CN200960980Y - Ejecting system applied to unmanned machine transmission system - Google Patents
Ejecting system applied to unmanned machine transmission system Download PDFInfo
- Publication number
- CN200960980Y CN200960980Y CN 200620059810 CN200620059810U CN200960980Y CN 200960980 Y CN200960980 Y CN 200960980Y CN 200620059810 CN200620059810 CN 200620059810 CN 200620059810 U CN200620059810 U CN 200620059810U CN 200960980 Y CN200960980 Y CN 200960980Y
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- unmanned aerial
- elastic body
- coaster
- ejection
- support body
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- 230000005540 biological transmission Effects 0.000 title 1
- 230000000694 effects Effects 0.000 claims description 8
- 230000033001 locomotion Effects 0.000 claims description 6
- 230000003068 static effect Effects 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 abstract 3
- 239000010959 steel Substances 0.000 abstract 3
- 238000000034 method Methods 0.000 description 4
- 230000035508 accumulation Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 239000000806 elastomer Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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Abstract
The utility model relates to an unmanned aerial vehicle system, more particularly to an ejecting system for an unmanned aerial vehicle launching system which comprises a pulley and a power system, wherein the pulley moves along a guide way under the function of the power system which comprises a retractable elastic body and further comprises a winch truck and a steel cable, wherein, one end of the steel cable is connected to the winch truck and the other end is connected to the pulley, and furthermore the steel cable flexibly connected with the free end of the elastic body and the other end of the elastic body is fixed still. The utility model utilizes the energy instant output stored by the elastic body as the power of the unmanned aerial vehicle ejecting system and utilizes guide way to speed for the unmanned aerial vehicle, and thereby the project that the unmanned aerial vehicle can leave the guide way after reaching a certain initial speed can be achieved and the using cost can be reduced. Meanwhile, the utility model with simple structure is convenient to master and use, thereby achieving the requirements of being safe, easy and reliable to use.
Description
Technical field
The utility model relates to a kind of Unmanned Aircraft Systems (UAS), particularly a kind of ejection system that is applied to unmanned aerial plane launching system.
Background technology
Unmanned plane (UAV) is the abbreviation of " robot airplane ", mainly relies on radio telecommand or realizes Autonomous Control flight by modes such as autopilots.It is one of current advanced technological arms, extensively applies to many warlike operations such as battle reconnaissance, electronic countermeasure, air attack, is described as " prying eyes " and " trump card " of modern battlefield.At present, the UAV emission coefficient of China mainly adopts hydraulic pressure, pneumatic, these several launch modes of rocket assist.These several launch modes exist complex structure, make the use cost height, the problem of maintenance difficulty.The safety measure of using as the transportation of booster rocket, storage requires high, for its use brings very big inconvenience.And the rocket assist emission coefficient, because of rocket can not repeated usage, each launch cost only one in rocket just needs thousands of units.The manufacturing cost of hydraulic pressure emission coefficient is up to 1,000,000 yuan.。
The utility model content
The purpose of this utility model is, a kind of simple in structure, cheap, ejection system that is applied to unmanned aerial plane launching system that can be reusable, safe and reliable is provided.
The purpose of this utility model realizes by the following technical solutions:
A kind of ejection system that is applied to unmanned aerial plane launching system, described ejection system comprise a coaster and a power system, described coaster under the effect of described power system along a guide rail movement; Described power system comprises an elastic body that can stretch and shrink.
Described power system also comprises a winch truck, a cable wire; Described cable wire one termination is gone into described winch truck, and an end links to each other with described coaster, and described cable wire links to each other with described elastomeric free end versatilely, and the described elastomeric other end maintains static.
Described elastic body is the elastic bundle.
Described elastic body is the spring bundle.
The utility model utilizes energy moment output that elastic body the accumulates power as unmanned aerial vehicle ejecting, utilizes guide rail to quicken to unmanned plane, makes unmanned plane reach the scheme of leaving guide rail behind certain rate of onset; The most basic low price of utilizing, the energy storage characteristic of the elastic body that can be repeatedly used (elastic) applies in the concrete UAV emission coefficient, reaches the reduction use cost; Native system is simple in structure simultaneously, is convenient to grasp, and is easy to use, reaches safe, the easy and failure-free requirement when using.
Description of drawings:
Fig. 1 is a kind of scheme drawing of unmanned aerial plane launching system;
Fig. 2 is the scheme drawing of the utility model ejection system.
Fig. 3 is the scheme drawing of the running block of the utility model ejection system
The specific embodiment
Embodiment one
As shown in Figure 1, a kind of unmanned aerial plane launching system comprises guide track system, ejection system, control system and propulsion source; Described ejection system and brake system are arranged on the described guide track system; Described control system is controlled described ejection system and guide track system, and propulsion source provides the energy for whole emission coefficient.
As shown in Figure 2, for being applied to the ejection system of unmanned aerial plane launching system shown in Figure 1, described ejection system comprises power system and coaster 1, described coaster 1 can be under the effect of described power system guide rail 2 in the described guide track system move, unmanned plane is placed on the described coaster 1 by the body carriage, by body locking and releasing mechanism locking.Described power system comprises winch truck 5, a cable wire 6 and the elastic body 7 that can stretch and shrink under described drive power source, and adopts the elastic bundle in the present embodiment; Described cable wire 6 one terminations are gone into described winch truck 5, one end links to each other with described coaster 1, and described cable wire 6 links to each other with the free end of described elastic body 7 versatilely, and the other end of described elastic body 7 is fixed on support body 4 one ends 41 in the described guide track system (or claiming rear end); For the size of measuring the elastic body energy accumulation can installed resistance dynamometer near on the elastic body of support body rear end.Described winch truck 5 is fixed on the described support body 4, and its position and described terminal 41 distance are greater than the extreme length in when elongation in described elastic body 7 mode of operations.When described coaster 1 was fixed on initial position by safety pin and hub lock releasing, described elastic body 7 was stretched under the effect of described winch truck 5 and cable wire 6, accumulates elastic energy.If the power drive shaft owner on the described coaster 1 is made up of main shaft bearing and rotatable cable connector and the wheel disc etc. of going in ring; Described cable wire 6 joins by described rotatable belt cable connector and described coaster 1.
Free end at described elastic body 7 is connected with a running block 3, and described cable wire 6 is movably connected by the free end of described running block 3 with described elastic body 7.As shown in Figure 3, described running block 3 comprises that one roughly is the support body 31 of " well ", correspondence is equipped with steady wheel 32 on the both lateral sides limit of described support body 31, under the effect of described steady wheel, described running block 3 can be in the described support body 4 under the drive of described cable wire 6 along an orbiting motion of support body elongated lengthwise.Described movable pulley 33 be installed in limit, described support body 31 vertical left side on, present embodiment is defined as 33 cores of movable pulley; The free end of described elastic body 7 is connected on the described support body 31 vertical right edge.The described elastic body that will stretch when described running block 3 moves under the effect of described cable wire 6 makes it accumulate elastic energy.Also be to drive described cable wire 6 by described running block 3 further to drive described coaster motion when described elastic body releases energy, for described unmanned plane provides rate of onset.
In order to make described cable wire 6 drive described running block 3 motions smoothly,, one first fixed pulley 8 is set preferably between described winch truck and described running block 3 along described rope length direction; One second fixed pulley 9 is set between described running block 3 and coaster 1.Described cable wire 6 walk around described first and second fixed pulleys can be better for described elastic body 7 energy accumulations with release energy.Described first and second fixed pulleys all are fixed on the described support body 4, and described terminal 41 distance is arrived in its position, the extreme length when extending greater than described elastic body 7.
Above-mentioned introduction be the related device of accelerator of described ejection system, introduce the related device of braking procedure of described ejection system below.Described braking procedure is after being used for reducing unmanned plane and obtaining rate of onset and leave described coaster, continue with higher speed to the terminal motion of guide rail and smash described guide track system in order to prevent described coaster, even described coaster 1 flies out.In the present embodiment, the shared power system of the accelerating sections of described ejection system and described retaining segment.After unmanned plane obtains rate of onset and leaves described coaster and described coaster and stride across described second fixed pulley 9, along with the change of cable wire 6 directions, elastomeric contraction, coaster will be subjected to pulling force backward, speed reduces can not produce harmful effect to guide track system until stopping gradually.In order better to make described coaster obtain slowing down, in left side (away from described support body end 41) near described second fixed pulley, being provided with one the 3rd fixed pulley 10, when described cable wire 6 commutates under the drive of described coaster 1, and will be bigger touching the resistance that is subjected to behind described the 3rd fixed pulley 10.
The working process of described unmanned aerial plane launching system is as follows: earlier coaster is locked in the initial point of emission, unmanned plane is locked on the carriage again, insert safety pin.Propulsion source provides the energy for power system, makes elastic body reach certain elastic potential energy.Remove safety pin then, emission coefficient is in battery, and after launch intruction was assigned, the lockout mechanism of coaster was opened, and discharges coaster.Coaster is under the effect of elastomer contracts power, and during the position quicken to arrive set for unmanned plane on the guide rail of launcher by carriage, the body blocking device on the carriage is opened unmanned plane and gone up to the air from frame.Simultaneously, coaster enters the braking job procedure.Coaster is under the effect of elastomer contracts power, and slowing down also rapidly, pulsation-free obtains braking.
Embodiment two
The difference of the present embodiment and first embodiment is that described elastic body is large-scale extension spring bundle.
Embodiment three
The difference of the present embodiment and first embodiment is, the not shared power system of the described retaining segment of described ejection system.But the elastic body that independent employing can stretch comes to described coaster 1 resistance.Certainly, must be after unmanned plane takes off to the opportunity of coaster 1 resistance.Described elastic body is separately positioned on the both sides of described guide rail, and described elastic body one end is fixed, and a termination has latching device, and when described coaster 1 arrives assigned address, latching device will be hung up above-mentioned coaster.
The utility model also has other distortion such as elastomeric selection can make corresponding variation; Described cable wire can be other materials with toughness, as bigger plastic ties of intensity etc.Fixed pulley and running block also can change other reversing arrangements into.If those skilled in the art does not need performing creative labour to make corresponding variation by inspiration of the present utility model, all should fall into the protection domain of the utility model claim.
Claims (9)
1, a kind of ejection system that is applied to unmanned aerial plane launching system, described ejection system comprises a coaster and a power system, it is characterized in that, described coaster under the effect of described power system along a guide rail movement; Described power system comprises an elastic body that can stretch and shrink, a winch truck, a cable wire; Described cable wire one termination is gone into described winch truck, and an end links to each other with described coaster, and described cable wire links to each other with described elastomeric free end versatilely, and the described elastomeric other end maintains static.
2, the ejection system that is applied to unmanned aerial plane launching system according to claim 1 is characterized in that, is connected with a running block at described elastomeric free end, and described cable wire is movably connected by described running block and described elastomeric free end.
3, the ejection system that is applied to unmanned aerial plane launching system according to claim 2, it is characterized in that, described running block comprises that one roughly is the support body of " well ", correspondence is equipped with steady wheel on the both lateral sides limit of described support body, one movable pulley be installed in limit, the vertical left side of described support body on, described elastomeric free end is connected on the vertical right edge of described support body.
4, the ejection system that is applied to unmanned aerial plane launching system according to claim 2 is characterized in that, along described rope length, one first fixed pulley is set between described winch truck and described running block.
5, the ejection system that is applied to unmanned aerial plane launching system according to claim 2 is characterized in that, along described rope length, one second fixed pulley is set between described running block and coaster.
6, according to claim 4 or the 5 described ejection systems that are applied to unmanned aerial plane launching system, it is characterized in that, described first and second fixed pulleys all are fixed on the described support body, and the distance of described support body end is arrived in its present position, the extreme length when extending greater than described elastic body.
7, according to any one described ejection system that is applied to unmanned aerial plane launching system among the claim 1-5, it is characterized in that described elastic body is the elastic bundle.
8, according to any one described ejection system that is applied to unmanned aerial plane launching system among the claim 1-5, it is characterized in that described elastic body is the spring bundle.
9, the ejection system that is applied to unmanned aerial plane launching system according to claim 5 is characterized in that, the left side near described second fixed pulley is provided with one the 3rd fixed pulley.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620059810 CN200960980Y (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied to unmanned machine transmission system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620059810 CN200960980Y (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied to unmanned machine transmission system |
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| Publication Number | Publication Date |
|---|---|
| CN200960980Y true CN200960980Y (en) | 2007-10-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620059810 Expired - Fee Related CN200960980Y (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied to unmanned machine transmission system |
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| CN (1) | CN200960980Y (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101962079A (en) * | 2010-09-27 | 2011-02-02 | 吴炳发 | Catapult used on aircraft carrier |
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN102530260A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Method and system for short-distance taking off of unmanned aerial vehicles |
| CN102616383A (en) * | 2012-04-19 | 2012-08-01 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| 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 |
| CN102951297A (en) * | 2011-08-19 | 2013-03-06 | 丁陶生 | Method and device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection |
| CN105711851A (en) * | 2016-01-25 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Electric and light-weight catapult with multiple strands of rubber strings for small unmanned aerial vehicle |
| CN118953699A (en) * | 2024-10-15 | 2024-11-15 | 北京淳一航空科技有限公司 | A mobile drone launching device |
-
2006
- 2006-06-02 CN CN 200620059810 patent/CN200960980Y/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102107737B (en) * | 2010-09-19 | 2013-03-27 | 济南环太机电技术有限公司 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN101962079A (en) * | 2010-09-27 | 2011-02-02 | 吴炳发 | Catapult used on aircraft carrier |
| CN102530260A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Method and system for short-distance taking off of unmanned aerial vehicles |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN102951297A (en) * | 2011-08-19 | 2013-03-06 | 丁陶生 | Method and device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection |
| CN102951297B (en) * | 2011-08-19 | 2015-04-22 | 丁陶生 | Device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection |
| CN102616383A (en) * | 2012-04-19 | 2012-08-01 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| CN102616383B (en) * | 2012-04-19 | 2014-08-13 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| 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 |
| CN105711851A (en) * | 2016-01-25 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Electric and light-weight catapult with multiple strands of rubber strings for small unmanned aerial vehicle |
| CN118953699A (en) * | 2024-10-15 | 2024-11-15 | 北京淳一航空科技有限公司 | A mobile drone launching device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: ZHUHAI XINGYU AVIATION TECHNOLOGY CO., LTD. Free format text: FORMER NAME: ZHUHAI XINGYU MODEL INDUSTRY CO.,LTD. |
|
| CP01 | Change in the name or title of a patent holder |
Address after: Three Hongqiao Road, Guangdong province Zhuhai City Baijiao Industrial Park No. 3, zip code: 519125 Patentee after: Zhuhai Xingyu Model Industrial Co., Ltd. Address before: Three Hongqiao Road, Guangdong province Zhuhai City Baijiao Industrial Park No. 3, zip code: 519125 Patentee before: Zhuhai Xingyu Model Industrial Co., Ltd. |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20071017 Termination date: 20100602 |