use needs thus.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
The specific embodiment
As shown in Figure 1, between preceding traction sheave 6 and back traction sheave 2, be socketed with drag rope 5, on drag rope 5, be provided with traction slide block 4.The bottom surface of meander sections is provided with traction slide block slide rail 14 on drag rope 5, is provided with traction slide block return actuating device 15 on the turning down section of messenger rope 5.Tension wheel 13 is located at the below of the turning down section of drag rope 5, is provided with tension wheel driver train 12 in the bottom of tension wheel 13, and the position that moves up and down by control tension wheel 13 reaches the effect of the degree of tension of control drag rope 5.On the turning down section of meander sections on the drag rope 5 and drag rope 5, be respectively equipped with drag rope brake actuator 3.
Among Fig. 1, the utility model is provided with the identical or different driver train of two nested structures, and wherein, preceding traction sheave 6 joins with front driving mechanism, and back traction sheave 2 joins with rear drive mechanism.In front driving mechanism and rear drive mechanism, be respectively equipped with rotation function memory device 10; The rotation function memory device 10 optional weighting distribution wheel forms that are made as routine.
Among Fig. 1, front driving mechanism is that the termination at main drive shaft 8 has forerunner's motivation 11, traction sheave 6 before the other end connects by friction clutch 7; On friction clutch 7, be connected to clutch actuator 9; Rotation function memory device 10 is installed in the middle part of main drive shaft 8.For the work that makes friction clutch 7 keeps normal, be provided with apparatus for cooling clutch 1 in the periphery of friction clutch 7.
Principle of work of the present utility model is:
The first step: new field of technical activity
1, will connect at the traction slide block 4 of initial position (A place) and the aircraft that will launch;
2, start driving machine (electrical motor or steam turbine) in front driving mechanism and the rear drive mechanism simultaneously, make main drive shaft 8 and rotation function memory device 10 reach desired speed;
3, tension wheel 13 is separated with drag rope 5 at low level, and drag rope 5 is no tension force relaxed state;
4, drag rope brake actuator 3 is releasing orientation;
5, all separated attitude of the friction clutch in the forward and backward driver train;
6, former and later two apparatus for cooling clutch 1 remain work at this ejector on period.
Second step: launch acceleration phase
1, under the effect of tension wheel actuating device 12, tension wheel 13 upward movements compress drag rope 5 and make drag rope 5 produce predetermined tension force;
2, startup clutch actuator 9 makes friction clutch 7 closures, and preceding traction sheave 6 quickens to rotate with back traction sheave 2, moves ahead fast thereby the aircraft on drive drag rope 5 and traction slide block 4 and the launching cradle is acceleration mode;
3, at this moment, driving machine 11 and rotation function memory device 10 all begin to do uniformly retarded motion from its predetermined working speed.
The 3rd step: launch and subtract acceleration (acceleration/accel reduces) stage
1, when traction slide block 4 arrives the B point, clutch actuator 9 control friction clutches 7 begin to enter released state, because the elasticity of drag rope 5 discharges, traction slide block 4 is entered subtract acceleration phase (time is very short), this moment, driving machine 11 reached the predetermined minimum speed of work;
2, simultaneously, tension wheel 13 moves down under the driving of tension wheel actuating device 12 fast, makes the tension force of drag rope 5 be reduced to zero rapidly;
3, when traction slide block 4 arrived C points, aircraft arrived predetermined takeoff speed, and at this moment, the draw power of 4 pairs of aircrafts of traction slide block reduces to zero, and aircraft breaks away from and draws slide block 4 and take off under the promotion of self driving engine.
The 4th step: ejector deboost phase
1, when traction slide block 4 arrives the C point, because the effect of force of inertia, drag rope 5 and traction slide block 4 continue motion, at this moment, start drag rope brake actuator 3 simultaneously, make drag rope 5 brake snub; When traction slide block 4 reaches terminal point (D point), drag rope 5 stop motions;
2, the rotation function memory device 10 of this moment driving machine 11 and its driving begins to quicken from its minimum working speed.
The 5th step: ejector enters the new field of technical activity
1, after preceding traction sheave 6 and back traction sheave 2 stalls, unclamps two drag rope brake actuators 3;
2, start traction slide block return actuating device 15, make traction slide block 4 return reference position (A point), prepare to enter next and launch working cycle;
3, make the rotation function memory device 10 of driving machine 11 and its driving reach predetermined startup working speed, enter next and launch circulation.
Data computation example of the present utility model is as follows:
Zui Da C-13-1 type steam catapult can launch away 36.3 tons carrier-borne aircraft in 94.6 meters stroke with the high speed of 95 meter per seconds in the world.The steam catapult total weight launches maximum output energy at every turn and can reach 95 megajoules near 500 tons, institute's energy requirement 〉=95 ÷ 0.06=1583 megajoules, and phase shorter workweek is 45 seconds, and is as follows with this budgetary estimate:
One, it is as follows condition to be set:
1, pre-power mooring system---the stressed maximum thrust that reaches of aircraft can be started, and aircraft is done equal accelerated movement in outfit;
2, played 36.3 tons of aircraft deadweights, selected for use AL-31F aero-engine (two), thrust=12500 kgfs * 2=25 ton force;
3, catapulting distance is made as 95 meters;
4, drag rope is selected linear contact lay wire rope for use, and diameter of phi 56, weighs 2.4 tons altogether by long 210 meters;
5, the traction slide block is 0.4 ton, the diameter of phi 3000mm of two traction sheaves, 5 tons of the resistances of hauling rope system (comprising hauling rope, traction slide block, traction sheave and tension wheel);
6, the root diameter Φ 2800mm of rotation function accumulator is about 1000mm, adopts steel weighting distribution wheel structure, rotates with driving machine, and its rotor inertia sum is a J=47530 kilogram-metre rice;
7, select the circular cone type friction clutch for use, friction material is bakelite and hard steel (friction coefficient 0.35, the mid diameter Φ 2800 of circular cone running surface, vertex of a cone half-angle=20 ℃, the effective thrust of two clutch actuators=4.11 tractions.
Two, be calculated as follows:
1, required pure thrust F=36.3 * 95 * 95 ÷ (2 * the 95)=1725KN=172.5 ton force that is subjected to of aircraft
2, departure time T=95 * 2 ÷ 95=2 second
3, aircraft acceleration/accel a=95 ÷ 2=47.5 meter per second * second, transship 47.5 ÷ 9.8=4.85g
4, the required effective merit of this ejector:
Q=(172.5-25+2.4+0.4+5) * 9.8 * 95=144584KJ=144.6, million Jiao
5, the effective thrust of separate unit clutch actuator=155.3 * 4.11 ÷ 2=319.14 ton forces;
6, originally penetrating device launches and finishes moment rotation function accumulator rotor speed and should be not less than (friction clutch engages) V0=604 rev/min; At this moment, two the contained kinetic energy of rotation function accumulator=190.15 million Jiao;
7, do uniformly retarded motion at ejection process rotation function accumulator, merit (Q)=two a rotation function accumulator of the energy (work done of friction force institute) that two circular cone type friction clutch ejection process consume+take off consumption plays bullet and finishes the difference of contained kinetic energy of moment, the rotating speed of rotation function accumulator when having drawn bullet thus: Vq=1045 rev/min;
Two energy=233,000,000 Jiao (product of friction moment and corner) that circular cone type friction clutch ejection process consumes;
Single ejection process ejector wastage in bulk or weight energy=144.6+233=377.6 million Jiao;
The mechanical efficiency of this ejector=144.6 ÷ 377.6=38%;
Two rotation function accumulators work contained kinetic energy=569.19 million Jiao when playing;
8, this ejector phase shorter workweek of launching got 20 seconds, and the power of two main drive motors=377.6 ÷, 20 ÷ 2=9.44 megawatts=0.944 ten thousand KW then is so take the frequency control motor of two 10,000 KW;
9, this ejector circular cone type friction clutch adopts cooled with seawater, and the Inlet and outlet water temperature difference is decided to be 20 ℃, and then single launches cycling use of water amount 〉=233 * 1000 ÷ 84=2774 (kg)=2.8 tons, cooling water flow=2.8 * 3=9 cubic meter/minute;
10, this ejector launches setup time=569.19 ÷ 20=28.5 second for the first time;
11, this ejector because the efficient of steam-electric power (containing steam turbine and electrical generator) is about 35%, consolidates the efficient=38% * 35%=13% of ejector again as using direct motor drive;
This ejector because Efficiency of Steam Turbine is about 38%, consolidates the efficient=38% * 38%=14% of ejector as using turbine drive.
If the driving machine of this ejector uses electrical motor, then can use two (or one) vector control frequency control devices to control, go out according to the calculation of parameter such as performance of institute's cataplane:
A. the propulsive effort of drag rope clamping system (by tensile force decision);
B. the actuating force of circular cone type friction clutch adapter (by tractive force decision);
C. the bullet speed that rises of rotation function accumulator.
After system adjusted accordingly, this ejector was the various types of aircrafts of ejectable, as unmanned plane etc.
Below only be the calculating of proof feasibility of the present utility model, concrete enforcement need be carried out the detail design of each parts and test correction.
Claims (6)
1. shipborne aircraft catapult, between preceding traction sheave (6) and back traction sheave (2), be socketed with drag rope (5), on drag rope (5), be provided with traction slide block (4), it is characterized in that, traction sheave (6) joins with front driving mechanism before described, and described back traction sheave (2) joins with rear drive mechanism; In described front driving mechanism and described rear drive mechanism, be respectively equipped with rotation function memory device (10); Below in the turning down section of described drag rope (5) is provided with tension wheel (13), is provided with the tension wheel driver train (12) that the described tension wheel of control moves up and down in the bottom of described tension wheel (13).
2. shipborne aircraft catapult according to claim 1 is characterized in that, described front driving mechanism is that the termination at main drive shaft (8) has forerunner's motivation (11), and the other end connects preceding traction sheave (6) by friction clutch (7); On described friction clutch (7), be connected to clutch actuator (9); Described rotation function memory device (10) is installed on the described main drive shaft (8).
3. shipborne aircraft catapult according to claim 2 is characterized in that, is provided with apparatus for cooling clutch (1) in the periphery of described friction clutch (7).
4. shipborne aircraft catapult according to claim 2 is characterized in that, described rotation function memory device (10) is a weighting distribution wheel.
5. according to claim 1,2,3 or 4 described shipborne aircraft catapults, it is characterized in that, be provided with traction slide block slide rail (14) in the bottom surface of the last meander sections of described drag rope (5), on the turning down section of described drag rope (5), be provided with traction slide block return actuating device (15).
6. according to claim 1,2,3 or 4 described shipborne aircraft catapults, it is characterized in that, be provided with drag rope brake actuator (3) in the last meander sections of described drag rope (5) and/or the turning down section of described drag rope (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202315111U CN201784808U (en) | 2010-06-22 | 2010-06-22 | Launching catapult for carrier-based aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202315111U CN201784808U (en) | 2010-06-22 | 2010-06-22 | Launching catapult for carrier-based aircraft |
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| Publication Number | Publication Date |
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| CN201784808U true CN201784808U (en) | 2011-04-06 |
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| CN2010202315111U Expired - Fee Related CN201784808U (en) | 2010-06-22 | 2010-06-22 | Launching catapult for carrier-based aircraft |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717895A (en) * | 2012-07-10 | 2012-10-10 | 马敏 | Continuous ejection ejector |
| CN102862684A (en) * | 2011-07-05 | 2013-01-09 | 王长存 | Novel aircraft carrier flying-off deck |
| CN103129745A (en) * | 2011-11-28 | 2013-06-05 | 丁陶生 | Method and device of whole course uniformly-accelerated mechanical traction high-speed take-off of shipboard aircraft |
| CN103183133A (en) * | 2013-03-26 | 2013-07-03 | 张本胜 | Ejector of aircraft carrier shipboard aircraft |
| CN104890893A (en) * | 2014-03-09 | 2015-09-09 | 徐延明 | Aircraft carrier catapult |
| CN105398580A (en) * | 2015-12-11 | 2016-03-16 | 戴金钟 | Plane catapulting device |
| CN105501458A (en) * | 2014-09-24 | 2016-04-20 | 田忠林 | Track block chain shipboard aircraft catapult |
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN105857635A (en) * | 2015-12-11 | 2016-08-17 | 杨 | Differential aircraft carrier catapult |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| CN109131923A (en) * | 2018-10-29 | 2019-01-04 | 陈穗 | A kind of pull-type auxiliary taking-off system of airplane peculiar to vessel |
| WO2019205726A1 (en) * | 2018-04-23 | 2019-10-31 | Han Peizhou | Aircraft carrier aircraft takeoff catapult equipment |
| CN112704864A (en) * | 2020-12-10 | 2021-04-27 | 北京航天益森风洞工程技术有限公司 | Athlete ejection device for ice and snow sports |
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2010
- 2010-06-22 CN CN2010202315111U patent/CN201784808U/en not_active Expired - Fee Related
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102862684A (en) * | 2011-07-05 | 2013-01-09 | 王长存 | Novel aircraft carrier flying-off deck |
| CN103129745B (en) * | 2011-11-28 | 2016-08-03 | 丁陶生 | Carrier-borne aircraft omnidistance even acceleration mechanical traction high speed takeoff method and device |
| CN103129745A (en) * | 2011-11-28 | 2013-06-05 | 丁陶生 | Method and device of whole course uniformly-accelerated mechanical traction high-speed take-off of shipboard aircraft |
| CN102717895B (en) * | 2012-07-10 | 2015-10-14 | 济南弘毅格致科贸有限公司 | A kind of ejection ejector continuously |
| CN102717895A (en) * | 2012-07-10 | 2012-10-10 | 马敏 | Continuous ejection ejector |
| CN103183133A (en) * | 2013-03-26 | 2013-07-03 | 张本胜 | Ejector of aircraft carrier shipboard aircraft |
| CN104890893A (en) * | 2014-03-09 | 2015-09-09 | 徐延明 | Aircraft carrier catapult |
| CN105501458B (en) * | 2014-09-24 | 2018-05-08 | 田忠林 | Rail sliding car chain carrier-based aircraft ejector |
| CN105501458A (en) * | 2014-09-24 | 2016-04-20 | 田忠林 | Track block chain shipboard aircraft catapult |
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN105857635A (en) * | 2015-12-11 | 2016-08-17 | 杨 | Differential aircraft carrier catapult |
| CN105398580B (en) * | 2015-12-11 | 2017-11-24 | 南京涵曦月自动化科技有限公司 | Aircraft ejection kit |
| CN105398580A (en) * | 2015-12-11 | 2016-03-16 | 戴金钟 | Plane catapulting device |
| CN105857635B (en) * | 2015-12-11 | 2018-07-24 | 杨�一 | Differential aircraft carrier ejector |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| WO2019205726A1 (en) * | 2018-04-23 | 2019-10-31 | Han Peizhou | Aircraft carrier aircraft takeoff catapult equipment |
| CN109131923A (en) * | 2018-10-29 | 2019-01-04 | 陈穗 | A kind of pull-type auxiliary taking-off system of airplane peculiar to vessel |
| CN112704864A (en) * | 2020-12-10 | 2021-04-27 | 北京航天益森风洞工程技术有限公司 | Athlete ejection device for ice and snow sports |
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| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110406 Termination date: 20130622 |