CN106428604A - Launching frame and system for launching unmanned aerial vehicle - Google Patents
Launching frame and system for launching unmanned aerial vehicle Download PDFInfo
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- CN106428604A CN106428604A CN201611032477.3A CN201611032477A CN106428604A CN 106428604 A CN106428604 A CN 106428604A CN 201611032477 A CN201611032477 A CN 201611032477A CN 106428604 A CN106428604 A CN 106428604A
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- launching
- launching cradle
- unmanned plane
- frame
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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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
Abstract
The invention relates to a launching frame and system for launching an unmanned aerial vehicle. The launching frame comprises a launching frame body, a skate frame, a launching rope and a driving device. The skate frame is arranged on the launching frame body and used for bearing and launching the unmanned aerial vehicle. The launching rope is arranged at the launching end of the launching frame body. The skate frame is arranged at the initial end of the launching body and can slide in the extending direction of the launching frame body. A driving device is connected with the skate frame and used for driving the skate frame to move in the extending direction of the launching frame body so that the skate frame can collide with the launching rope to launch the unmanned aerial vehicle. When the unmanned aerial vehicle is launched, the driving device is used for driving the skate frame to linearly move on the launching frame body, and motion of the skate frame does not need to be powered by stretching deformation of an elastic string, so that the launching frame is small in overall size, easy to operate and capable of improving the launching efficiency of the unmanned aerial vehicle.
Description
Technical field
The present invention relates to unmanned plane lift-off technology field, more particularly, to a kind of launching cradle for unmanned plane transmitting and ejection
System.
Background technology
The launching cradle of existing SUAV, using stretch cord as energy-accumulating medium, aluminium alloy does launching cradle to great majority,
Under the tensile-elasticity of stretch cord acts on, sliding frame and the unmanned plane thereon of running moves to the transmitting terminal of launching cradle, when the sliding frame that runs touches
When touching the sliding ejection rope running the setting of frame transmitting terminal, the sliding frame that runs stops because of resistance continuing to move to, the sliding unmanned plane moment run on frame
Gone out by ejection, complete to launch.
There is problems with this kind of stretch cord launching cradle：First, because stretch cord energy storage is a kind of energy storage of stretching degeneration
Form, long-time use can lead to stretch cord aging, affects elasticity and compactedness.The usability to stretch cord for the temperature environment simultaneously
Can impact be also very big, when ambient temperature is low, stretch cord is more crisp, and when temperature is too high, elastic force has declined again；Second, due to bullet
Power rope can be wound around several circles locked joint on launching cradle, so can go to change elastic force when different ejection weight demands
The winding number of turns of rope or the total length of stretch cord, this process is just relatively cumbersome and needs professional and technical personnel to operate；
So the range relative narrower of same a stretch cord launching cradle on the market；3rd, this stretch cord launching cradle is due to bullet
Penetrate the principle of principle and structure, generally all relatively bigger than normal, lay particular stress on, and open and folding is required for arranging stretch cord, operation element
Relatively cumbersome.
Content of the invention
For overcoming the above-mentioned technical problem of prior art presence, the invention provides a kind of ejection for unmanned plane transmitting
Frame, it drives the sliding frame that runs to move on launching cradle using driving means, complete the transmitting of unmanned plane, it is to avoid described above making
The problem being led to stretch cord.
The technical scheme that the present invention solves above-mentioned technical problem is as follows：A kind of launching cradle for unmanned plane transmitting, its bag
Include launching cradle body, sliding race frame, ejection rope and driving means；Described sliding race erection is placed on described launching cradle body, is used for holding
Carry and launch unmanned plane；
Described ejection rope is arranged on the transmitting terminal of described launching cradle body, and described sliding race erection is placed in described launching cradle body
Initial end, and can along described launching cradle body bearing of trend slide；
Described driving means are connected with the described sliding frame that runs, for driving the described sliding frame that runs along the extension of described launching cradle body
Direction is moved, so that the described sliding frame that runs collides described ejection rope and launches described unmanned plane.
On the basis of technique scheme, the present invention can also do following improvement.
Further, described driving means include cylinder body, the First piston bar being arranged in described cylinder body
And first piston；The first end of described First piston bar is fixed on described first piston, and the second end is to described cylinder body
Axial direction extend；
Described cylinder body is arranged on described launching cradle body, the extension of its axial direction and described launching cradle body
Direction is consistent, and the second end of described First piston bar is connected with the described sliding frame that runs；
When launching described unmanned plane, in described cylinder body, it is passed through hydraulic oil, described First piston bar is described
Its bearing of trend of drive lower edge of one piston moves, to drive the described sliding frame that runs to move to the transmitting terminal of described launching cradle body.
Beneficial effect using above-mentioned further scheme is：With hydraulic-driven principle, promote to slide under the drive of piston
Run frame to move on launching cradle, when sliding run frame and touch ejection rope when, the unmanned plane on frame will be run launch positioned at sliding.
Further, described driving means include cylinder body, the second piston bar being arranged in described cylinder body and
Two pistons；The first end of described second piston bar is fixed in described second piston, and the second end is to the axial direction of described cylinder body
Direction extends；
Described cylinder body is arranged on described launching cradle body, the extension side of its axial direction and described launching cradle body
To consistent, the second end of described second piston bar is connected with the described sliding frame that runs；
When launching described unmanned plane, in described cylinder body, it is passed through compressed air, described second piston bar is described
Its bearing of trend of drive lower edge of two pistons moves, to drive the described sliding frame that runs to move to the transmitting terminal of described launching cradle body.
Beneficial effect using above-mentioned further scheme is：By being passed through compressed air in cylinder, piston is driven to move,
Drive the motion of piston rod, thus driving launching cradle to move on frame in sliding race, when launching cradle touches ejection rope, launching cradle stops
Mobile, the unmanned plane on launching cradle is then because inertia is launched away.
Further, described launching cradle body includes the first main paragraph and the second main paragraph, described first main paragraph with described
Second main paragraph is hinged so that described first main paragraph is folded to the position parallel with described second main paragraph or makes described
First main paragraph is expanded to and is on same straight line with described second main paragraph.
Beneficial effect using above-mentioned further scheme is：When using this launching cradle, main by the first of launching cradle body
Body section is expanded to and is in collinear position with the second main paragraph, and the first main paragraph and the second main paragraph are locked；Work as portion
During using this launching cradle, the first main paragraph and the second main paragraph can be folded, be readily transported, easy to operate, a people can be complete
Become expansion and the folding of launching cradle.
Further, described cylinder body includes the first cylinder and the second cylinder, and described first cylinder is arranged on described first
Main paragraph, described second cylinder is arranged on described second main paragraph；Described first main paragraph is expanded to and described second main paragraph
When being on same straight line, described first cylinder and the second cylinder pass through fittings.
Present invention also offers a kind of ejection system for unmanned plane transmitting, it include described above for unmanned plane
The launching cradle of transmitting, the compressed-air energy storage tank being arranged on described launching cradle body and air compressor, described compressed air
Energy storage canister is connected with described air compressor and described cylinder body respectively, for providing compressed air to described cylinder body.
Further, described compressed-air energy storage tank is arranged on described launching cradle body.
Further, also include pneumatic spring telescoping tube, described air compressor passes through described pneumatic spring telescoping tube and institute
State air energy storage canister to connect.
Further, also include control device and electromagnetic valve, described control device respectively with described air compressor and described
Electromagnetic valve connects, and described air energy storage canister is connected with described cylinder body by described electromagnetic valve.
Beneficial effect using above-mentioned further scheme is：Control the unlatching of electromagnetic valve by control device, sky will be compressed
To cylinder, gases at high pressure do work to piston for gas abrupt release, drive the sliding frame that runs to move along a straight line on launching cradle, clash into ejection
Stop after ejection rope on frame, thus unmanned plane is launched, whole process only needs remotely control, simple to operate, can
It is greatly enhanced unmanned plane emission effciency.
Further, also include pressure-detecting device, described pressure-detecting device and described air energy storage canister and described control
Device connects, and for monitoring the pressure of described air energy storage canister, and the pressure value being monitored feeds back to described control device.
Beneficial effect using above-mentioned further scheme is：Using in pressure-detecting device timely feedback air energy storage canister
Gas pressure, is easy to adjust, using control device, the air pressure that compressor conveys to air energy storage canister, thus can achieve difference
The unmanned aerial vehicle ejecting of weight.
Brief description
The structural representation of the launching cradle for unmanned plane transmitting that Fig. 1 provides for the embodiment of the present invention one；
The structural representation of the launching cradle for unmanned plane transmitting that Fig. 2 provides for the embodiment of the present invention two；
The structural representation of the deployed condition of the launching cradle for unmanned plane transmitting that Fig. 3 provides for the embodiment of the present invention two
Figure；
Fig. 4 is the enlarged drawing of A in Fig. 3；
The structural representation of the folded state of the launching cradle for unmanned plane transmitting that Fig. 5 provides for the embodiment of the present invention two
Figure；
The structural representation of the ejection system for unmanned plane transmitting that Fig. 6 provides for the embodiment of the present invention three.
In accompanying drawing, the list of parts representated by each label is as follows：
1- launching cradle body, 2- is sliding to run frame, 3- first main paragraph, 4- second main paragraph, 5- folding hinge, 6- rotating shaft, 7-
First connector, 8- second connector, 9- locking clamping apparatus, 10- locking member, 11- first cylinder, 12- second cylinder, 13- joint,
14- air energy storage canister, 15- electromagnetic valve, 16- cylinder body.
Specific embodiment
Below in conjunction with accompanying drawing, the principle of the present invention and feature are described, example is served only for explaining the present invention, and
Non- for limiting the scope of the present invention.It should be noted that in the case of not conflicting, in embodiments herein and embodiment
Feature can be mutually combined.
Embodiment one
As shown in figure 1, present embodiments providing a kind of launching cradle for unmanned plane transmitting, it include launching cradle body 1,
Sliding race frame 2, ejection rope and driving means；The described sliding frame 2 that runs is arranged on described launching cradle body 1, for carrying and launching no
Man-machine；Described ejection rope is arranged on the transmitting terminal of described launching cradle body 1, and the described sliding frame 2 that runs is arranged at described launching cradle body 1
Initial end, and can along described launching cradle body 1 bearing of trend slide；Described driving means are connected with the described sliding frame 2 that runs, and use
In driving the described sliding frame 2 that runs along the bearing of trend movement of described launching cradle body 1, so that the described sliding frame 2 that runs collides described bullet
Penetrate rope and launch described unmanned plane.
It drives the sliding frame 2 that runs to move on launching cradle body 1 using driving means, when sliding race frame 2 collision ejection rope, sliding
Run frame 2 because being stopped by launching the resistance restricted moving, positioned at the sliding unmanned plane running on frame 2 then because inertia is launched away,
The whole emission process of unmanned plane, the stretcher strain that need not rely on stretch cord is for sliding the mobile offer power running frame 2 so that launching
The overall volume of frame 2 is less, operation is relatively easy, is conducive to improving the emission effciency of unmanned plane.
Embodiment two
As shown in Figures 2 to 4, a kind of launching cradle for unmanned plane transmitting that the present embodiment provides, it includes launching cradle originally
Body 1, sliding race frame 2, ejection rope and driving means；The described sliding frame 2 that runs is arranged on described launching cradle body 1, concurrent for carrying
Penetrate unmanned plane；Described ejection rope is arranged on the transmitting terminal of described launching cradle body 1, and the described sliding frame 2 that runs is arranged at described launching cradle
The initial end of body 1, and can slide along the bearing of trend of described launching cradle body 1；Described driving means are connected with the described sliding frame 2 that runs
Connect, for driving the described sliding frame 2 that runs along the bearing of trend movement of described launching cradle body 1, so that described sliding race frame 2 collision institute
State ejection rope and launch described unmanned plane.
In one of embodiment of the present embodiment, this driving means adopts hydraulic driving mode, specifically, this drive
Dynamic device includes cylinder body, the First piston bar being arranged in described cylinder body and first piston；This first piston
The first end of bar should be fixed on this first piston, and the second end extends to the axial direction of cylinder body；This cylinder body
Should be arranged on launching cradle body 1, its axial direction is consistent with the bearing of trend of described launching cradle body 1, this First piston bar
The second end be connected with the sliding frame 2 that runs；When needing to launch described unmanned plane, it is passed through high pressure liquid force feed in cylinder body, the
One piston rod moves in its bearing of trend of drive lower edge of first piston, and drives the sliding race transmitting terminal to launching cradle body 1 for the frame 2
Mobile.This kind of driving means use hydraulic-driven principle, promote sliding race frame 2 prolonging in launching cradle body 1 under the drive of piston
Stretch rectilinear movement on direction, when sliding race frame 2 touches ejection rope, the sliding frame 2 that runs stops due to the resistance restricted by ejection moving,
It is located at the sliding unmanned plane running on frame 2 then because inertia is launched away.
In a preferred implementation of the present embodiment, also unmanned plane can be launched using pneumatic mode, specifically, such as scheme
Shown in 2, this driving means includes cylinder body 16, the second piston bar being arranged in this cylinder body 16 and second piston；Should
The first end of second piston bar is fixed in second piston, and the second end extends to the axial direction of cylinder body 16；Cylinder body
16 are arranged on launching cradle body 1, and its axial direction is consistent with the bearing of trend of launching cradle body 1, and the second of second piston bar
End is connected with the sliding frame 2 that runs；When needing to launch described unmanned plane, it is passed through compressed air, second piston bar in cylinder body 16
Move in its bearing of trend of drive lower edge of second piston, the cunning that the mobile drive of second piston bar is attached thereto runs frame 2 in bullet
Penetrate rectilinear movement on the bearing of trend of frame body 1, when sliding race frame 2 moves to launching cradle body 1 transmitting terminal, touch ejection rope
And stop moving, the unmanned plane on launching cradle 2 is then launched away, completes the transmitting of unmanned plane.For ease of sliding run frame 2 with
The connection of second piston bar, the sliding frame 2 that runs is connected by the stake rope of available Kev with second piston bar, promotes to slide race frame 2 with second
Piston rod synchronous linear moves.
Easy to use for ease of launching cradle 2, in one of embodiment of the present embodiment, as shown in Figure 3,4, Fig. 4
For the enlarged drawing of A in Fig. 3, described launching cradle body 1 includes the first main paragraph 3 and the second main paragraph 4, described first main paragraph 3
With described second main paragraph 4 be hinged so that described first main paragraph 3 be folded to the position parallel with described second main paragraph 4 or
Described first main paragraph 3 is expanded to be on same straight line with described second main paragraph 4.Wherein, described first main paragraph 3
To pass through folding hinge 5 hinged with the second main paragraph 4, and described folding hinge 5 is provided with rotating shaft 6 and the first connector 7, and described the
Second connector 8 is provided with two main paragraphs 4, when folding described first main paragraph 3, as shown in figure 5, described first main paragraph
3 turn to the position parallel with described second main paragraph 4 around described rotating shaft 6, when launching described first main paragraph 3, as Fig. 3 institute
Show, described first main paragraph 3 turns to around described rotating shaft 6 and is in collinear position with described second main paragraph 4, and first even
Fitting 7 and the second connector 8 clamping.For ensureing that the first main paragraph 3 tightened together with the second main paragraph 4, can be in the second main body
In section 4, locking clamping apparatus 9 are set, the locking member 10 being matched with described locking clamping apparatus 9 is provided with the first main paragraph 3, when the
One main paragraph 3 turns to around described rotating shaft 6 when being in collinear position with described second main paragraph 4, the first connector 7 with
Second connector 8 clamping, meanwhile, by the cooperation of locking member 10 and locking clamping apparatus 9 by the first main paragraph 3 and the second main paragraph 4
Fastening.In practical operation, only need a people can launch launching cradle to connecting, easy to operate, save the installation of launching cradle
Time.
For ensureing not produce impact to cylinder body when folding the first main paragraph 3, cylinder body is designed as two-period form
Structure, that is, this cylinder body 16 include the first cylinder 11 and the second cylinder 12, it is main that described first cylinder 11 is arranged on described first
Body section 3, described second cylinder 12 is arranged on described second main paragraph 4；Described first main paragraph 3 is expanded to main with described second
When body section 4 is on same straight line, described first cylinder 11 is connected by joint 13 with the second cylinder 12, completes the first main paragraph
3 and second main paragraph 4 fastening and the first cylinder 11 and the second cylinder 12 connection, set about implement unmanned plane transmitting beam worker
Make.
To sum up, the launching cradle for unmanned plane transmitting providing in multiple embodiments in the present embodiment, it utilizes hydraulic pressure
Type of drive or pneumatic mode drive the sliding frame 2 that runs to move on launching cradle body 1, it is to avoid using stretch cord in prior art
The problem leading to, can be rapidly completed the transmitting of unmanned plane；Meanwhile, when installing launching cradle or reclaiming launching cradle, simple to operate fast
Prompt.
Embodiment three
As shown in fig. 6, present embodiments providing a kind of ejection system for unmanned plane transmitting, it includes above-described embodiment
The launching cradle for unmanned plane transmitting described in one or two, the compressed-air energy storage tank 14 being arranged on launching cradle body 1 and sky
Air compressor, this compressed-air energy storage tank 14 is connected with air compressor and cylinder body respectively, for providing to cylinder body
Compressed air.
For ease of operating the transmitting of unmanned plane, improve the automatization of this ejection system, increase control device within the system
With electromagnetic valve 15, air energy storage canister 14 is connected with cylinder body by electromagnetic valve 15, and control device passes through electromagnetic valve 15 control line
With cylinder body even, air compressor therein can be connected with air energy storage canister 14 by pneumatic spring telescoping tube, be easy to sky
Convey compression control in gas energy storage tank 14, a pressure-detecting device also can be set, by this pressure-detecting device and air energy storage canister
14 and control device connect, using the gas pressure in this pressure-detecting device real-time monitoring air energy storage canister 14.Specifically, may be used
One electric cabinet of setting, setting lithium battery, air compressor, pressure-detecting device, control line of electromagnetic valve, pneumatic in electric cabinet
The electrical equipment such as spring extension tube and controlling switch, control unit, when needing to prepare for transmitting unmanned plane, by electromagnetic valve control
Line processed is taken out and is connected between electromagnetic valve 15 and control unit, the connection of pneumatic spring telescoping tube is taken out and is connected to air compressor
And air energy storage canister 14 between, it is air energy storage canister 14 conveying compressed air, pressure-detecting device is by force information back to control
Device processed, control device determines when to stop conveying compressed air to air energy storage canister 14 according to the pressure information of feedback, automatically
The inflation of stopping air energy storage canister 14, and automatically control the unlatching of electromagnetic valve 15, to cylinder body abrupt release compressed air, gas
Cylinder drives the sliding frame 2 that runs to move linearly on launching cradle body 1, implements the Launch Operation of unmanned plane.When complete unmanned plane send out
After penetrating, pneumatic spring telescoping tube and control line of electromagnetic valve can be accommodated in electric cabinet.
Cylinder body described above or pneumatic cylinder body can be designed with launching cradle body 1 detachable, also can one
Formula designs it is preferable that adopting unitary design, make launching cradle globality higher and make compressed-air energy storage tank 14 and cylinder this
The distance of body is shorter, reduces the resistance of ducting, raising efficiency.
The ejection system for unmanned plane transmitting being provided based on the present embodiment, it is due to being the energy storage shape with compressed air
Formula, no matter so be the place of height above sea level or reality can be carried out by adjusting the pressure store of compressed air in the low place of height above sea level
Now reasonably launch demand, therefore, it can adjust compressed gas according to different height above sea levels or different ejection weight
Pressure store require realizing ejection, and regulative mode is quick and easy；In addition, not having key components and partss to be subject to height in this system
The impact and accelerating of temperature or low temperature was lost efficacy aging, made operation more reliable；Furthermore, due to using different from common stretch cord
The principle of stored energy form, using globality and the small size advantage of cylinder, will be all big to the overall dimensions of whole launching cradle and weight
Big reduce so that lighter during operation in the wild save trouble.
In describing the invention, it should be noted that the orientation of instruction or the position such as term " top ", " bottom ", " interior ", " outward "
The relation of putting is based on orientation shown in the drawings or position relationship, is for only for ease of the description present invention and simplifies description, rather than
Indicate or the hint device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not
It is interpreted as limitation of the present invention.Additionally, term " first ", " second " be only used for describe purpose, and it is not intended that instruction or
Hint relative importance.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or is integrally connected；Can
To be to be mechanically connected or electrical connection；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.Additionally, in describing the invention, unless otherwise stated, " multiple " are meant that two or two
More than.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all spirit in the present invention and
Within principle, any modification, equivalent substitution and improvement made etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of launching cradle for unmanned plane transmitting is it is characterised in that include launching cradle body (1), sliding race frame (2), ejection
Rope and driving means；The described sliding frame (2) that runs is arranged on described launching cradle body (1), for carrying and launching unmanned plane；
Described ejection rope is arranged on the transmitting terminal of described launching cradle body (1), and the described sliding frame (2) that runs is arranged at described launching cradle originally
The initial end of body (1), and can slide along the bearing of trend of described launching cradle body (1)；
Described driving means are connected with the described sliding frame (2) that runs, for driving the described sliding frame (2) that runs along described launching cradle body (1)
Bearing of trend move sliding run frame (2) collision described ejection rope and launch described unmanned plane so that described.
2. the launching cradle for unmanned plane transmitting according to claim 1 is it is characterised in that described driving means include liquid
Cylinder pressure body, the First piston bar being arranged in described cylinder body and first piston；The first end of described First piston bar
It is fixed on described first piston, the second end extends to the axial direction of described cylinder body；
Described cylinder body is arranged on described launching cradle body (1), and its axial direction is prolonged with described launching cradle body (1)
Stretch direction consistent, the second end of described First piston bar is connected with the described sliding frame that runs；
When launching described unmanned plane, in described cylinder body, it is passed through hydraulic oil, described First piston bar is lived described first
Its bearing of trend of drive lower edge of plug moves, to drive the described sliding frame (2) that runs to move to the transmitting terminal of described launching cradle body (1)
Dynamic.
3. the launching cradle for unmanned plane transmitting according to claim 1 is it is characterised in that described driving means include gas
Cylinder body (16), the second piston bar being arranged in described cylinder body (16) and second piston；The of described second piston bar
One end is fixed in described second piston, and the second end extends to the axial direction of described cylinder body (16)；
Described cylinder body (16) is arranged on described launching cradle body (1), its axial direction and described launching cradle body (1)
Bearing of trend is consistent, and the second end of described second piston bar is connected with the described sliding frame (2) that runs；
When launching described unmanned plane, in described cylinder body (16), it is passed through compressed air, described second piston bar is described
Its bearing of trend of drive lower edge of two pistons moves, to drive the transmitting terminal to described launching cradle body (1) for described sliding race frame (2)
Mobile.
4. the launching cradle for unmanned plane transmitting according to claim 3 is it is characterised in that described launching cradle body (1)
Including the first main paragraph (3) and the second main paragraph (4), described first main paragraph (3) hinged with described second main paragraph (4) so that
Obtain described first main paragraph (3) to be folded to the position parallel with described second main paragraph (4) or make described first main paragraph (3)
It is expanded to and be on same straight line with described second main paragraph (4).
5. the launching cradle for unmanned plane transmitting according to claim 4 is it is characterised in that described cylinder body (16) wraps
Include the first cylinder (11) and the second cylinder (12), described first cylinder (11) is arranged on described first main paragraph (3), described second
Cylinder (12) is arranged on described second main paragraph (4)；
Described first main paragraph (3) is expanded to when being on same straight line with described second main paragraph (4), described first cylinder
(11) connected by joint (13) with the second cylinder (12).
6. a kind of ejection system for unmanned plane transmitting is it is characterised in that include described in the claims 1 or 3 or 4 or 5
The launching cradle for unmanned plane transmitting, compressed-air energy storage tank (14) and air compressor, described compressed-air energy storage tank
(14) it is connected with described air compressor and described cylinder body (16) respectively, for providing compression to described cylinder body (16)
Air.
7. the ejection system for unmanned plane transmitting according to claim 6 is it is characterised in that described compressed-air energy storage
Tank (14) is arranged on described launching cradle body (1).
8. the ejection system for unmanned plane transmitting according to claim 6 is stretched it is characterised in that also including pneumatic spring
The draw, described air compressor is connected with described air energy storage canister (14) by described pneumatic spring telescoping tube.
9. the ejection system for unmanned plane transmitting according to claim 6 it is characterised in that also include control device and
Electromagnetic valve (15), described control device is connected with described air compressor and described electromagnetic valve (15) respectively, described air energy storage
Tank (14) is connected with described cylinder body (16) by described electromagnetic valve (15).
10. the ejection system for unmanned plane transmitting according to claim 9 is it is characterised in that also include pressure detecting
Device, described pressure-detecting device is connected with described air energy storage canister (14) and described control device respectively, described for monitoring
The pressure of air energy storage canister, and the pressure value being monitored feeds back to described control device.
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| CN201611032477.3A CN106428604B (en) | 2016-11-16 | 2016-11-16 | A launching cradle and ejection system for unmanned aerial vehicle transmission |
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| CN201611032477.3A CN106428604B (en) | 2016-11-16 | 2016-11-16 | A launching cradle and ejection system for unmanned aerial vehicle transmission |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107380477A (en) * | 2017-08-31 | 2017-11-24 | 长光卫星技术有限公司 | Folding ejector can quickly be assembled |
| CN107600449A (en) * | 2017-09-06 | 2018-01-19 | 哈尔滨工业大学 | A kind of unmanned aerial vehicle ejecting device |
| CN108116691A (en) * | 2017-12-29 | 2018-06-05 | 郑州光之源电子科技有限公司 | A kind of hydraulic catapult method of unmanned plane |
| 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 |
| CN109110146A (en) * | 2018-09-03 | 2019-01-01 | 芜湖天航装备技术有限公司 | A kind of self-adjustable unmanned plane emitter of throw-weight |
| CN109502043A (en) * | 2018-09-30 | 2019-03-22 | 沈阳戈达德智能装备科技有限公司 | A kind of long-range Quality Initiative driven motor ejector system of small drone |
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