CN205060006U - Four -rotor unmanned aerial vehicle - Google Patents
Four -rotor unmanned aerial vehicle Download PDFInfo
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- CN205060006U CN205060006U CN201520748614.8U CN201520748614U CN205060006U CN 205060006 U CN205060006 U CN 205060006U CN 201520748614 U CN201520748614 U CN 201520748614U CN 205060006 U CN205060006 U CN 205060006U
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Abstract
The utility model provides a four -rotor unmanned aerial vehicle, includes fuselage and two flight arms, screwed connection is passed through on the fuselage in the middle part of flight arm, is provided with the motor respectively at the both ends of flight arm, is equipped with the screw at the output of motor. Unmanned aerial vehicle adopts and passes through screwed connection on the fuselage with the middle part of two flight arms to set up motor and screw respectively at the both ends of each flight arm, revolve wing structure in order to form four, only can form the wing arm of four rotors through two flight arms, simple structure, easily equipment, and structural stability obviously improves, article two, the flight arm all be through screwed connection on the fuselage, make things convenient for the dismouting, it is little to dismantle back occupation space, portable.
Description
Technical field
The utility model relates generally to unmanned air vehicle technique field, particularly relates to four rotor wing unmanned aerial vehicle technical fields.
Background technology
Many rotor wing unmanned aerial vehicles are one unmanned plane during flying devices comparatively flexibly, mainly comprise the several types such as four rotor wing unmanned aerial vehicles, six rotor wing unmanned aerial vehicles, eight rotor wing unmanned aerial vehicles, wherein especially maximum, most widely used with four rotor wing unmanned aerial vehicles.
At present, four rotor wing unmanned aerial vehicle aircraft on market are all adopt hub-and-spoke configuration, are mainly made up of the flight arm of fuselage and four translators and screw propeller, and this structure takes up room comparatively greatly, should not carry, and dismounting trouble, less stable.
Summary of the invention
The utility model provides a kind of four rotor wing unmanned aerial vehicles, and this unmanned plane structure easy disassembly, take up room little, be easy to carry, and structural stability significantly improves after dismounting.
The technical scheme that the utility model adopts is:
A kind of four rotor wing unmanned aerial vehicles, comprise fuselage and two flight arms, the middle part of flight arm is connected on fuselage by screw, is respectively arranged with motor, is provided with screw propeller at the mouth of motor at the two ends of flight arm.
Above-mentioned unmanned plane adopts and is connected on fuselage by the middle part of two flight arms by screw, and motor and screw propeller are set respectively at the two ends of each flight arm, to form four rotor structures, the wing arm of four rotors can be formed by means of only two flight arms, structure is simple, be easy to assembling, and structural stability significantly improves; Article two, the arm that flies is all be connected on fuselage by screw, and easy disassembly, takes up room after dismounting little, be easy to carry.
The middle part of arbitrary flight arm offers the recess at the middle part that can hold another flight arm.Article two, the middle part of flight arm is fitted together to mutually, and to realize relatively fixing, and then be arranged on fuselage, structure is more stable, and ensures that flight arm is all positioned in same level, and namely each screw propeller is all positioned in same level, ensures the performance of unmanned plane.
Article two, the arm that flies is that square crossing is fixed.Structure is simple, improves product stability.
In flight arm, corresponding each motor is respectively equipped with electronic governor.The rotating speed of flexible motor, can adjust the rotating speed of screw propeller according to actual needs.
Above fuselage, be provided with gps antenna, in fuselage, be provided with the remote control reception module of flight control modules, wireless image transmission module, wireless digital transmission module and reception remote controller signal, below fuselage, be connected with sensor carry by screw.Make full use of integrated space, carry the different sensor device such as numeric data code camera, photography camera by lift-launch in sensor carry and carry out operation, sensor carry is dismantled and assembled, easy to carry.
Below outside two of fuselage is arranged with alighting gear, under the both sides, upper end of alighting gear are connected to adjacent two flight arms respectively by screw.Alighting gear is dismantled and assembled, easy to carry, and be arranged on two flight arms, Stability Analysis of Structures, impact resistance significantly improves.
Alighting gear is N-shaped, is connected with battery carry in the below of alighting gear by screw.Can load battery in battery carry, for the device on unmanned plane is powered, structure is simply dismantled and assembled, easy to carry.
The beneficial effect that the utility model brings is:
This unmanned plane structure is simple, and achieve two flight arms and carry four motors and four screw propellers, be easy to assembling, structural stability significantly improves; And easy disassembly, take up room after dismounting little, be easy to carry.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of the utility model embodiment;
Fig. 2 is the front view of the utility model embodiment;
Fig. 3 is the left view of the utility model embodiment;
Fig. 4 is the structural representation after the dismounting of the utility model embodiment;
Reference numeral:
1, electronic governor; 2, motor; 3, screw propeller; 4, gps antenna; 5, flight control modules; 6, wireless image transmission module; 7, wireless digital transmission module; 8, remote control reception module; 9, remote controller; 10, battery carry; 11, sensor carry; 12, alighting gear; 13, fly arm; 14, fuselage; 15, recess.
Detailed description of the invention
As Figure 1-4, a kind of four rotor wing unmanned aerial vehicles, comprise fuselage 14 and two flight arms 13, the middle part of flight arm 13 is connected on fuselage 14 by screw, is respectively arranged with motor 2, is provided with screw propeller 3 at the mouth of motor 2 at the two ends of flight arm 13.
Unmanned plane adopts and is connected on fuselage 14 by the middle part of two flight arms 13 by screw, and motor 2 and screw propeller 3 are set respectively at the two ends of each flight arm 13, to form four rotor structures, the wing arm of four rotors can be formed by means of only two flight arms 13, structure is simple, be easy to assembling, and structural stability significantly improves; Article two, the arm 13 that flies is all be connected on fuselage 14 by screw, and easy disassembly, takes up room after dismounting little, be easy to carry.
The middle part of arbitrary flight arm 13 offers the recess 15 at the middle part that can hold another flight arm 13.Article two, the middle part of flight arm 13 is fitted together to mutually, and to realize relatively fixing, and then be arranged on fuselage 14, structure is more stable, and ensures that flight arm 13 is all positioned in same level, and namely each screw propeller 3 is all positioned in same level, ensures the performance of unmanned plane.
Article two, the arm 13 that flies is fixed in square crossing.Structure is simple, improves product stability.
In flight arm 13, corresponding each motor 2 is respectively equipped with electronic governor 1.The rotating speed of flexible motor 2, can adjust the rotating speed of screw propeller 3 according to actual needs.
Gps antenna 4 is provided with above fuselage 14, in fuselage 14, be provided with the remote control reception module 8 of flight control modules 5, wireless image transmission module 6, wireless digital transmission module 7 and reception remote controller 9 signal, below fuselage 14, be connected with sensor carry 11 by screw.Make full use of integrated space, carry the different sensor device such as numeric data code camera, photography camera by lift-launch in sensor carry 11 and carry out operation, sensor carry 11 is dismantled and assembled, easy to carry.
Below outside two of fuselage 14 is arranged with alighting gear 12, and the both sides, upper end of alighting gear 12 are connected to adjacent two flight arm 13 times respectively by screw.Alighting gear 12 is dismantled and assembled, easy to carry, and be arranged on two flight arms 13, Stability Analysis of Structures, impact resistance significantly improves.
Alighting gear 12, in N-shaped, is connected with battery carry 10 in the below of alighting gear 12 by screw.Can load battery in battery carry 10, structure is simply dismantled and assembled, easy to carry.
Concrete implementation step during this four rotor wing unmanned aerial vehicles application is:
(1) first electronic governor 1 correspondence is embedded in flight arm 13, gps antenna 4 is fixed on fuselage 14, flight control modules 5, wireless image transmission module 6, wireless digital transmission module 7, remote control reception module 8 are mounted and fixed in fuselage 14;
(2) 4 screw propellers 3 are arranged on the mouth of 4 motors 2 respectively, 4 motors 2 are mounted on 2 flight arms 13, and electronic governor 1 is connected with motor 2 signal;
(3) middle part recess 15 pairs of recesses 15 of 2 flight arms 13 are carried out square crossing to fix, and be arranged on fuselage 14 times;
(4) sensor carry 11 is arranged on 2 flight arms 13 middle part below;
(5) 2 alighting gears 12 installed be fixed on flight arm 13, make 2 alighting gears 12 be symmetricly set on fuselage 14 two outside below;
(6) 2 battery carries 10 are arranged on below alighting gear 12 respectively;
(7) 2 pieces of batteries are articulated on 2 battery carries 10 respectively;
(8) sensor is articulated on the sensor carry 11 of fuselage 14 mainboard;
(9) to take off after unmanned plane being debugged operation;
(10) after operation completes, unmanned plane landing, power-off;
(11) the sensor carry 11 of sensor from fuselage 14 is unloaded;
(12) 2 pieces of batteries are unloaded from battery carry 10;
(13) 2 battery carry 10 devices are unloaded from flight arm 13;
(14) sensor carry 11 is unloaded from flight arm 13;
(15) 2 flight arms 13 are unloaded from fuselage 14;
(16) 4 motors 2 and 4 screw propellers 3 are unloaded from 2 flight arms 13;
(17) all accessories are positioned in carrying device, namely complete flight operation.
Above-listed detailed description is illustrating for one of the utility model possible embodiments, this embodiment is also not used to limit the scope of the claims of the present utility model, allly do not depart from the equivalence that the utility model does and implement or change, all should be contained in the scope of the claims of this case.
Claims (7)
1. four rotor wing unmanned aerial vehicles, is characterized in that: comprise fuselage and two flight arms, the middle part of described flight arm is connected on described fuselage by screw, is respectively arranged with motor, is provided with screw propeller at the mouth of described motor at the two ends of described flight arm.
2. four rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: the recess offering the middle part that can hold the arm that to fly described in another on the middle part of arbitrary described flight arm.
3. four rotor wing unmanned aerial vehicles according to claim 1 and 2, is characterized in that: described two flight arms are that square crossing is fixed.
4. four rotor wing unmanned aerial vehicles according to claim 3, is characterized in that: in described flight arm, corresponding each described motor is respectively equipped with electronic governor.
5. four rotor wing unmanned aerial vehicles according to claim 4, it is characterized in that: above described fuselage, be provided with gps antenna, in described fuselage, be provided with the remote control reception module of flight control modules, wireless image transmission module, wireless digital transmission module and reception remote controller signal, below described fuselage, be connected with sensor carry by screw.
6. four rotor wing unmanned aerial vehicles according to claim 5, is characterized in that: the below outside two of described fuselage is arranged with alighting gear, under the both sides, upper end of alighting gear are connected to respectively by screw the arm that to fly described in adjacent two.
7. four rotor wing unmanned aerial vehicles according to claim 6, is characterized in that: described alighting gear is N-shaped, are connected with battery carry in the below of described alighting gear by screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520748614.8U CN205060006U (en) | 2015-09-24 | 2015-09-24 | Four -rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520748614.8U CN205060006U (en) | 2015-09-24 | 2015-09-24 | Four -rotor unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN205060006U true CN205060006U (en) | 2016-03-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520748614.8U Active CN205060006U (en) | 2015-09-24 | 2015-09-24 | Four -rotor unmanned aerial vehicle |
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| CN (1) | CN205060006U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106915435A (en) * | 2017-04-27 | 2017-07-04 | 歌尔科技有限公司 | A kind of unmanned plane |
| CN109383776A (en) * | 2017-08-02 | 2019-02-26 | 百润红科技有限公司 | H.D unmanned plane is determined with air pressure |
| CN109383775A (en) * | 2017-08-02 | 2019-02-26 | 百润红科技有限公司 | The dedicated photographic device of unmanned plane |
| CN110475719A (en) * | 2017-04-07 | 2019-11-19 | 马克·H·汉纳 | Distributed battery aircraft and its method of supplying power to |
| WO2021232703A1 (en) * | 2020-05-19 | 2021-11-25 | 广东电网有限责任公司清远供电局 | Quad-rotor unmanned aerial vehicle |
-
2015
- 2015-09-24 CN CN201520748614.8U patent/CN205060006U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110475719A (en) * | 2017-04-07 | 2019-11-19 | 马克·H·汉纳 | Distributed battery aircraft and its method of supplying power to |
| EP3606828A4 (en) * | 2017-04-07 | 2021-01-13 | Hanna, Mark Holbrook | Distributed-battery aerial vehicle and a powering method therefor |
| US11811224B2 (en) | 2017-04-07 | 2023-11-07 | Mark Holbrook Hanna | Distributed-battery aerial vehicle and a powering method therefor |
| CN106915435A (en) * | 2017-04-27 | 2017-07-04 | 歌尔科技有限公司 | A kind of unmanned plane |
| CN106915435B (en) * | 2017-04-27 | 2023-08-15 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN109383776A (en) * | 2017-08-02 | 2019-02-26 | 百润红科技有限公司 | H.D unmanned plane is determined with air pressure |
| CN109383775A (en) * | 2017-08-02 | 2019-02-26 | 百润红科技有限公司 | The dedicated photographic device of unmanned plane |
| WO2021232703A1 (en) * | 2020-05-19 | 2021-11-25 | 广东电网有限责任公司清远供电局 | Quad-rotor unmanned aerial vehicle |
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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: No. 100, Xianlie Middle Road, Guangzhou, Guangdong 510070 Patentee after: Guangzhou Institute of geography, Guangdong Academy of Sciences Address before: 510070 one of the compound No. 100, Xianlie Middle Road, Guangzhou City, Guangdong Province Patentee before: GUANGZHOU INSTITUTE OF GEOGRAPHY |