CN102923312A - Small take-off launch frame for unmanned aerial vehicle - Google Patents
Small take-off launch frame for unmanned aerial vehicle Download PDFInfo
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- CN102923312A CN102923312A CN2012103971018A CN201210397101A CN102923312A CN 102923312 A CN102923312 A CN 102923312A CN 2012103971018 A CN2012103971018 A CN 2012103971018A CN 201210397101 A CN201210397101 A CN 201210397101A CN 102923312 A CN102923312 A CN 102923312A
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Abstract
The invention provides a small take-off launch frame for an unmanned aerial vehicle, and is characterized by mainly comprising a launch trolley, a trailer, a trolley slide rail, a back support frame, a front support frame, a launch rope, a windlass and a locking mechanism. The trolley is arranged on the trolley slide rail, the front support frame is arranged at the front end of the slide rail, the back support frame is arranged at the back end of the slide rail, the windlass and the locking mechanism are arranged on the back support end of the slide rail, and the windlass is connected with the trailer through a wire rope. The small take-off launch frame for the unmanned aerial vehicle, provided by the invention, has the advantages of simple structure, low cost, simple operation, high launch success rate of the unmanned aerial vehicle, safety operation, difficulty in destroying the launch rope, and long service life of the launch frame.
Description
Technical field
The present invention relates to the launching apparatus of unmanned plane, specifically a kind of SUAV (small unmanned aerial vehicle) launching catapult.
Background technology
Current military development in science and technology is rapid, and unmanned plane is closely being brought into play more and more important effect in the High-technology local war several times as information weapon equipment, and the flat pad of unmanned plane also more and more is subject to the attention of countries in the world.Unmanned aerial plane launching system has become the important step in the unmanned plane Campaign Process now, progressively develops into to carry out an urgent task, and has again the advanced weaponry equipment of adaptability.
When unmanned plane takes off on ground, mainly adopt and take off on the car launcher and the catapult-assisted take-off dual mode.Taking off on the car launcher is that unmanned plane is installed on the car launcher, under engine thrust effect on the machine, unmanned plane and launch vehicle combination body is run along common slideway is sliding, when accelerating to the unmanned plane takeoff speed, discharges unmanned plane.This launch mode exists complex structure, and it is high to make applicable cost, the maintenance hard problem.Catapult-assisted take-off is that unmanned plane is contained on the launching cradle, by power, high pressure gas or the elastic string ejector of solid-propellant booster rocket, realizes the method that zero-height ejection takes off.Wherein solid-propellant booster rocket is a solid combustion rocket engine, and this takeoff method is applicable more a kind of startup launch method, but the applicable security requirement of transportation, storage is high, has brought very large inconvenience for it is applicable; The manufacturing cost of High-Pressure Gas System is up to 1,000,000 yuan.
Summary of the invention
The purpose of this invention is to provide a kind of simple in structure, easy to operate, launching success rate is high, reused SUAV (small unmanned aerial vehicle) launching catapult.
The technical scheme that realizes the object of the invention is:
A kind of SUAV (small unmanned aerial vehicle) launching catapult, mainly by launch dolly, motorcycle, dragging track, bracket of rear mounting, front support stand, launch rope, winch, lockout mechanism form, launching dolly places on the dragging track, be provided with unmanned plane locking on the dolly and reach voluntarily unlocking structure, the pulley rail front end is provided with front support stand, dolly pulling force commutating structure, the rear end is provided with bracket of rear mounting, bracket of rear mounting at dragging track is provided with winch and lockout mechanism, and winch is connected by steel rope with motorcycle.
Described front support stand is the spider that the strut bar by adjustable-angle and direction forms.
Described dragging track is three joint folding tracks, convenient transportation, and the length of track depends on the weight of unmanned plane and the size of acceleration/accel.
The described dolly that launches is comprised of the two parts that detachably separate up and down, launches the upper track adjusting wheel of dolly, and lower locating wheel is retraining dolly and can only slide in orbit and do not go here and there outside the errant.
Describedly launch little roof and also be provided with short slideway, be used for the attitude of launching of control aircraft.
Described launch the rope be an elastic string with strong contractility, launching rope one end is connected with the fixed block of dragging track front end, the other end is connected with dolly, and the pulling force that launches rope is divided into 4-6 interval, the pulling force mean allocation in every interval by the guiding pulley on the dolly.The steel rope of winch is connected with motorcycle, and motorcycle drives motorcycle toward post-tensioning by the waist in the centre of launching rope by winch, and the length of launching rope between the fixed block of change dolly and front end changes the pulling force that launches rope.
Described lockout mechanism comprises fixing lock and safety lever energetically, and fixedly lock is a clamp-buckle, hauls dolly, and safety lever is for crossing dolly and track, and insurance is outer power releasing all, launches rear dolly and slowly stops at the ratio wheel place.
The using method of the launching cradle that this SUAV (small unmanned aerial vehicle) is taken off is:
1, will launch dolly is pulled down to the dolly starting point, locks in free state;
2, install armed unmanned plane on dolly;
3, launch rope by the winch tension, make dolly have the elastic potential energy of some strength;
4, untie little lock, the dolly potential energy converting and energy becomes kinetic energy to drive acceleration/accel of unmanned plane generation, moves to the dolly ratio wheel from starting point by dragging track, and unmanned plane reaches certain speed disengaging dolly and takes off;
5, after dolly was crossed ratio wheel, because oppositely holdback force effect, dolly was zero at deceleration final position relative velocity;
6, dolly is got back to dolly ratio wheel position under the effect of reverse holdback force;
7, unclamp winch, loosen and launch rope, dolly is pulled under the start position preparation once launches.
The invention has the beneficial effects as follows: the small-sized pilotless aircraft launching cradle is simple in structure, and cost is low, and is simple to operate, the unmanned aerial vehicle success ratio height that takes off, and safety of operation, it is not fragile to launch rope, and the launching cradle life-span is long.
Description of drawings
Fig. 1 is the unmanned plane launching cradle structural representation that takes off
Among the figure: 1. 5. dolly ratio wheels, 6. dollies, 7. motorcycles, 8. dolly starting point positions, bracket of rear mounting 2. dolly dragging tracks 3. front support stands 4. dolly deceleration final positions, 9. winchs 10. launch rope
The specific embodiment
With reference to Fig. 1, a kind of SUAV (small unmanned aerial vehicle) launching cradle that takes off, dolly 6 motorcycles 7 dragging tracks 2 bracket of rear mountings 1 front support stand 3 launches rope 10 winchs 9 and lockout mechanism forms by launching, launching dolly 6 places on the dragging track 2, be provided with unmanned plane locking on the dolly 6 and reach voluntarily unlocking structure, pulley rail 2 front ends are provided with front support stand 3 dolly pulling force commutating structures, the rear end is provided with bracket of rear mounting 1, bracket of rear mounting 1 at dragging track 2 is provided with winch 9 and lockout mechanism, and winch 9 and motorcycle 7 are connected by steel rope.
Dolly dragging track 2 is the track that connects three joint folding structures with dwang, convenient transportation, and the length of track depends on the weight of unmanned plane and the size of acceleration/accel.
Dolly 6 is comprised of the two parts that detachably separate up and down.
Dolly 6 tops also are provided with short slideway, are used for the attitude of launching of control aircraft.
Launching rope 10 is an elastic string with strong contractility, launching rope 10 1 ends is connected fixed block and connects with the slide rail front end, the other end is connected with dolly 6 by dolly ratio wheel 5, and the pulling force that launches rope 10 is divided into 4-6 interval, the pulling force mean allocation in every interval by the guiding pulley on the dolly 6.
Lockout mechanism comprises fixing lock and safety lever energetically, and fixedly lock is a clamp-buckle, hauls dolly, and safety lever crosses dolly 6 and track, and insurance all outer power is removed.
Claims (7)
1. SUAV (small unmanned aerial vehicle) launching cradle that takes off, it is characterized in that: mainly by launch dolly, motorcycle, dragging track, bracket of rear mounting, front support stand, launch rope, winch, lockout mechanism form, launching dolly places on the dragging track, be provided with unmanned plane locking on the dolly and reach voluntarily unlocking structure, the pulley rail front end is provided with front support stand, dolly pulling force commutating structure, the rear end is provided with bracket of rear mounting, bracket of rear mounting at dragging track is provided with winch and lockout mechanism, and winch is connected by steel rope with motorcycle.
2. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off is characterized in that: the spider that front support stand forms for the strut bar by adjustable-angle and direction.
3. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off, it is characterized in that: described dragging track is three joint folding tracks, convenient transportation, the length of track depends on the weight of unmanned plane and the size of acceleration/accel.
4. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off, it is characterized in that: dolly is comprised of the two parts that detachably separate up and down, launches the upper track adjusting wheel of dolly, and lower locating wheel is retraining dolly and can only slide in orbit and do not go here and there outside the errant.
5. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off, it is characterized in that: little roof also is provided with short slideway, the attitude before constraint is taken off.
6. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off, it is characterized in that: launching rope is an elastic string with strong contractility, launch one section in rope and be connected the fixed block connection with the slide rail leading portion, the other end is connected with dolly, the pulling force that launches rope is divided into 4-6 interval, the pulling force mean allocation in every interval by the guiding pulley on the dolly; The steel rope of winch is connected with motorcycle, and motorcycle drives motorcycle toward post-tensioning by the waist in the centre of launching rope by winch, and the length of launching rope between the fixed block of change dolly and front end changes the pulling force that launches rope.
7. a kind of SUAV (small unmanned aerial vehicle) according to claim 1 launching cradle that takes off is characterized in that: lockout mechanism comprises fixing lock and safety lever energetically, and fixedly lock is a clamp-buckle, and safety lever is for crossing dolly and track.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012103971018A CN102923312A (en) | 2012-10-18 | 2012-10-18 | Small take-off launch frame for unmanned aerial vehicle |
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| CN2012103971018A CN102923312A (en) | 2012-10-18 | 2012-10-18 | Small take-off launch frame for unmanned aerial vehicle |
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Cited By (16)
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| CN103112586A (en) * | 2013-02-26 | 2013-05-22 | 山东华宇职业技术学院 | Multi-mode power assisted levitation aerial detector |
| CN103224032A (en) * | 2013-05-15 | 2013-07-31 | 郝南楠 | Portable ejection mechanism for unmanned aerial vehicle |
| CN103466099A (en) * | 2013-09-22 | 2013-12-25 | 河南省寰宇测绘科技发展有限公司 | High-speed ejector rack of unmanned measuring plane |
| CN103496447A (en) * | 2013-09-29 | 2014-01-08 | 南京航空航天大学 | Mechanism and method for locking unmanned aerial vehicle of small unmanned aerial vehicle orbit shot system |
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN103963989A (en) * | 2014-05-29 | 2014-08-06 | 贵州帝三数字技术有限公司 | Portable foldable electromagnetic catapult of unmanned aerial vehicle |
| CN104015933A (en) * | 2014-06-11 | 2014-09-03 | 毕和军 | Folded launching and withdrawing device for unmanned aerial vehicle |
| CN104554814A (en) * | 2014-12-24 | 2015-04-29 | 南京航空航天大学 | Quickly and integrally folding type rubber band ejector |
| CN104608937A (en) * | 2015-02-03 | 2015-05-13 | 河南省汇隆精密设备制造有限公司 | Hydraulic pressure energy storage catapult of multi-plane type unmanned plane |
| CN107600447A (en) * | 2017-09-26 | 2018-01-19 | 甘肃省测绘工程院 | Air-mapping aircraft launching apparatus |
| CN107839843A (en) * | 2017-10-27 | 2018-03-27 | 深圳市云洲创新科技有限公司 | A kind of more piece bracket, ships and light boats and ships and light boats lay recovery method |
| CN107985623A (en) * | 2017-12-08 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of fixed wing aircraft launching apparatus |
| CN108082522A (en) * | 2017-12-19 | 2018-05-29 | 四川宝天智控系统有限公司 | Unmanned plane emitter and method |
| CN108190040A (en) * | 2017-12-20 | 2018-06-22 | 海鹰航空通用装备有限责任公司 | A kind of pneumatic launching cradle of universal small drone |
| CN108639369A (en) * | 2018-04-27 | 2018-10-12 | 宋忠春 | A kind of model plane JATO engine |
| CN111634437A (en) * | 2020-06-08 | 2020-09-08 | 海丰通航科技有限公司 | Connecting structure of unmanned aerial vehicle ejection system |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200960980Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Ejecting system applied to unmanned machine transmission system |
| CN101081638A (en) * | 2006-06-02 | 2007-12-05 | 珠海星宇模型实业有限公司 | Unmanned aerial plane launching system and method |
| CN101096224A (en) * | 2006-06-29 | 2008-01-02 | 珠海星宇模型实业有限公司 | Locking mechanism applied for unmanned aerial vehicle ejecting system and unmanned aerial vehicle locking method |
| CN201580561U (en) * | 2009-11-19 | 2010-09-15 | 刘华 | Carrier-based aircraft launching catapult |
| CN201729276U (en) * | 2010-06-30 | 2011-02-02 | 湖南山河科技股份有限公司 | Ejection system of small-sized unmanned aircraft |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN202130573U (en) * | 2011-01-27 | 2012-02-01 | 深圳市鸣鑫实业有限公司 | Light portable takeoff ejecting rack for small-sized individual soldier unmanned plane |
| CN102673797A (en) * | 2011-12-22 | 2012-09-19 | 河南科技大学 | Device employed to assist shipboard aircraft in takeoff |
-
2012
- 2012-10-18 CN CN2012103971018A patent/CN102923312A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200960980Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Ejecting system applied to unmanned machine transmission system |
| CN101081638A (en) * | 2006-06-02 | 2007-12-05 | 珠海星宇模型实业有限公司 | Unmanned aerial plane launching system and method |
| CN101096224A (en) * | 2006-06-29 | 2008-01-02 | 珠海星宇模型实业有限公司 | Locking mechanism applied for unmanned aerial vehicle ejecting system and unmanned aerial vehicle locking method |
| CN201580561U (en) * | 2009-11-19 | 2010-09-15 | 刘华 | Carrier-based aircraft launching catapult |
| CN201729276U (en) * | 2010-06-30 | 2011-02-02 | 湖南山河科技股份有限公司 | Ejection system of small-sized unmanned aircraft |
| CN202130573U (en) * | 2011-01-27 | 2012-02-01 | 深圳市鸣鑫实业有限公司 | Light portable takeoff ejecting rack for small-sized individual soldier unmanned plane |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN102673797A (en) * | 2011-12-22 | 2012-09-19 | 河南科技大学 | Device employed to assist shipboard aircraft in takeoff |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103112586A (en) * | 2013-02-26 | 2013-05-22 | 山东华宇职业技术学院 | Multi-mode power assisted levitation aerial detector |
| CN103112586B (en) * | 2013-02-26 | 2016-03-16 | 山东华宇职业技术学院 | The aerial reconnaissance device of various ways power-assisted lift-off |
| CN103224032A (en) * | 2013-05-15 | 2013-07-31 | 郝南楠 | Portable ejection mechanism for unmanned aerial vehicle |
| CN103224032B (en) * | 2013-05-15 | 2015-11-25 | 郝南楠 | A kind of Portable unmanned machine ejection mechanism |
| CN103466099A (en) * | 2013-09-22 | 2013-12-25 | 河南省寰宇测绘科技发展有限公司 | High-speed ejector rack of unmanned measuring plane |
| CN103466099B (en) * | 2013-09-22 | 2015-09-16 | 河南省寰宇测绘科技发展有限公司 | Unmanned measuring machine high speed ejection frame |
| CN103496447A (en) * | 2013-09-29 | 2014-01-08 | 南京航空航天大学 | Mechanism and method for locking unmanned aerial vehicle of small unmanned aerial vehicle orbit shot system |
| CN103496447B (en) * | 2013-09-29 | 2016-08-17 | 南京航空航天大学 | The unmanned plane locking mechanism of SUAV orbit shot system and method |
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN103803095B (en) * | 2014-03-03 | 2016-05-25 | 重庆翼动科技有限公司 | The Pneumatic catapult of SUAV |
| CN103963989A (en) * | 2014-05-29 | 2014-08-06 | 贵州帝三数字技术有限公司 | Portable foldable electromagnetic catapult of unmanned aerial vehicle |
| CN103963989B (en) * | 2014-05-29 | 2016-04-06 | 贵州帝三数字技术有限公司 | Portable folding type electromagnetic launch technology of unmanned aerial vehicle device |
| CN104015933B (en) * | 2014-06-11 | 2016-03-30 | 毕和军 | Collapsible unmanned aerial vehicle ejecting regenerative apparatus |
| CN104015933A (en) * | 2014-06-11 | 2014-09-03 | 毕和军 | Folded launching and withdrawing device for unmanned aerial vehicle |
| CN104554814A (en) * | 2014-12-24 | 2015-04-29 | 南京航空航天大学 | Quickly and integrally folding type rubber band ejector |
| CN104554814B (en) * | 2014-12-24 | 2016-08-24 | 南京航空航天大学 | Can quick Integral foldable rubber-band ejection device |
| CN104608937A (en) * | 2015-02-03 | 2015-05-13 | 河南省汇隆精密设备制造有限公司 | Hydraulic pressure energy storage catapult of multi-plane type unmanned plane |
| CN107600447A (en) * | 2017-09-26 | 2018-01-19 | 甘肃省测绘工程院 | Air-mapping aircraft launching apparatus |
| CN107839843A (en) * | 2017-10-27 | 2018-03-27 | 深圳市云洲创新科技有限公司 | A kind of more piece bracket, ships and light boats and ships and light boats lay recovery method |
| CN107985623A (en) * | 2017-12-08 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of fixed wing aircraft launching apparatus |
| CN108082522A (en) * | 2017-12-19 | 2018-05-29 | 四川宝天智控系统有限公司 | Unmanned plane emitter and method |
| CN108082522B (en) * | 2017-12-19 | 2021-03-30 | 四川宝天智控系统有限公司 | Unmanned aerial vehicle launching device and method |
| CN108190040A (en) * | 2017-12-20 | 2018-06-22 | 海鹰航空通用装备有限责任公司 | A kind of pneumatic launching cradle of universal small drone |
| CN108639369A (en) * | 2018-04-27 | 2018-10-12 | 宋忠春 | A kind of model plane JATO engine |
| CN111634437A (en) * | 2020-06-08 | 2020-09-08 | 海丰通航科技有限公司 | Connecting structure of unmanned aerial vehicle ejection system |
| CN111634437B (en) * | 2020-06-08 | 2022-01-11 | 海丰通航科技有限公司 | Connecting structure of unmanned aerial vehicle ejection system |
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Application publication date: 20130213 |