CN203832760U - Catapulting system for small size unmanned aerial vehicle - Google Patents
Catapulting system for small size unmanned aerial vehicle Download PDFInfo
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- CN203832760U CN203832760U CN201420205260.8U CN201420205260U CN203832760U CN 203832760 U CN203832760 U CN 203832760U CN 201420205260 U CN201420205260 U CN 201420205260U CN 203832760 U CN203832760 U CN 203832760U
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- guide rail
- dolly
- aerial vehicle
- unmanned aerial
- launch
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Abstract
The utility model relates to a portable catapulting system for an unmanned aerial vehicle. The portable catapulting system for the unmanned aerial vehicle is convenient to demount and mount, simple in operation, efficient in working, light in system mass, convenient to transport and low in using cost. A guide rail (6) is supported by a plurality of supporting legs (2), a buffering seat (4) is arranged at the front end of the guide rail (6), a launching wrench (8) is arranged at the rear end of the guide rail (6), a catapulting trolley (7) is mounted on the guide rail (6) in a sliding mode, and the catapulting trolley (7) and the guide rail (6) are limited and controlled through a lock pin (9) and a safety plug (10). Flying rings (3) are arranged at the front end of the catapulting trolley (7) and the front end of the guide rail (6), one end of a rubber band set (11) is connected with the flying ring (3) at the front end of the guide rail (6), and the other end of the rubber band set (11) is connected with the flying ring (3) of the catapulting trolley (7). The supporting legs (2) are connected with the guide rail (6) through bolts and are limited through the buffering seat (4).
Description
Technical field
The present invention relates to the Portable catapult system of a kind of ejection system, particularly unmanned aerial vehicle.
Background technology
Unmanned aerial vehicle, from that time of its birth, is just constantly used in dual-use field.Because unmanned plane has advantages of a lot, as better manoevreability, better aerodynamic force, lighter quality and cost still less, in conjunction with the fast development of remote sensing, camera work, unmanned aerial vehicle has been widely used in the military domain such as the civil areas such as land resources, digital city, rescue and relief work and anti-ballistic, early warning, strategy investigation and monitoring.Although unmanned aerial vehicle has the multiple mode of taking off, as ground roll-out, take off, rise driving rolling start, hand-thrown and take off, catapult-assisted take-off etc., but in many special places, particularly when take-off venue limited space, the runway that there is no open smooth and sufficient length or highway, rolling start mode cannot realize, and hand-thrown takes off and can only be adapted to the miniature pilotless plane of very light weight, for the unmanned aerial vehicle that carries special equipment, be also inapplicable.Catapult-assisted take-off mode has well made up the shortcoming of the aforementioned mode of taking off, and has the plurality of advantages such as take off distance is short, site condition requirement is low, strong adaptability.
Utility model content
The technical problem to be solved in the present invention is to provide the Portable catapult system that a kind of easy accessibility, simple to operate, efficient work, mass of system are light, be convenient to transportation and the low unmanned aerial vehicle of use cost.
In order to solve the problems of the technologies described above, the Portable catapult system of unmanned aerial vehicle provided by the invention, there are four supporting leg supporting guides, at described guide rail front end, be provided with buffing pad, on described guide rail, be slidably fitted with and launch dolly, at the described apparatus for placing that unmanned aerial vehicle is installed on dolly that launches, in described guide rail rear end, be provided with the feedway that launches dolly described in acting on.
Described guide rail is comprised of two or many square aluminum pipes, and one end of described square aluminum pipe is inner installs two little square aluminum pipes, and two described little square aluminum pipes can insert last joint square aluminum pipe inside and position.The square aluminum pipe of described composition guide rail is locked by snap close.
Described feedway is in described guide rail rear end, to be provided with lock pin and the transmitting spanner that hooks described launching trolley.Between described guide rail and described launching trolley, be provided with safe keyhole.
Described bungee group is connected with guide rail with suspension ring by latch hook.
Described supporting leg is comprised of small-sized square tube.Between described square tube and described guide rail by bolt be connected, fastening.The support angle of described square tube is undertaken spacing by the buffing pad being arranged on described guide rail.
The described dolly that launches is placed on described guide rail by four bolts pulsation-frees.Two nuts are installed on described every bolts in the middle again, and two described bearings are clamped the rib of the side of described guide rail, guarantee that the described dolly pulsation-free on described guide rail that launches slides.The described holding plane that unmanned aerial vehicle is installed on dolly that launches, described holding plane consists of sheet metal, described plane is connected by screw fastening by crooked Metallic rod with the described dolly that launches, and the rear end metal sheet of described holding plane is bent to can clamp unmanned aerial vehicle.The described dolly that launches is connected with the latch hook being connected in described bungee group by being arranged on the described suspension ring that launch dolly both sides with described bungee group.
Adopt the Portable catapult system of the unmanned aerial vehicle of technique scheme, utilize the elastic force of India rubber tube of bungee group as power, bungee group discharges launches after dolly, launches dolly mother aircraft and runs along guide rail is sliding, makes aircraft reach takeoff speed.Bungee group by latch hook and guide rail with launch dolly and be connected, connection mode is simple, reliable.Guide rail rear end is provided with the double insurance of lock pin and safe keyhole, guarantees to launch safety.
Advantage of the present utility model: 1) guide rail of the present invention adopts snap close locking to connect by two joints or more piece square aluminum pipe, and dismounting is convenient rapidly, transports light; 2) bungee directly with latch hook with guide rail, launch dolly and be connected, mode is simple, reliable; 3) launch the double insurance that dolly adopts lock pin and safe keyhole, use safety; 4) only to need to step on transmitting spanner be ejectable unmanned aerial vehicle in the present invention, without electric device, thereby reduces noise, energy-conserving and environment-protective, better economy.
In sum, the present invention is the Portable catapult system that a kind of easy accessibility, simple to operate, efficient work, mass of system are light, be convenient to transportation and the low unmanned aerial vehicle of use cost.
Accompanying drawing explanation
Fig. 1 is unmanned aircraft ejection system composition diagram of the present invention;
Fig. 2 is left view of the present invention;
Fig. 3 is the structural representation that launches dolly;
Fig. 4 is guide rail connection diagram.
The specific embodiment
Referring to Fig. 1 and Fig. 2, many supporting legs (2) are supported with guide rail (6), front end at guide rail (6) has buffing pad (4), in the rear end of guide rail (6), be provided with transmitting spanner (8), on guide rail (6), be slidably fitted with and launch dolly (7), launch between dolly (7) and guide rail (6) with lock pin (9) and safety cock (10) is spacing and control.Launching dolly (7) and guide rail (6) front end is provided with suspension ring (3), bungee group (11) one end is connected with the suspension ring (3) of guide rail (6) front end, and the other end is connected with the suspension ring (3) that launch dolly (7).Between supporting leg (2) and guide rail (6), with bolt, be connected, and have buffing pad (4) to carry out spacing.
Referring to Fig. 3, launch dolly (7) and be arranged on reposefully on guide rail (6) by steel plate (19), four bolts (16) and two intermediate plates (17).The middle part of every bolts (16) is provided with the rib that two bearings (16) are clamped guide rail (6) both sides, makes to launch dolly (7) reposefully at the upper sliding and running of guide rail (6).Two suspension ring (3) are installed, in order to the connection with bungee group (11) on steel plate (19).Support (20) is connected with screw with steel plate (19), holding plane (21) is installed on support (20), the rear end of holding plane (21) is bent to clamps unmanned aerial vehicle, it is not slided backward, and when launching dolly (7) high-speed slide to the buffing pad (4) of guide rail (6) front end, unmanned aerial vehicle has certain speed and flies away from automatically and launch dolly (7).
Referring to Fig. 4, according to the needs of ejection speed, guide rail (6) is by two or how with square aluminum pipe (12), docking forms.In square aluminum pipe (12), be installed with two small-sized square aluminum pipes (14), during installation, two small-sized square aluminum pipes (14) are just in time inserted in last square aluminum pipe (12), and the guide rail (6) that square aluminum pipe (12) forms like this guarantees in a plane and guarantees being smoothly connected of guide rail (6).Latch hook (11) and the lock ring (13) of two snap closes (5) are installed respectively on the two square aluminum pipes (12) that connect, and lockable square aluminum pipe (12) guarantees to connect fastening reliable.
Unmanned aerial vehicle is placed on holding plane (19).During cataplane, extract safety cock (10), the lower transmitting spanner (8) that tramps with one's feet, bungee group (11) traction is launched dolly (7) in the upper slip of guide rail (6).Launch dolly (7) quick sliding to buffing pad (4) and collision buffering seat (4), launch the rapid braking of dolly (7) to stopping.And unmanned aerial vehicle relies on and to launch the power that speed that dolly (7) provides and driving engine provide, fly away from holding plane (19), thereby realize taking off without runway of unmanned aerial vehicle.
Claims (8)
1. the portable ejection system of a unmanned aerial vehicle, it is characterized in that: many supporting legs (2) are supported with guide rail (6), front end at guide rail (6) has buffing pad (4), in the rear end of guide rail (6), be provided with transmitting spanner (8), on guide rail (6), be slidably fitted with and launch dolly (7), launch between dolly (7) and guide rail (6) with lock pin (9) and safety cock (10) is spacing and control, launching dolly (7) and guide rail (6) front end is provided with suspension ring (3), bungee group (11) one end is connected with the suspension ring (3) of guide rail (6) front end, the other end is connected with the suspension ring (3) that launch dolly (7), between supporting leg (2) and guide rail (6), with bolt, be connected, and there is buffing pad (4) to carry out spacing, during cataplane, extract safety cock (10), lower transmitting spanner (8) tramps with one's feet, bungee group (11) traction is launched dolly (7) in the upper slip of guide rail (6), launch dolly (7) quick sliding to buffing pad (4) and collision buffering seat (4), rapidly braking is to stopping to launch dolly (7), and unmanned aerial vehicle relies on and launches speed and the power that dolly (7) and bungee group (11) provide, fly away from holding plane (19), thereby realize taking off without runway of unmanned aerial vehicle.
2. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, it is characterized in that: guide rail (6) is comprised of two or many square aluminum pipes (12), two little square aluminum pipes (12) of the inner installation in one end of described square aluminum pipe (12), two described little square aluminum pipes (12) can insert last joint square aluminum pipe (12) inside and position, and the square aluminum pipe (12) of described composition guide rail (6) is locked by snap close (15).
3. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, it is characterized in that: feedway is in described guide rail (6) rear end, to be provided with to hook the described lock pin that launches dolly (7) (9) and launch spanner (8), described guide rail (6) and described in launch and between dolly (7), be provided with safety cock (10) hole.
4. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, is characterized in that: bungee group (11) is connected with guide rail (6) with suspension ring (3) by latch hook.
5. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, it is characterized in that: supporting leg (2) is comprised of small-sized square tube (2), between described square tube (2) and described guide rail (6) by bolt (4) be connected, fastening, the support angle of described square tube (2) is undertaken spacing by the buffing pad (4) being arranged on described guide rail (6).
6. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, it is characterized in that: launch dolly (7) and be placed on described guide rail (6) by four bolts (16) pulsation-free, on described every bolts (16), two nuts are installed in the middle again, described two bearings (16) are clamped the rib of the side of described guide rail (6), guarantee that the described dolly (7) that launches slides at the upper pulsation-free of described guide rail (6).
7. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, it is characterized in that: launch the holding plane (21) that unmanned aerial vehicle is installed on dolly (7), described holding plane (21) consists of sheet metal, described plane (21) is connected by screw fastening by crooked Metallic rod with the described dolly (7) that launches, and the rear end metal sheet of described holding plane (21) is bent to can clamp unmanned aerial vehicle.
8. the portable ejection system of a kind of unmanned aerial vehicle according to claim 1, is characterized in that: launch dolly (7) and be connected with the latch hook being connected in described bungee group (11) by being arranged on the described suspension ring (3) that launch dolly (7) both sides with described bungee group (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420205260.8U CN203832760U (en) | 2014-04-25 | 2014-04-25 | Catapulting system for small size unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420205260.8U CN203832760U (en) | 2014-04-25 | 2014-04-25 | Catapulting system for small size unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN203832760U true CN203832760U (en) | 2014-09-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420205260.8U Expired - Fee Related CN203832760U (en) | 2014-04-25 | 2014-04-25 | Catapulting system for small size unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428624A (en) * | 2016-08-30 | 2017-02-22 | 陕西千山航空电子有限责任公司 | Dynamic jettisoning and separation test method |
| CN107640330A (en) * | 2017-09-15 | 2018-01-30 | 中国科学院长春光学精密机械与物理研究所 | A kind of unmanned aerial vehicle ejecting device |
-
2014
- 2014-04-25 CN CN201420205260.8U patent/CN203832760U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428624A (en) * | 2016-08-30 | 2017-02-22 | 陕西千山航空电子有限责任公司 | Dynamic jettisoning and separation test method |
| CN107640330A (en) * | 2017-09-15 | 2018-01-30 | 中国科学院长春光学精密机械与物理研究所 | A kind of unmanned aerial vehicle ejecting device |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 100176 room 505, 1 building, 36 Chuang four street, Beijing economic and Technological Development Zone, Beijing. Patentee after: Beijing Zhong Chi Chi Hui Technology Co., Ltd. Address before: 100078 Beijing Fengtai District Fangzhuang Fang Qun garden four phase Jincheng center 403 room Patentee before: Beijing Zhong Liangance Science and Technology Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140917 Termination date: 20190425 |