CN102530260A - Method and system for short-distance taking off of unmanned aerial vehicles - Google Patents
Method and system for short-distance taking off of unmanned aerial vehicles Download PDFInfo
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- CN102530260A CN102530260A CN201010597652XA CN201010597652A CN102530260A CN 102530260 A CN102530260 A CN 102530260A CN 201010597652X A CN201010597652X A CN 201010597652XA CN 201010597652 A CN201010597652 A CN 201010597652A CN 102530260 A CN102530260 A CN 102530260A
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- catapult car
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Abstract
The invention relates to a method and a system for short-distance taking off of unmanned aerial vehicles. The system comprises an ejection vehicle and a driving mechanism arranged on the ejection vehicle. The ejection vehicle comprises a loading plate, at least one support arranged on the loading plate and wheels at the bottom of the loading plate. The driving mechanism comprises at least one pulley block, a driving rope and a driving device, each pulley block comprises a rope, a fixed pulley, a spring and a pile, the springs are connected with the ropes through the fixed pulleys, and the piles are used for fixing the free ends of the springs and arranged outside the ejection vehicle. One end of the driving rope is fixed onto the ejection vehicle, and the other end of the driving rope is driven by the driving device to retract. The method and the system for short-distance taking off of unmanned aerial vehicles solve the technical problem that existing auxiliary equipment for short-distance taking off is huge, labor-consuming and material-consuming, and the system is simple in structure, convenient in operation and safe in implementation.
Description
Technical field
The present invention relates to a kind of unmanned plane auxiliary device that takes off, relate in particular to a kind of unmanned plane short takeoff method and system.
Background technology
The mode that aircraft short distance auxiliary takeoff apparatus adopts steam to launch more in the existing aeronautical technology; This appliance arrangement is huge, system complex, wasting manpower and material resources; Also has a kind of employing rocket booster mode; Aircraft need be born great acceleration/accel of moment, and common unmanned plane can receive wound and fuselage load.
Summary of the invention
Existing short takeoff accessory equipment is huge in order to solve, wasting manpower and material resources's technical matters, and the present invention provides a kind of convenient-to-running unmanned plane short takeoff method and system.
Technical solution of the present invention:
A kind of unmanned plane short takeoff method may further comprise the steps:
1] unmanned plane is placed on the catapult car,
Said catapult car comprises load plate, is arranged at least one wheel placing the support of unmanned plane and be arranged on the load plate bottom on the load plate;
2] in step 1] described in catapult car on installing drive mechanism,
Said driver train comprises at least one group of pulley assembly, drives rope and actuating device; Said pulley assembly comprise an end be fixed on rope on the catapult car, fixed pulley, through fixed pulley and rope bonded assembly spring and the free-ended stake that is arranged on the catapult car outside of fixing spring; Said driving rope one end is fixed on the catapult car, and the other end of said driving rope drives folding and unfolding through actuating device.
3] drive rope through actuating device to the take off reverse recovery of direction of unmanned plane, until springs;
4] unclamp the driving rope through actuating device.
Above-mentioned actuating device is a winch truck.
Above-mentioned catapult car is placed in orbit.
Above-mentioned catapult car is provided with three supports.
Above-mentioned pulley assembly is two and the symmetrical both sides that are arranged on catapult car.
A kind of unmanned plane short takeoff system, its special character is: comprises catapult car and is arranged on the driver train on the catapult car,
The wheel that said catapult car comprises load plate, is arranged at least one support on the load plate and is arranged on the load plate bottom;
Said driver train comprises at least one group of pulley assembly, drives rope and actuating device; Said pulley assembly comprises that an end is fixed on rope on the catapult car, fixed pulley, is arranged on the stake in the catapult car outside through fixed pulley and rope bonded assembly spring and fixing spring free end; Said driving rope one end is fixed on the catapult car, and the other end of said driving rope drives folding and unfolding through actuating device.
Above-mentioned actuating device is a winch truck.
Also comprise track, said catapult car is placed on track.
Above-mentioned catapult car is provided with three supports.
Above-mentioned pulley assembly is two and the symmetrical both sides that catapult car is set.
The advantage that the present invention had:
1, the present invention adopts the simple combination of elastomeric material and pulley assembly for solving unmanned plane short field take-off problem simple and easy actv. solution to be provided, and is very easy to realize industrialization production.
2, simple in structure, the handled easily of the present invention is implemented safety.
Description of drawings
Fig. 1 is the structural representation of unmanned plane short takeoff of the present invention system;
Fig. 2 is an embodiment of the invention structural representation;
Wherein Reference numeral is: 1-drives rope, 2-unmanned plane, 3-rope, 4-track, 5-fixed pulley, 6-spring, 7-post, 8-winch truck, 9-winch truck.
Specific embodiments
As shown in Figure 1, a kind of unmanned plane short takeoff method may further comprise the steps:
1] unmanned plane is placed on the catapult car,
Said catapult car comprises load plate, is arranged at least one wheel placing the support of unmanned plane and be arranged on the load plate bottom on the load plate;
2] in step 1] described in catapult car on installing drive mechanism,
Driver train comprises at least one group of pulley assembly, drives rope and actuating device; Pulley assembly comprises that an end is fixed on rope on the catapult car, fixed pulley, is arranged on the stake in the catapult car outside through fixed pulley and rope bonded assembly spring and fixing spring free end; Drive rope one end and be fixed on the catapult car, the other end that drives rope drives folding and unfolding through actuating device.
3] drive rope through actuating device to the take off reverse recovery of direction of unmanned plane, until springs;
4] unclamp the driving rope through actuating device.
Actuating device is a winch truck, and catapult car is placed in orbit, and catapult car is provided with three supports, and pulley assembly is two and the symmetrical both sides that are arranged on catapult car.
A kind of unmanned plane short takeoff system comprises catapult car and is arranged on the driver train on the catapult car,
The wheel that catapult car comprises load plate, is arranged at least one support on the load plate and is arranged on the load plate bottom; Said driver train comprises at least one group of pulley assembly, drives rope and actuating device; Pulley assembly comprises that an end is fixed on rope on the catapult car, fixed pulley, is arranged on the stake in the catapult car outside through fixed pulley and rope bonded assembly spring and fixing spring free end; Drive rope one end and be fixed on the catapult car, the other end of said driving rope drives folding and unfolding through actuating device.Actuating device is a winch truck.Also comprise track, catapult car is placed on track.Catapult car is provided with three supports.Pulley assembly is two and the symmetrical both sides that catapult car is set.
Embodiment: as shown in Figure 2, catapult car is placed in orbit, unmanned plane is placed on the support on the catapult car; Support can keep unmanned plane to stablize again can not had to hinder when unmanned plane takes off; Reclaim the driving rope through winch truck, the counter motion that the pulling catapult car takes off towards unmanned plane is until springs; Big in order to guarantee the unmanned plane power take-off, be preferably in to reclaim when driving rope springs is arrived the maximum tension degree.
In order to guarantee that catapult car is steady, unmanned plane power foot, the both sides that are preferably in the catapult car symmetry are provided with pulley assembly respectively.When arriving springs at utmost, unclamp to drive and stretch, utilize this moment the energy storage of extension spring to give the certain kinetic energy of catapult car, when catapult car advanced at utmost speed, the unmanned plane that is placed on the catapult car also just possessed kinetic energy, and unmanned plane is launched.
Claims (10)
1. unmanned plane short takeoff method may further comprise the steps:
1] unmanned plane is placed on the catapult car,
Said catapult car comprises load plate, is arranged at least one wheel placing the support of unmanned plane and be arranged on the load plate bottom on the load plate;
2] in step 1] described in catapult car on installing drive mechanism,
Said driver train comprises at least one group of pulley assembly, drives rope and actuating device; Said pulley assembly comprise an end be fixed on rope on the catapult car, fixed pulley, through fixed pulley and rope bonded assembly spring and the free-ended stake that is arranged on the catapult car outside of fixing spring; Said driving rope one end is fixed on the catapult car, and the other end of said driving rope drives folding and unfolding through actuating device.
3] drive rope through actuating device to the take off reverse recovery of direction of unmanned plane, until springs;
4] unclamp the driving rope through actuating device.
2. unmanned plane short takeoff method according to claim 1 is characterized in that: said actuating device is a winch truck.
3. unmanned plane short takeoff method according to claim 1 and 2 is characterized in that: said catapult car is placed in orbit.
4. unmanned plane short takeoff method according to claim 3 is characterized in that: said catapult car is provided with three supports.
5. unmanned plane short takeoff method according to claim 4 is characterized in that: said pulley assembly is two and the symmetrical both sides that are arranged on catapult car.
6. unmanned plane short takeoff system is characterized in that: comprises catapult car and is arranged on the driver train on the catapult car,
The wheel that said catapult car comprises load plate, is arranged at least one support on the load plate and is arranged on the load plate bottom;
Said driver train comprises at least one group of pulley assembly, drives rope and actuating device; Said pulley assembly comprises that an end is fixed on rope on the catapult car, fixed pulley, is arranged on the stake in the catapult car outside through fixed pulley and rope bonded assembly spring and fixing spring free end; Said driving rope one end is fixed on the catapult car, and the other end of said driving rope drives folding and unfolding through actuating device.
7. unmanned plane short takeoff according to claim 6 system, it is characterized in that: said actuating device is a winch truck.
8. according to claim 6 or 7 described unmanned plane short takeoff systems, it is characterized in that: also comprise track, said catapult car is placed on track.
9. unmanned plane short takeoff according to claim 8 system, it is characterized in that: said catapult car is provided with three supports.
10. unmanned plane short takeoff according to claim 9 system is characterized in that: said pulley assembly is the both sides that catapult car is set of two and symmetry.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010597652XA CN102530260A (en) | 2010-12-20 | 2010-12-20 | Method and system for short-distance taking off of unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010597652XA CN102530260A (en) | 2010-12-20 | 2010-12-20 | Method and system for short-distance taking off of unmanned aerial vehicles |
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| CN102530260A true CN102530260A (en) | 2012-07-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201010597652XA Pending CN102530260A (en) | 2010-12-20 | 2010-12-20 | Method and system for short-distance taking off of unmanned aerial vehicles |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640707A (en) * | 2013-12-06 | 2014-03-19 | 匡仲平 | Method for take-off of aircraft carrier-borne and army aviation fixed wing aircraft |
| CN104097785A (en) * | 2013-04-05 | 2014-10-15 | 何程 | Arrow string type shipboard aircraft ejector |
| CN106043730A (en) * | 2016-05-27 | 2016-10-26 | 匡仲平 | Aircraft carrier carrier-bearing and land-aviation fixed wing aircraft take-off method |
| CN111204470A (en) * | 2020-01-15 | 2020-05-29 | 哈尔滨工程大学 | Spring energy storage type ejection traction device |
Citations (5)
| 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 |
| CN201023660Y (en) * | 2006-12-22 | 2008-02-20 | 宣建民 | Ejector |
| CN101367438A (en) * | 2008-09-28 | 2009-02-18 | 沈阳锐翼科技有限公司 | Takeoff ejecting system of self-service flying platform |
| CN201380967Y (en) * | 2009-04-28 | 2010-01-13 | 中国农业科学院农业资源与农业区划研究所 | Takeoff ejector rack of small-sized pilotless aircraft |
| CN201415757Y (en) * | 2009-05-08 | 2010-03-03 | 陈伟民 | Self-supply power ejection device of aircraft carrier |
-
2010
- 2010-12-20 CN CN201010597652XA patent/CN102530260A/en active Pending
Patent Citations (5)
| 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 |
| CN201023660Y (en) * | 2006-12-22 | 2008-02-20 | 宣建民 | Ejector |
| CN101367438A (en) * | 2008-09-28 | 2009-02-18 | 沈阳锐翼科技有限公司 | Takeoff ejecting system of self-service flying platform |
| CN201380967Y (en) * | 2009-04-28 | 2010-01-13 | 中国农业科学院农业资源与农业区划研究所 | Takeoff ejector rack of small-sized pilotless aircraft |
| CN201415757Y (en) * | 2009-05-08 | 2010-03-03 | 陈伟民 | Self-supply power ejection device of aircraft carrier |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104097785A (en) * | 2013-04-05 | 2014-10-15 | 何程 | Arrow string type shipboard aircraft ejector |
| CN103640707A (en) * | 2013-12-06 | 2014-03-19 | 匡仲平 | Method for take-off of aircraft carrier-borne and army aviation fixed wing aircraft |
| CN106043730A (en) * | 2016-05-27 | 2016-10-26 | 匡仲平 | Aircraft carrier carrier-bearing and land-aviation fixed wing aircraft take-off method |
| CN111204470A (en) * | 2020-01-15 | 2020-05-29 | 哈尔滨工程大学 | Spring energy storage type ejection traction device |
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Application publication date: 20120704 |