CN204415723U - A kind of integrated light quadrotor - Google Patents
A kind of integrated light quadrotor Download PDFInfo
- Publication number
- CN204415723U CN204415723U CN201520057808.3U CN201520057808U CN204415723U CN 204415723 U CN204415723 U CN 204415723U CN 201520057808 U CN201520057808 U CN 201520057808U CN 204415723 U CN204415723 U CN 204415723U
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- Prior art keywords
- fuselage
- speed regulation
- brushless motor
- electronic speed
- quadrotor
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Abstract
The utility model discloses a kind of integrated light quadrotor, belong to aircraft field.Quadrotor of the present utility model, comprise fuselage, master control system, electronic speed regulation module, brushless motor and screw propeller, fuselage is PCB, and master control system is arranged on waist, four extension arms of fuselage are provided with brushless motor, brushless motor rotating shaft is provided with screw propeller; Four extension arms are also equipped with electronic speed regulation module, and each electronic speed regulation module is connected with corresponding brushless motor by the circuit on fuselage, and electronic speed regulation module is set with protective cover; In fuselage one end, wireless remote control signals transmitter is housed, the downside of fuselage is fixed with fuselage brace panel, between fuselage and fuselage brace panel, be connected with alighting gear.The utility model alleviates fuselage weight, and integrated property is better, and flying power is strong, and Signal transmissions is not subject to external interference, can real-time Transmission observation signal.
Description
Technical field
The utility model relates to vehicle technology field, more particularly, relates to a kind of integrated light quadrotor.
Background technology
Quadrotor, namely extends four arms at the fuselage centre portion of aircraft, the end difference mounted motor of each arm and the aircraft of rotor.Different from traditional helicopter, its four rotors are not coaxial, but on different four axles, therefore also referred to as four-axle aircraft.The advantage of quadrotor is, owing to there being four not coaxial rotors, so the power driven mode that can provide on mechanics is a lot.Only need the rotating speed of change four rotors, can aircraft be allowed very easily to make rising, decline, pitching, the actions such as rolling.That is, its alerting ability is very good, and mechanical structure is simple with analysis.
But mostly the modules of current quadrotor is discrete, is fixed on fuselage by the mode such as bolt or welding, and is interconnected by wire.If need aircraft to have more function, then aircraft fuselage will increase corresponding module, this will cause fuselage weight to increase, consumption of current is large, flying power is poor, and the flight time of aircraft is the necessary condition having ensured flight operation, between guarantee flight time and extended flight device function, there is contradiction always.In addition, when fuselage load is more, connect up numerous and diverse, and may mutually disturb between each module, easily break down, cause aircraft normally to work.Therefore, how effectively alleviating fuselage weight, strengthening aircraft flying power when not affecting aircraft Combination property, is a great problem that aircraft industry faces.
Through retrieval, in prior art, existing related art scheme is open, as Chinese Patent Application No.: 201410383309.3, the applying date: on August 6th, 2014, invention and created name is: a kind of miniature quadrotor based on MSP430F5310 micro controller system, this application case discloses a kind of miniature quadrotor based on MSP430F5310 micro controller system, it comprises fuselage, control circuit, motor, rotor, described motor and rotor are respectively four, be located at the corner of fuselage respectively, described fuselage is that PCB is made, described control circuit is directly installed in PCB.In the program, fuselage only has 10cm*10cm size, and fluted, the easy to use and Function Extension of the design such as hanger.Micro controller system and digital gyro and accelerometer, JTAG debugging interface etc. is connected by signal wire (SW), forms control system.Aircraft fuselage in the program is less, then carry take pictures, the words not easily rational deployment of the module such as shooting, and treater heating is comparatively large, can have an impact to surrounding devices; In addition, in the program, aircraft lacks protective device, easily breaks fuselage, need further improvement.
Utility model content
1. the utility model technical matters that will solve
The purpose of this utility model to be to overcome in prior art each module of quadrotor and line related layout is numerous and diverse, flying power is poor, be subject to the deficiency of external interference, provide a kind of integrated light quadrotor, the technical solution of the utility model, take PCB as fuselage, each module integration is installed in PCB, alleviates fuselage weight, integrated property is better, flying power is strong, and Signal transmissions is not subject to external interference, can real-time Transmission observation signal.
2. technical scheme
For achieving the above object, the technical scheme that the utility model provides is:
A kind of integrated light quadrotor of the present utility model, comprise fuselage, master control system, electronic speed regulation module, brushless motor and screw propeller, described fuselage is PCB, master control system is arranged on waist, four extension arms of fuselage are provided with brushless motor, brushless motor rotating shaft is provided with screw propeller; Four extension arms are also equipped with electronic speed regulation module, and each electronic speed regulation module is connected with corresponding brushless motor by the circuit on fuselage, and electronic speed regulation module is set with protective cover; In fuselage one end, wireless remote control signals transmitter is housed, this wireless remote control signals transmitter is electrically connected with master control system; The downside of described fuselage is fixed with fuselage brace panel, between fuselage and fuselage brace panel, be connected with alighting gear.
Further improve as the utility model, picture signal transceiver module described fuselage is equipped with, this picture signal transceiver module and wireless remote control signals transmitter are positioned at same one end, at the other end of fuselage, camera head is housed, described picture signal transceiver module and camera head are all electrically connected with master control system.
Further improve as the utility model, the treater of described master control system is stm32 treater.
Further improve as the utility model, described screw propeller is carbon fiber spiral oar.
3. beneficial effect
The technical scheme adopting the utility model to provide, compared with prior art, has following beneficial effect:
(1) a kind of integrated light quadrotor of the present utility model, take PCB as fuselage, the treater of master control system is stm32 treater, improve the self performance of aircraft, alleviate fuselage weight, and adopt carbon fiber spiral oar, during work, blade is not yielding, add work-hours, enhance flying power;
(2) a kind of integrated light quadrotor of the present utility model, master control system is arranged on waist, wireless remote control signals transmitter is installed on fuselage tail end, electronic speed regulation module is arranged on fuselage extension arm, and protective cover is set with in electronic speed regulation module, decrease the mutual interference between higher power device, ensure that the normal reception transmission of signal, adopt PCB to simplify wiring, integrated property is good;
(3) a kind of integrated light quadrotor of the present utility model, fuselage brace panel is fixed with in the downside of fuselage, add the intensity of fuselage, alighting gear is connected with between fuselage and fuselage brace panel, wearing and tearing can not be caused to fuselage in aircraft landing process, extend aircraft service life;
(4) a kind of integrated light quadrotor of the present utility model, at the tail end of fuselage, picture signal transceiver module is housed, in the front end of fuselage, camera head is housed, the shooting angle of camera head can be selected by controlling flight attitude, and picture signal is sent to ground in real time, coverage is wide, and the hover time is long, and what can realize that autonomous flight combines with manual remote control flies control pattern.
Accompanying drawing explanation
Fig. 1 is the main TV structure schematic diagram of a kind of integrated light quadrotor of the present utility model;
Fig. 2 is the side-looking structural representation of a kind of integrated light quadrotor of the present utility model.
Label declaration in schematic diagram:
1, fuselage; 2, picture signal transceiver module; 3, wireless remote control signals transmitter; 4, master control system; 5, electronic speed regulation module; 6, brushless motor; 7, screw propeller; 8, fuselage brace panel; 9, alighting gear; 10, camera head.
Detailed description of the invention
For understanding content of the present utility model further, in conjunction with the accompanying drawings and embodiments the utility model is described in detail.
Embodiment 1
Composition graphs 1 and Fig. 2, a kind of integrated light quadrotor of the present embodiment, comprise fuselage 1, master control system 4, electronic speed regulation module 5, brushless motor 6 and screw propeller 7, fuselage 1 in the present embodiment is PCB, master control system 4 is directly installed in the middle part of fuselage 1, the treater of master control system 4 is stm32 treater, obtains higher performance to make aircraft.In order to improve the horsepower output of motor, reducing wear, four extension arms of fuselage 1 being provided with brushless motor 6, brushless motor 6 rotating shaft is provided with screw propeller 7.Four extension arms are equipped with electronic speed regulation module 5, because electronic speed regulation module 5 power is larger, operationally easy other equipment to be had an impact, therefore its point is located on four extension arms, and each electronic speed regulation module 5 is connected with corresponding brushless motor 6 by the circuit on fuselage 1.In addition, electronic speed regulation module 5 is also set with protective cover, and wireless remote control signals transmitter 3 is located at fuselage 1 end, in order to avoid interference causes Signal transmissions not smooth mutually.Described fuselage 1 is also equipped with picture signal transceiver module 2, this picture signal transceiver module 2 and wireless remote control signals transmitter 3 are positioned at same one end of fuselage 1, at the other end of fuselage 1, camera head 10 is housed, described wireless remote control signals transmitter 3, picture signal transceiver module 2 are all connected by the circuit on fuselage 1 with master control system 4 with camera head 10.Can be controlled the flight attitude of aircraft by ground remote control, and then control the shooting angle of camera head 10, and picture signal is sent to ground in real time, what can realize that autonomous flight combines with manual remote control flies control pattern.
In order to strengthen the intensity of fuselage 1, the downside of fuselage 1 is fixed with fuselage brace panel 8, and this fuselage brace panel 8 be arranged in parallel with fuselage 1.Between fuselage 1 and fuselage brace panel 8, be connected with alighting gear 9, this alighting gear 9 makes to cause wearing and tearing to fuselage 1 in aircraft landing process; In addition, when alighting gear 9 lands and on two of earth surface cross bars, be set with rubber coating, vibration when can effectively reduce aircraft landing by this rubber coating, avoids the hard collision with level point, extends aircraft service life.Screw propeller 7 in the present embodiment is carbon fiber spiral oar, and during work, blade is not yielding, has higher efficiency, benefits to the lifting of overall performance.The present embodiment using PCB as fuselage 1, each module is directly installed on fuselage 1, alleviate fuselage 1 weight, ensure that the normal reception transmission of signal, and simplifying wiring in installation process, integrated property is good, and flying power is strong, and can the content of real-time monitored shooting, can be widely used in taking photo by plane, rescue, the field such as search.
Schematically above be described the utility model and embodiment thereof, this description does not have restricted, and also just one of the embodiment of the present utility model shown in accompanying drawing, actual structure is not limited thereto.So, if those of ordinary skill in the art enlightens by it, when not departing from the utility model and creating aim, design the frame mode similar to this technical scheme and embodiment without creationary, protection domain of the present utility model all should be belonged to.
Claims (4)
1. an integrated light quadrotor, comprise fuselage (1), master control system (4), electronic speed regulation module (5), brushless motor (6) and screw propeller (7), it is characterized in that: described fuselage (1) is PCB, master control system (4) is arranged on fuselage (1) middle part, four extension arms of fuselage (1) are provided with brushless motor (6), brushless motor (6) rotating shaft are provided with screw propeller (7); Electronic speed regulation module (5) four extension arms is also equipped with, each electronic speed regulation module (5) is connected with corresponding brushless motor (6) by the circuit on fuselage (1), and electronic speed regulation module (5) is set with protective cover; In fuselage (1) one end, wireless remote control signals transmitter (3) is housed, this wireless remote control signals transmitter (3) is electrically connected with master control system (4); The downside of described fuselage (1) is fixed with fuselage brace panel (8), is connected with alighting gear (9) between fuselage (1) and fuselage brace panel (8).
2. a kind of integrated light quadrotor according to claim 1, it is characterized in that: described fuselage (1) is equipped with picture signal transceiver module (2), this picture signal transceiver module (2) and wireless remote control signals transmitter (3) are positioned at same one end, at the other end of fuselage (1), camera head (10) is housed, described picture signal transceiver module (2) and camera head (10) are all electrically connected with master control system (4).
3. a kind of integrated light quadrotor according to claim 2, is characterized in that: the treater of described master control system (4) is stm32 treater.
4. a kind of integrated light quadrotor according to claim 3, is characterized in that: described screw propeller (7) is carbon fiber spiral oar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520057808.3U CN204415723U (en) | 2015-01-27 | 2015-01-27 | A kind of integrated light quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520057808.3U CN204415723U (en) | 2015-01-27 | 2015-01-27 | A kind of integrated light quadrotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204415723U true CN204415723U (en) | 2015-06-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520057808.3U Expired - Fee Related CN204415723U (en) | 2015-01-27 | 2015-01-27 | A kind of integrated light quadrotor |
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| CN (1) | CN204415723U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394893A (en) * | 2016-12-12 | 2017-02-15 | 中国民用航空飞行学院 | Multifunctional solar multi-rotor |
-
2015
- 2015-01-27 CN CN201520057808.3U patent/CN204415723U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394893A (en) * | 2016-12-12 | 2017-02-15 | 中国民用航空飞行学院 | Multifunctional solar multi-rotor |
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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: 20150624 Termination date: 20160127 |
|
| EXPY | Termination of patent right or utility model |