CN205759688U - A kind of SUAV - Google Patents
A kind of SUAV Download PDFInfo
- Publication number
- CN205759688U CN205759688U CN201620447296.6U CN201620447296U CN205759688U CN 205759688 U CN205759688 U CN 205759688U CN 201620447296 U CN201620447296 U CN 201620447296U CN 205759688 U CN205759688 U CN 205759688U
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- fuselage
- control
- horn
- suav
- remote
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Abstract
A kind of SUAV, including fuselage main body and fuselage cover, fuselage main body is included lower module and upper layer module, is connected by shock structure between lower module with upper layer module；The internally installed receiver of remote-control sytem of fuselage upper layer module with fly control, the signal output part of receiver of remote-control sytem connects the signal input part flying control, the signal output part flying control connects electron speed regulator, electron speed regulator is arranged on horn, the outfan of electron speed regulator connects brushless motor, and the outfan of photographic head is connected with image transmission module input；Unmanned plane is energized, flying to control automatic check flight device attitude and state, if flight state is good, flying control can inform and can fly by flash for prompting, remote controller is by transmitting remote signal to receiver of remote-control sytem, and receiver of remote-control sytem transmits a signal to fly control manipulation unmanned plane and takes off, cruises and land；This utility model has centre of gravity, rationally distributed, fuselage fast assembling-disassembling, structural strength feature high, lightweight.
Description
Technical field
This utility model relates to unmanned plane modelling technique field, particularly to a kind of SUAV.
Background technology
Currently, unmanned plane market is like a raging fire, and the kind of civilian unmanned plane and purposes are the most increasingly
Many, wherein FPV (First Person View) is the one of unmanned plane function presentation mode.
Small-sized FPV unmanned plane is also known as " passing through machine ", and it can " first person " high-speed flight
Advantage, bring strong visual impact sense to player and atypical experience, receiving vast consumption
Person and the favor of specialty player.Unmanned plane rider tournament is also known as the Formula 1 in unmanned plane, player
Match can be participated in designed, designed or purchase " passing through machine ".But player operate at ordinary times FPV without
Time man-machine, often result in unmanned plane air crash, or cause unmanned plane with other hard thing high velocity impacts
Damaging, FPV unmanned plane is little because of its volume, and part is little, disassembles inconvenience, therefore keeps in repair numerous and diverse,
And the design of some type is unreasonable, causes damaging other important zero in crash course
Part, control like flying, motor, image transmission module etc..
Summary of the invention
In order to overcome above-mentioned existing defect, the purpose of this utility model is to provide a kind of small-sized nothing
Man-machine, there is centre of gravity, rationally distributed, two-piece unit design, integral type damping, fuselage fast
Speed dismounting, structural strength feature high, lightweight.
To achieve these goals, the technical solution adopted in the utility model is:
A kind of SUAV, including fuselage main body 2 and fuselage cover 1, described fuselage master
Body 2 includes lower module 3 and upper layer module 4, logical between lower module 3 and upper layer module 4
Cross shock structure 5 to connect；
Described upper layer module 4 includes fuselage base plate 6 and fuselage roof 7, at fuselage base plate 6
Fuselage roof 7 both sides are provided with fuselage side plate 22；Described fuselage base plate 6 front end is installed
There are photographic head fixed plate 10 and camera bracket 11；
Described lower module 3 includes horn reinforcing plate 12, at four of horn reinforcing plate 12
Being provided with horn 13 on angle, the top of horn 13 is provided with motor cabinet 14；Brushless motor
20 are arranged on motor cabinet 14, brushless motor 20 is installed anti-oar 16 and just starches 17；Instead
Oar 16 with just starch 17 and arrange two-by-two in diagonal angle；
The described internally installed receiver of remote-control sytem of fuselage upper layer module 4 23 with fly to control 18, remote control
The signal output part connection of receptor 23 flies to control the signal input part of 18, flies to control the signal of 18
Outfan connects electron speed regulator 19, and electron speed regulator 19 is arranged on horn 13, electronics
The outfan of speed regulator 19 connects brushless motor 20, and described camera bracket 11 is pacified
Equipped with photographic head 25, the outfan of photographic head 25 is connected with image transmission module 24 input.
Described fuselage cover 1 is streamlined many curved surfaces, and sideline, fuselage side plate 22 top is for becoming
The streamlined circular arc of radius, fits with fuselage cover 1.
Described fuselage side plate 22 is fiber side plate.
Described lower module 3 is demountable structure.
Described horn 13 is independently mounted in horn reinforcing plate 12.
Fuselage side plate 22 front end of described both sides is connected by fuselage side bolt 8, and rear end leads to
Cross fixed bolt 9 to connect.
Described shock structure 5 is rubber shock absorber strut.
Described fuselage main body 2 uses 3K carbon fibre materials, horn 13 and horn reinforcing plate
The 12 3K carbon fibers that have employed 3mm.
The beneficial effects of the utility model:
Use rubber shock absorber strut to be connected between lower module 3 with upper layer module 4, effectively reduce
In flight course, interference that top level control system is caused by the vibrations of lower floor's dynamical system.And
And fuselage is when falling or clash into hard thing, shock structure 5 can play the effect of buffering, usual feelings
Under condition, shock structure 5 can rupture, absorbing impact energy, protection flies to control 18, lithium battery 21,
Other important positions such as fuselage.
Further, the use of shock structure 5 so that between lower module 3 and upper layer module 4
Distance be more nearly so that this body nodal point is lower, flies more stable.
Accompanying drawing explanation
Fig. 1 is axis of no-feathering mapping of the present utility model.
Fig. 2 is fuselage of the present utility model upper and lower module explosive view.
Fig. 3 is this utility model upper strata fuselage module explosive view.
Fig. 4 is the scheme of installation of stand alone type horn of the present utility model.
Fig. 5 is this utility model structural representation.
Fig. 6 is this utility model internal structure catenation principle block diagram.
Detailed description of the invention
Below in conjunction with the accompanying drawings this utility model is described in further detail.
As shown in Figure 1 and Figure 2, a kind of SUAV, including fuselage main body 2 with fuselage outside
Shell 1, described fuselage main body 2 includes lower module 3 and upper layer module 4, at lower module
It is connected by shock structure 5 between 3 with upper layer module 4；Described shock structure 5 is rubber shock-absorbing
Post.
As it is shown on figure 3, described upper layer module 4 includes fuselage base plate 6 and fuselage roof 7,
Fuselage base plate 6 and fuselage roof 7 both sides are provided with fuselage side plate 22；At the bottom of described fuselage
Plate 6 front end is provided with photographic head fixed plate 10 and camera bracket 11；The machine of described both sides
Body side plate 22 front end is connected by fuselage side bolt 8, and rear end is connected by fixed bolt 9.
As shown in Figure 4, Figure 5, described lower module 3 includes horn reinforcing plate 12, at machine
Being provided with horn 13 on four angles of arm reinforcing plate 12, the top of horn 13 is provided with motor
Seat 14；Brushless motor 20 is arranged on motor cabinet 14, brushless motor 20 is installed anti-
Oar 16 with just starching 17；Anti-oar 16 with just starch 17 and arrange two-by-two in diagonal angle.
The described internally installed receiver of remote-control sytem of fuselage upper layer module 4 23 with fly to control 18, remote control
The outfan connection of receptor 23 flies to control the input of 18, flies to control the signal output part company of 18
Connecing electron speed regulator 19, electron speed regulator 19 is arranged on horn 13, electron speed regulator 19
Outfan connect brushless motor 20, described camera bracket 11 is provided with photographic head
25, the outfan of photographic head 25 is connected with image transmission module 24 input；Lithium battery 21
Power supply is provided to each parts.
Described fuselage cover 1 is streamlined many curved surfaces, described fuselage side plate 22 top sides
Line is the streamlined circular arc becoming radius, fits with fuselage cover 1.Can preferably protect fuselage
Main body 2.Described lower module 3 is demountable structure.Effectively prevent interior arrangement from damaging.
Described horn 13 is independently mounted in horn reinforcing plate 12.
Described fuselage side plate 22 is fiber side plate.
Fuselage cover 1 uses PC material, soft flexible, when being clashed into, can occur
Elastic deformation, absorbing impact energy, body is played a protective role.
Fuselage cover 1 is streamlined many curved design, can effectively reduce the windage that body moves ahead,
Make to fly more efficient, flight attitude is more stable.
Fuselage main body 2 uses the 3K carbon fibre materials that quality is little, intensity is high so that fuselage master
Body 2 react the quickest simply, and resistance to fall, Impact Resisting Capability strengthens, wherein horn 13 and machine
Arm reinforcing plate 12 have employed thickness especially and reaches the 3K carbon fiber of 3mm, improves fuselage further
Integral rigidity and intensity.
Operation principle of the present utility model:
Unmanned plane is energized, flies to control 18 automatic check flight device attitude and states, if aircraft
In good condition, flying to control 18 can inform and can fly by flash for prompting, and remote controller is by launching remote control
Signal (generally 2.4G Frequency Hopping Signal) gives receiver of remote-control sytem 23, and receiver of remote-control sytem 23 passes
Defeated signal is flown to control 18, informs that flying to control 18 can unlock and take off, the most controllable unmanned plane takes off,
Cruise and landing.
After taking off, due to the change of carriage angle, fly to control the electronic gyroscope within 18 and
The change of attitude of flight vehicle experienced by electron acceleration measuring instrument, will automatically export correction signal to
Electron speed regulator 19, electron speed regulator 19, from lithium battery 21 power taking, controls brushless motor
The rotating speed of 20, and then control the rotating speed of propeller, ensure the attitude stabilization of aircraft.With
This simultaneously, the picture signal that photographic head 25 gathers will be conveyed to image transmission module 24, image
Transport module 24 is that another kind of frequency (usually 5.8G Frequency Hopping Signal) launches equipment, image
Transport module 24 transmits signal and shows.
Claims (8)
1. a SUAV, including fuselage main body (2) and fuselage cover (1), it is special
Levying and be, described fuselage main body (2) includes lower module (3) and upper layer module (4),
It is connected by shock structure (5) between lower module (3) with upper layer module (4)；
Described upper layer module (4) includes fuselage base plate (6) and fuselage roof (7), at machine
Body base plate (6) and fuselage roof (7) both sides are provided with fuselage side plate (22)；Described machine
Body base plate (6) front end is provided with photographic head fixed plate (10) and camera bracket (11)；
Described lower module (3) includes horn reinforcing plate (12), in horn reinforcing plate (12)
Four angles on horn (13) is installed, the top of horn (13) is provided with motor cabinet (14)；
Brushless motor (20) is arranged on motor cabinet (14), and brushless motor (20) is upper to be installed
Anti-oar (16) with just starch (17)；Anti-oar (16) is arranged in diagonal angle two-by-two with just starching (17)；
Described fuselage upper layer module (4) internally installed receiver of remote-control sytem (23) with fly control (18),
The signal output part of receiver of remote-control sytem (23) connects the signal input part flying to control (18), flies control
(18) signal output part connects electron speed regulator (19), and electron speed regulator (19) is installed
On horn (13), the outfan of electron speed regulator (19) connects brushless motor (20),
Photographic head (25) is installed, photographic head (25) defeated on described camera bracket (11)
Go out end to be connected with image transmission module (24) input.
A kind of SUAV the most according to claim 1, it is characterised in that described
Fuselage cover (1) be streamlined many curved surfaces, fuselage side plate (22) sideline, top is for becoming half
The streamlined circular arc in footpath, fits with fuselage cover (1).
A kind of SUAV the most according to claim 1, it is characterised in that described
Fuselage side plate (22) be fiber side plate.
A kind of SUAV the most according to claim 1, it is characterised in that described
Lower module (3) be demountable structure.
A kind of SUAV the most according to claim 1, it is characterised in that described
Horn (13) be independently mounted in horn reinforcing plate (12).
A kind of SUAV the most according to claim 1, it is characterised in that described
Both sides fuselage side plate (22) front end by fuselage side bolt (8) connect, rear end is passed through
Fixed bolt (9) connects.
A kind of SUAV the most according to claim 1, it is characterised in that described
Shock structure (5) be rubber shock absorber strut.
A kind of SUAV the most according to claim 1, it is characterised in that described
Fuselage main body (2) use 3K carbon fibre materials, horn (13) and horn reinforcing plate (12)
Use the 3K carbon fiber of 3mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620447296.6U CN205759688U (en) | 2016-05-17 | 2016-05-17 | A kind of SUAV |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620447296.6U CN205759688U (en) | 2016-05-17 | 2016-05-17 | A kind of SUAV |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205759688U true CN205759688U (en) | 2016-12-07 |
Family
ID=58118947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620447296.6U Expired - Fee Related CN205759688U (en) | 2016-05-17 | 2016-05-17 | A kind of SUAV |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205759688U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107316352A (en) * | 2017-07-13 | 2017-11-03 | 东莞市异能无人机科技有限公司 | A kind of unmanned plane match timing and scoring system |
| CN109625254A (en) * | 2018-12-28 | 2019-04-16 | 浙江星米体育有限公司 | Sports class unmanned plane |
| CN110678389A (en) * | 2018-09-26 | 2020-01-10 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN111846228A (en) * | 2020-07-15 | 2020-10-30 | 嘉创飞航(苏州)智能科技有限公司 | Multifunctional unmanned aerial vehicle |
-
2016
- 2016-05-17 CN CN201620447296.6U patent/CN205759688U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107316352A (en) * | 2017-07-13 | 2017-11-03 | 东莞市异能无人机科技有限公司 | A kind of unmanned plane match timing and scoring system |
| CN107316352B (en) * | 2017-07-13 | 2023-03-28 | 东莞市异能无人机科技有限公司 | Unmanned aerial vehicle match timing branch system |
| CN110678389A (en) * | 2018-09-26 | 2020-01-10 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN109625254A (en) * | 2018-12-28 | 2019-04-16 | 浙江星米体育有限公司 | Sports class unmanned plane |
| CN111846228A (en) * | 2020-07-15 | 2020-10-30 | 嘉创飞航(苏州)智能科技有限公司 | Multifunctional unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161207 Termination date: 20170517 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |