CN107352041A - Unmanned plane Pneumatic catapult - Google Patents
Unmanned plane Pneumatic catapult Download PDFInfo
- Publication number
- CN107352041A CN107352041A CN201710722345.1A CN201710722345A CN107352041A CN 107352041 A CN107352041 A CN 107352041A CN 201710722345 A CN201710722345 A CN 201710722345A CN 107352041 A CN107352041 A CN 107352041A
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- CN
- China
- Prior art keywords
- unmanned plane
- base
- transmitting tube
- rear end
- transmitting
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/10—Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manipulator (AREA)
Abstract
The invention discloses a kind of unmanned plane Pneumatic catapult, including base, launching trolley, transmitting tube, air accumulator, the transmitting tube rear end is connected by magnetic valve with air accumulator, the transmitting tube front end is connected by piston rod with launching trolley, the transmitting tube front end is provided with retaining mechanism, and rear end is provided with pressure sensor；Base rear end is provided with controller, and affiliated controller is connected with pressure sensor, retaining mechanism, magnetic valve；The launching trolley is arranged in the chute on base by pulley；The base upper surface front end is provided with buffer unit；The pan frontward end is higher than rear end, and pan frontward end is provided with the tripod with elevating lever.The launch angle of unmanned plane is adjusted by tripod, control system controls air accumulator to inflate transmitting tube, and launching trolley advances along base during transmitting drives unmanned plane transmitting, and launching trolley is stopped lower and makes its stopping by buffer unit.The present invention improves the safety and reliability of transmitting.
Description
Technical field
The present invention relates to a kind of emitter, more particularly to a kind of Pneumatic catapult of unmanned plane.
Background technology
Achievement of the unmanned plane as modernization scientific and technological progress, have mobility height, use cost low, safeguard using simple etc.
Advantage, thus unmanned plane take photo by plane, agricultural, plant protection, express transportation, observation wild animal, mapping, the field such as the disaster relief suffer from extensively
General application, and play an important role.And unmanned plane is under many circumstances, it can not realize and independently take off, it is therefore necessary to
There are extra device or technology to help unmanned plane to take off, the mode of taking off of unmanned plane mainly has takeoff, taken off vertically at present
With catapult-assisted take-off etc.；Take off higher to site requirements, this mode is difficult in the wild；Take off vertically and require unmanned plane
The engine that must have strength produces enough lift, and most of unmanned vehicle engine power can not meet；Catapult-assisted take-off phase
Relatively low is required to the engine power of unmanned plane for, the requirement to environment is also very low, therefore to be risen using more universal
The mode of flying.
At present, launching the catapult-launching gear of unmanned plane mainly includes rubber band launching cradle, spring launching cradle.Rubber band launching cradle quality
Greatly, the space of occupancy is larger, and it is inconvenient to carry, and launch power and power adjustment scope are all smaller, and the scope of application is small；Bullet
Spring launching cradle there is also it is above-mentioned the problem of, and many launching cradles are also present some other the problem of at present, such as the angle of departure
Spend it is single cause launching success rate is low, security it is relatively low easily cause accidental injury, release reliability is low, portability is low etc..
The content of the invention
In order to solve the problems of prior art, the present invention provides a kind of unmanned plane Pneumatic catapult, the device
Have the advantages that security is higher, launcher reliability is strong, it is simple in construction, be easy to carry.
The technical solution adopted for the present invention to solve the technical problems is：Unmanned plane Pneumatic catapult, including base, hair
Dolly, transmitting tube, air accumulator are penetrated, the transmitting tube rear end is connected by magnetic valve with air accumulator, and the transmitting tube front end passes through
Piston rod is connected with launching trolley, and the transmitting tube front end is provided with retaining mechanism, and rear end is provided with pressure sensor；After base
End is provided with controller, and affiliated controller is connected with pressure sensor, retaining mechanism, magnetic valve and (is not drawn into figure)；The hair
Dolly is penetrated to be arranged in the chute on base by pulley；The base upper surface front end is provided with buffer unit；The base
Front end is higher than rear end.
Further, the pan frontward end is connected with tripod, and rear end is fixed by fixed ground nail with ground.
Further, elevating lever is provided with the tripod, elevating lever is connected through a screw thread control lifting with tripod
The position of bar.
Further, the chute has certain intervals and parallel to each other.
Further, when transmitting tube internal pressure reaches setting value, controller control retaining mechanism is controlled while release
Closed electromagnetic valve processed.
Further, the air accumulator is connected by the fixation ground nail of its bottom with ground.
The beneficial effects of the invention are as follows：The present invention is by setting base, launching trolley and buffer unit, by transmitting tube
Energy is delivered on launching trolley by the piston rod on launching trolley and is converted to mechanical energy, makes the launching trolley with unmanned plane
Moved along slide rail, unmanned plane is launched when reaching base top, and shot trolley is slowed down and stopped by buffer unit, entirely
Process is fool proof, avoids the devices such as piston rod and is transmitted into ground with unmanned plane and causes potential safety hazard.At the same time, by setting
The tripod elevating lever put realizes the angle of inclination on base and ground, you can adjusts the direction of transmitting；Sensor, control are set
The devices such as device, magnetic valve can more precise control emission process, launching trolley is along the chute row on base in emission process
Enter, it is possible to increase the reliability of transmitting, improve launching success rate.
Whole unmanned plane Pneumatic catapult ensure that the safety of transmitting while unmanned plane launcher reliability is improved
Property.
Brief description of the drawings
Fig. 1 is the front view of unmanned plane Pneumatic catapult；
Fig. 2 is the top view of unmanned plane Pneumatic catapult；
Shown in figure：1- bases, 2- launching trolleys, 3- piston rods, 4- transmitting tubes, 5- air accumulators, 6- magnetic valves, 7- pressure
Sensor, 8- retaining mechanisms, 9- controllers, 10- chutes, 11- buffer units, 12- tripods, 13- elevating levers, 14- are regularly
Nail, 15- pulleys.
Embodiment
The present invention is further described with reference to the accompanying drawings and examples.
As shown in figure 1, unmanned plane Pneumatic catapult, including base 1, launching trolley 2, transmitting tube 4, air accumulator 5, it is described
The rear end of transmitting tube 4 is connected by magnetic valve 6 with air accumulator 5, and the front end of transmitting tube 4 passes through piston rod 3 and the phase of launching trolley 2
Even, the front end of transmitting tube 4 is provided with retaining mechanism 8, and rear end is provided with pressure sensor 7；Base rear end is provided with controller
9, affiliated controller 9 is connected with pressure sensor 7, retaining mechanism 8, magnetic valve 6 and (is not drawn into figure)；The launching trolley 2 is logical
Pulley 15 is crossed in the chute 10 on base 1；The upper surface front end of base 1 is provided with buffer unit 11；The base 1
Front end is higher than rear end.
In use, first inserting the piston rod 3 of the afterbody of launching trolley 2 in transmitting tube 4, and locked with retaining mechanism 8, it is living
Stopper rod 3 is made of one with launching trolley 2, makes structure simpler, sets retaining mechanism 8 to avoid transmitting tube 4 in inflation
Piston rod 3 is released, is advantageous to form sufficiently strong pressure in transmitting tube 4, in order to launch.Adjust the lifting on tripod 12
Bar 13, base 1 is formed an optimal launch angle with level ground, be then turned on controller 9, controller 9 controls electromagnetism
Valve 6 allows air accumulator 5 to be inflated transmitting tube 4, and pressure sensor 7 monitors the pressure value in transmitting tube 4 in real time, is set when reaching
Optimum value when, controller 9 controls retaining mechanism 8 to unclamp piston rod 3, while controls magnetic valve 6 to close, and stops to transmitting tube 4
Inflate, the pressure in transmitting tube 4 is delivered to launching trolley 2 by piston rod 3, makes launching trolley 2 along the chute 10 on base 1
Rapidly advance, the unmanned plane on launching trolley 2 just launches.Transmitting tube 4 can be allowed by setting sensor 7 and controller 9
Interior pressure is advantageous to improve the launching success rate of unmanned plane close to optimal pressure value and optimal release opportunity.Hair
When penetrating dolly 2 and advancing to 1 front end of base, hit the buffer unit 11 in the front end of base 1 and realize and slow down and finally stop, launching trolley
2 with the structural relation of base 1 and the setting of buffer unit 11, launching trolley 2 can be avoided to go out base in emission process
1, potential safety hazard is caused, improves the security of whole device.
In order to realize that the front end of base 1 is higher than rear end, various means and method can be used, is such as individually positioned in front and back end
Rugged ground, it is preferable that the present apparatus is connected with tripod 12 in the front end of base 1, and rear end passes through fixed ground nail and ground
It is fixed.
Unmanned plane can be launched in transmitting by different launch angles, but the structure setting of each unmanned plane
Can all there is an optimal launch angle after fixed, in order to reach an optimal launch angle in transmitting, it is preferable that
Elevating lever 13 is provided with tripod 12, elevating lever 13 is connected through a screw thread the position of control elevating lever 13 with tripod 12, this
Sample to adjust the angle of base 1 and level ground by adjusting the position of elevating lever 13, can improve the transmitting of unmanned plane into
Power.
Launching trolley 2 and base 1 can use a variety of fit systems, and installation guide rod realizes movement such as on base 1, preferably
Ground, the present apparatus are coordinated using chute 10 with pulley 15, can realize the position for sliding and can limitation launching trolley 2, and chute 10
With certain intervals and parallel to each other, to realize and coordinate with the pulley 15 on launching trolley 2, it is necessary to have certain intervals, mutually
It is parallel, it ensure that transmitting is small, 2 move ahead in one direction.
When the internal pressure of transmitting tube 4 reaches setting value, controller 9 controls electromagnetism while controlling retaining mechanism 8 to unclamp
Valve 6 is closed, and can so avoid continuing when carrying out unmanned plane transmitting 4 inflation into transmitting tube, while realize in optimal hair
The opportunity of penetrating is launched.
Air accumulator 5 can be placed on the afterbody of base 1 and can also be disposed close on the ground of the afterbody of base 1, it is preferable that storage
Gas tank 5 is connected by the fixation ground nail 14 of its bottom with ground, and fixed ground nail 14 is simple in construction, easy to operate.
Claims (6)
1. unmanned plane Pneumatic catapult, including base (1), launching trolley (2), transmitting tube (4), air accumulator (5), its feature exist
In：Transmitting tube (4) rear end is connected by magnetic valve (6) with air accumulator (5), and transmitting tube (4) front end passes through piston rod
(3) it is connected with launching trolley (2), transmitting tube (4) front end is provided with retaining mechanism (8), and rear end is provided with pressure sensor
(7)；Base (1) rear end is provided with controller (9), affiliated controller (9) and pressure sensor (7), retaining mechanism (8), electromagnetism
Valve (6) is connected；The launching trolley (2) is arranged in the chute (10) on base (1) by pulley (15)；The base (1)
Upper surface front end is provided with buffer unit (11)；Base (1) front end is higher than rear end.
2. unmanned plane Pneumatic catapult as claimed in claim 1, it is characterised in that：Base (1) front end is connected with three
Foot stool (12), rear end are fixed by fixed ground nail with ground.
3. unmanned plane Pneumatic catapult as claimed in claim 2, it is characterised in that：Liter is provided with the tripod (12)
Bar (13) drops, and elevating lever (13) is connected through a screw thread the position of control elevating lever (13) with tripod (12).
4. unmanned plane Pneumatic catapult as claimed in claim 1, it is characterised in that：The chute (10) has certain intervals
It is and parallel to each other.
5. unmanned plane Pneumatic catapult as claimed in claim 1, it is characterised in that：When transmitting tube (4), internal pressure reaches
During setting value, magnetic valve (6) is controlled to close while controller (9) control retaining mechanism (8) unclamps.
6. unmanned plane Pneumatic catapult as claimed in claim 1, it is characterised in that：The air accumulator (5) passes through its bottom
Fixation ground nail (14) be connected with ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710722345.1A CN107352041A (en) | 2017-08-22 | 2017-08-22 | Unmanned plane Pneumatic catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710722345.1A CN107352041A (en) | 2017-08-22 | 2017-08-22 | Unmanned plane Pneumatic catapult |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107352041A true CN107352041A (en) | 2017-11-17 |
Family
ID=60288943
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710722345.1A Withdrawn CN107352041A (en) | 2017-08-22 | 2017-08-22 | Unmanned plane Pneumatic catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107352041A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107856877A (en) * | 2017-12-15 | 2018-03-30 | 四川汉科计算机信息技术有限公司 | The transmitting of SUAV, recovery system |
| CN108454874A (en) * | 2018-05-30 | 2018-08-28 | 深圳市易飞方达科技有限公司 | Unmanned plane emitter |
| CN108482701A (en) * | 2018-05-21 | 2018-09-04 | 重庆大学 | A kind of unmanned aerial vehicle ejecting system based on pneumatic muscle |
| CN109398741A (en) * | 2018-12-12 | 2019-03-01 | 威海广泰空港设备股份有限公司 | Trailer-type unmanned plane emitter |
| CN110667873A (en) * | 2019-11-05 | 2020-01-10 | 贵州华图科技有限公司 | Unmanned aerial vehicle and method for catapulting unmanned aerial vehicle by utilizing compressed air |
| CN113815882A (en) * | 2021-11-22 | 2021-12-21 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
-
2017
- 2017-08-22 CN CN201710722345.1A patent/CN107352041A/en not_active Withdrawn
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107856877A (en) * | 2017-12-15 | 2018-03-30 | 四川汉科计算机信息技术有限公司 | The transmitting of SUAV, recovery system |
| CN107856877B (en) * | 2017-12-15 | 2023-09-05 | 四川汉科计算机信息技术有限公司 | Small unmanned aerial vehicle's transmission, recovery system |
| CN108482701A (en) * | 2018-05-21 | 2018-09-04 | 重庆大学 | A kind of unmanned aerial vehicle ejecting system based on pneumatic muscle |
| CN108454874A (en) * | 2018-05-30 | 2018-08-28 | 深圳市易飞方达科技有限公司 | Unmanned plane emitter |
| CN108454874B (en) * | 2018-05-30 | 2023-08-29 | 深圳市华讯方舟系统技术有限公司 | Unmanned aerial vehicle emitter |
| CN109398741A (en) * | 2018-12-12 | 2019-03-01 | 威海广泰空港设备股份有限公司 | Trailer-type unmanned plane emitter |
| CN109398741B (en) * | 2018-12-12 | 2024-03-19 | 威海广泰空港设备股份有限公司 | Trailer type unmanned aerial vehicle launching device |
| CN110667873A (en) * | 2019-11-05 | 2020-01-10 | 贵州华图科技有限公司 | Unmanned aerial vehicle and method for catapulting unmanned aerial vehicle by utilizing compressed air |
| CN113815882A (en) * | 2021-11-22 | 2021-12-21 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
| CN113815882B (en) * | 2021-11-22 | 2022-03-29 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20171117 |
|
| WW01 | Invention patent application withdrawn after publication |