CN101607602A - A kind of launching power method and device - Google Patents
A kind of launching power method and device Download PDFInfo
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- CN101607602A CN101607602A CNA2008100391014A CN200810039101A CN101607602A CN 101607602 A CN101607602 A CN 101607602A CN A2008100391014 A CNA2008100391014 A CN A2008100391014A CN 200810039101 A CN200810039101 A CN 200810039101A CN 101607602 A CN101607602 A CN 101607602A
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Abstract
The invention discloses a kind of launching power method and device.The objective of the invention is to overcome the prior art shortcoming, provide a kind of power own little, in light weight, volume is little, and big a kind of launching power method and the device of launch power.Described method is to link to each other with the inertia energy storage device of a quality greater than emitter by the power system that will make circumference power, power system constantly inputs to the inertia energy storage device with energy, the energy that the inertia energy storage device can be imported power system stores energy accumulation with the form of rotor inertia, thereby become a huge rotor inertia, pass to emitter by power-transfer clutch moment, make emitter obtain enough energy in moment, thereby be accelerated to predefined speed, reach the purpose that emitter is launched.Described device comprises power system, inertia energy storage device, power-transfer clutch, kinetic energy output unit, emitter.The present invention is used for the emission of automobile, aircraft testing etc.
Description
Technical field
The present invention relates to a kind of power system, particularly a kind of launching power method and device.
Technical background
Power system is to be used to launch the usual means that automobile is used for vehicle impact testing and aircraft, but because the big speed of quality of automobile and aircraft is fast, so dynamic system power is required height, thereby the volume and weight of feedway is increased, test and use cost increase.Though now also have correlation technique that the power feedway has been carried out some improvement, as application number 94115859.4 denominations of invention " airplane catapult and recovery system " of Patent Office of the People's Republic of China in the 1997.04.02 bulletin, launch by adopting steel rope and piston directly to encircle ways of connecting, though this invention is reliable and practical, speed is fast, the efficient height is suitable for characteristics such as production domesticization, but is difficult to accomplish the launch plane desired power from technology.And for example Patent Office of the People's Republic of China is that 01807253.4 denomination of invention " a kind of accelerator device " exists the needed requirement of power out of reach launch plane too in the number of patent application of 2003.05.21 bulletin.And United States Navy employed be to adopt the steam openings cylinder of 1 meter of diameter to promote aircraft, each quantity of steam that uses is up to 1 ton, but the complicated volume of this device manufacturing process is big, weight is big, is unfavorable for installing and using, and has occupied the big quantity space and the load carrying ability of ship simultaneously.It is little, in light weight to be badly in need of solving a kind of power own now, and volume is little, and big launching power method and the device of launch power.
Summary of the invention
The objective of the invention is to overcome above-mentioned shortcoming, provide a kind of power own little, in light weight, volume is little, and big a kind of launching power method and the device of launch power.
For this reason, the invention provides a kind of launching power method and device, described method is to link to each other with the inertia energy storage device of a quality greater than emitter by the power system that will make circular movement, power system constantly inputs to the inertia energy storage device with energy, the energy that the inertia energy storage device can be imported power system stores energy accumulation with the form of rotor inertia, thereby become a huge rotor inertia, pass to emitter by power-transfer clutch moment, make emitter obtain enough energy, thereby be accelerated to predefined speed in moment; Reach the purpose that emitter is launched.Described device comprises power system, inertia energy storage device, power-transfer clutch, kinetic energy output unit, emitter, wherein said power system links to each other with the inertia energy storage device, power system constantly inputs to the inertia energy storage device with the energy, and the energy that the inertia energy storage device can be imported power system stores energy accumulation with the form of rotor inertia; Described power-transfer clutch links to each other with the inertia energy storage device, and the transfer of energy effect does not take place when power-transfer clutch is inoperative between the two; When power-transfer clutch worked, power-transfer clutch passed to the kinetic energy output unit that links together with the energy of the inertia energy storage device mode by friction force, and described kinetic energy output unit links to each other with emitter, and emitter obtains to be launched away behind the kinetic energy.Described inertia energy storage device is a flywheel.As a low power electrical motor is linked to each other with a heavy weight flywheel, the weight of flywheel is greater than the weight of the emitter that will launch, by constantly rotating of electrical motor with flywheel, make the rotating speed of flywheel reach the rotating speed close at last with electrical motor, because flywheel is to make circular movement, the linear velocity of flywheel can be much larger than the speed of emitter, so the energy that flywheel is stored is energy needed when emitter is launched, so when power-transfer clutch is given emitter with the transfer of energy of flywheel, because the emission energy needed is the very little part of flywheel, so flywheel can't stop the rotation because having driven emitter when being subjected to rubbing, still with than original low slightly speed rotation, and emitter obtains to be launched away behind the energy from flywheel.The present invention accumulates the acquisition energy by the improving constantly of rotative speed of flywheel, and in abrupt release, thereby has solved the problem of power effectively.
In another kind of launching power method provided by the invention and device, described power-transfer clutch is a friction clutch, and friction clutch mode ratio is easier to make and control.Certainly, according to different situations and demand, also can adopt centrifugal clutch or other power-transfer clutch.The frictional power system is arranged on described friction clutch, the frictional power system can accurately control the size of friction force, just can accurately control the size of the power that gives emitter by the size of accurate control friction force, accurately control the speed that the power size that gives emitter just can accurately be controlled emitter.Described frictional power system can be a hydraulic efficiency servo, and hydraulic efficiency servo is controlled easily and operated.In order to reduce the interference of other uncertainty to frictional power, the mounting plane bearing transmits power-transfer clutch by surface bearing with frictional power between frictional power system and friction lining.
In another kind of launching power method provided by the invention and the device, described power take-off implement is a wire rope drum, and around steel rope, steel rope links to each other with emitter on the cylinder.When under the effect of power-transfer clutch in frictional power with after flywheel links to each other, power-transfer clutch will little by little rotate with speed with flywheel, the wire rope drum that links to each other with power-transfer clutch also will little by little rotate with flywheel synchronously, steel rope on the wire rope drum is synchronized with the movement with wire rope drum too, its speed is controlled by the diameter and the rotating speed of wire rope drum, thereby is accelerated under the pulling of steel rope.On the steel rope of wire rope drum and emitter uncoupling rigging is installed, after emitter reached predefined speed, emitter broke away from by uncoupling rigging and steel rope, thereby is launched away.As required, power take-off implement also can be installed speed change system, adjusts emission rate.
Launching power method provided by the invention and device are compared with existing method and are had the following advantages:
1. device is simple: device of the present invention is more simple in structure than existing emission coefficient;
2. volume is little in light weight: with U.S.'s like product ratio, volume has only 1/10th, and weight has only 1/4th;
3. low cost of manufacture: product of the present invention has only 1/5th of like product.
Embodiments of the invention below by accompanying drawing is described can more be expressly understood design of the present invention, method.
Description of drawings
Accompanying drawing 1 is the principle schematic of an embodiment of a kind of launching power method provided by the invention and device.
The specific embodiment
With reference to accompanying drawing 1, accompanying drawing 1 has been described the principle schematic of an embodiment of a kind of launching power method provided by the invention and device: electrical motor 1 passes to flywheel 3 with energy by belt pulley 2, and the weight of flywheel 3 is much larger than the weight of aircraft 12; When friction clutch 4 did not contact with flywheel 3, flywheel 3 was constantly stored the energy that electrical motor 1 passes under the drive of electrical motor 1, and along with the continuous increase of energy, speed is more and more faster, and the energy of storage is more and more.When launching, hydraulic servo power system 5 is given surface bearing 7 by center shaft 6 with transmission of pressure, and center shaft 6 is fixing by bracing frame 10, and center shaft 6 can move up and down for 10 li at bracing frame, and bracing frame 10 is fixing by attachment point 9; Surface bearing 7 is between center shaft 6 and kinetic energy output unit 8, and by the effect of surface bearing 7, center shaft 6 can not rotate thereupon and keep motionless when 8 rotations of kinetic energy output unit.Under the pressure effect of hydraulic servo power system 5, friction clutch 4 produces rubbing effect with flywheel 3, energy output device 8 begins rotation under the effect of friction force, the also motion simultaneously of steel rope 13 above during energy output device 8 rotations, steel rope 13 motion drive uncoupling riggings 11 and the aircraft 12 that is attached thereto move together.According to the friction force law, the size of friction force equals the product of pressure and friction coefficient, and friction coefficient is certain; Therefore, pressure is big more, the friction force that produces is just big more, requirement according to the weight of aircraft 12, runway distance, takeoff speed, can determine the size of the pulling force of steel rope 13, the pulling force of having determined steel rope 13 just can be known needs great friction force, needs great friction force just can determine that hydraulic efficiency servo 5 need provide great pressure.Because the weight of flywheel 3 is much larger than the weight of aircraft 12, the rotating speed of flywheel 3 is also much larger than the aircraft 12 needed speed of taking off, so flywheel 3 can drive aircraft fully simultaneously.When aircraft 12 arrives taking off during the place of runways, uncoupling rigging 11 separates with aircraft 12.
Above described embodiment be that the present invention will be described, be not that the present invention is limited.Design, method and scope that the present invention is claimed all are documented in claims of the present invention.
Claims (10)
1. launching power method and device, it is characterized in that: described method is to link to each other with the inertia energy storage device of a quality greater than emitter by the power system that will make circumference power, power system constantly inputs to the inertia energy storage device with energy, the energy that the inertia energy storage device can be imported power system stores energy accumulation with the form of rotor inertia, thereby become a huge rotor inertia, pass to emitter by power-transfer clutch moment, make emitter obtain enough energy, thereby be accelerated to predefined speed in moment; Reach the purpose that emitter is launched.
2. launching power method according to claim 1 and device, it is characterized in that: described device comprises power system, inertia energy storage device, power-transfer clutch, kinetic energy output unit, emitter, wherein said power system links to each other with the inertia energy storage device, power system constantly inputs to the inertia energy storage device with the energy, and the energy that the inertia energy storage device can be imported power system stores energy accumulation with the form of rotor inertia; Described power-transfer clutch links to each other with the inertia energy storage device, and the transfer of energy effect does not take place when power-transfer clutch is inoperative between the two; When power-transfer clutch worked, power-transfer clutch passed to the kinetic energy output unit that links together with the energy of the inertia energy storage device mode by friction force, and described kinetic energy output unit links to each other with emitter, and emitter obtains to be launched away behind the kinetic energy.
3. launching power method according to claim 2 and device is characterized in that: described inertia energy storage device is a flywheel.
4. launching power method according to claim 1 and 2 and device is characterized in that: described power-transfer clutch is a centrifugal clutch.
5. launching power method according to claim 1 and 2 and device is characterized in that: described power-transfer clutch is a friction clutch.
6. launching power method according to claim 5 and device is characterized in that: the frictional power system is arranged on the described friction clutch, and the frictional power system can accurately control the size of friction force.
7. launching power method according to claim 6 and device is characterized in that: described frictional power system is a hydraulic efficiency servo.
8. according to claim 5 or 6 described launching power method and devices, it is characterized in that: pass through the surface bearing transferring power between frictional power system and the friction lining.
9. launching power method according to claim 2 and device is characterized in that: described power take-off implement is a wire rope drum, and around steel rope, steel rope links to each other with emitter on the cylinder.
10. launching power method according to claim 9 and device is characterized in that: on described and the steel rope that emitter links to each other uncoupling rigging is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100391014A CN101607602A (en) | 2008-06-18 | 2008-06-18 | A kind of launching power method and device |
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| Application Number | Priority Date | Filing Date | Title |
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| CNA2008100391014A CN101607602A (en) | 2008-06-18 | 2008-06-18 | A kind of launching power method and device |
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| CN101607602A true CN101607602A (en) | 2009-12-23 |
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| CNA2008100391014A Pending CN101607602A (en) | 2008-06-18 | 2008-06-18 | A kind of launching power method and device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103357766A (en) * | 2012-03-29 | 2013-10-23 | 上海汇众汽车制造有限公司 | Complex spin-riveting head, spin-riveting machine, and press-fitting and spin-riveting complex assembly process for automotive ball pins |
| CN104890893A (en) * | 2014-03-09 | 2015-09-09 | 徐延明 | Aircraft carrier catapult |
| CN105015790A (en) * | 2015-08-17 | 2015-11-04 | 陈穗 | Airplane takeoff assisting system of marine worm and wormwheel device |
| CN106809403A (en) * | 2017-02-08 | 2017-06-09 | 田艳东 | The launching apparatus of middle light aircraft device |
| CN106864765A (en) * | 2015-12-11 | 2017-06-20 | 章华正 | flywheel ejector |
| CN112298595A (en) * | 2020-11-20 | 2021-02-02 | 江西洪都航空工业股份有限公司 | Unmanned aerial vehicle rotary launching device and launching method |
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| EP0777603B1 (en) * | 1994-09-15 | 1998-12-16 | Airscrew Howden Limited | Launching projectiles |
| CN1419508A (en) * | 2000-02-24 | 2003-05-21 | 弗雷德里克·让-皮埃尔·德莫勒 | An acceleration system |
| JP3426369B2 (en) * | 1994-11-04 | 2003-07-14 | 日野自動車株式会社 | Glider towing method |
| US20060175463A1 (en) * | 2003-01-17 | 2006-08-10 | The Insitu Group, Inc. | Methods and apparatuses for launching, capturing, and storing unmanned aircraft, including a container having a guide structure for aircraft components |
| CN101081639A (en) * | 2006-06-02 | 2007-12-05 | 珠海星宇模型实业有限公司 | Ejecting system applied for unmanned aerial plane launching system |
-
2008
- 2008-06-18 CN CNA2008100391014A patent/CN101607602A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0777603B1 (en) * | 1994-09-15 | 1998-12-16 | Airscrew Howden Limited | Launching projectiles |
| JP3426369B2 (en) * | 1994-11-04 | 2003-07-14 | 日野自動車株式会社 | Glider towing method |
| CN1419508A (en) * | 2000-02-24 | 2003-05-21 | 弗雷德里克·让-皮埃尔·德莫勒 | An acceleration system |
| US20060175463A1 (en) * | 2003-01-17 | 2006-08-10 | The Insitu Group, Inc. | Methods and apparatuses for launching, capturing, and storing unmanned aircraft, including a container having a guide structure for aircraft components |
| CN101081639A (en) * | 2006-06-02 | 2007-12-05 | 珠海星宇模型实业有限公司 | Ejecting system applied for unmanned aerial plane launching system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103357766A (en) * | 2012-03-29 | 2013-10-23 | 上海汇众汽车制造有限公司 | Complex spin-riveting head, spin-riveting machine, and press-fitting and spin-riveting complex assembly process for automotive ball pins |
| CN103357766B (en) * | 2012-03-29 | 2016-01-13 | 上海汇众汽车制造有限公司 | Compound is revolved die, riveter and car ball stud and is press-fited and revolve riveting Applying Compound Assembling Technology |
| CN104890893A (en) * | 2014-03-09 | 2015-09-09 | 徐延明 | Aircraft carrier catapult |
| CN105015790A (en) * | 2015-08-17 | 2015-11-04 | 陈穗 | Airplane takeoff assisting system of marine worm and wormwheel device |
| CN106864765A (en) * | 2015-12-11 | 2017-06-20 | 章华正 | flywheel ejector |
| CN106809403A (en) * | 2017-02-08 | 2017-06-09 | 田艳东 | The launching apparatus of middle light aircraft device |
| CN112298595A (en) * | 2020-11-20 | 2021-02-02 | 江西洪都航空工业股份有限公司 | Unmanned aerial vehicle rotary launching device and launching method |
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Application publication date: 20091223 |