CN204822071U - Multi -functional coaxial bispin wing four shaft air vehicle - Google Patents
Multi -functional coaxial bispin wing four shaft air vehicle Download PDFInfo
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- CN204822071U CN204822071U CN201520469838.5U CN201520469838U CN204822071U CN 204822071 U CN204822071 U CN 204822071U CN 201520469838 U CN201520469838 U CN 201520469838U CN 204822071 U CN204822071 U CN 204822071U
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Abstract
The utility model discloses a multi -functional coaxial bispin wing four shaft air vehicle, there are four support arms on the organism, every support arm tip all has drive arrangement, drive arrangement includes the fixing base, install third motor and four Motors in the fixing base respectively, there are coaxial first axis of rotation and second axis of rotation on the fixing base, first rotation axle sleeve is outside the second axis of rotation, the first rotor of first axis of rotation top installation, second axis of rotation top installation second rotor, first rotor is opposite with second rotor direction of rotation, the first axis of rotation of output connection of third motor, four Motors's output connection second axis of rotation, the multifunction system still integrates on the aircraft. The utility model discloses an aircraft adopts coaxial bispin wing keep -It -Simple -Control system, improves bearing force, adopt solar energy power generation and wireless charging, realize superstrong continuation of the journey, the increase flight distance, integrated multiple functions are increased operation rate.
Description
Technical field
The utility model belongs to vehicle technology field, particularly multi-functional coaxial double-rotary wing four-axle aircraft.
Background technology
Four-axle aircraft is a kind of multi-rotor aerocraft the most common, and compared with single rotor craft, it can adopt less drive motor, in addition, it is one four inputs, six under-actuated systems exported, and by design Flight Control Algorithm, four-axle aircraft is controlled very well.
Also there is following problem in use in existing four-axle aircraft:
1, flight control system complexity causes algorithm complicated, and operation controls difficulty.
2, load-carrying capacity is little, and the band being difficult to meet multifunction aircraft carries demand.
3, flying power is poor, and flying distance is short.
4, function is comparatively single, maybe can only navigate etc., can not meet the multi-functional needs under harsh environment or operating mode as carried out taking photo by plane.
Utility model content
For solving deficiency of the prior art, the utility model provides multi-functional coaxial double-rotary wing four-axle aircraft, adopts coaxial double-rotary wing simplified control system, improves load-carrying capacity; Adopt solar electrical energy generation and wireless charging, realize superpower continuation of the journey, increase flying distance; Integrated several functions, increases operation rate.
For achieving the above object, the utility model is by the following technical solutions:
Multi-functional coaxial double-rotary wing four-axle aircraft, comprise the control system in body and body, described body there are four hold-down arms, all there is actuating device each hold-down arm end, described actuating device comprises permanent seat, 3rd motor and the 4th motor are installed in permanent seat respectively, permanent seat there are the first coaxial turning cylinder and the second turning cylinder, described second rotary axle box is outside the first turning cylinder, the first rotor is installed at first turning cylinder top, the second rotor is installed at second turning cylinder top, first rotor is contrary with the second rotor wing rotation direction, the output of the 3rd motor connects the second turning cylinder, the output of the 4th motor connects the first turning cylinder,
Described control system comprises core processor;
Described body there is multifunction system, comprises the range finder module, aerial transport system, pick up camera, networking permitted user system, position fixing system, temperature detecting module, emergency communication system, anti-tracking EVAC (Evacuation Network Computer Model), device of solar generating and the wireless charging device that are connected with core processor respectively;
Device of solar generating is connected with Hi cell respectively with wireless charging device, and wireless charging device is connected with base station radio.
Have two hold-down arms to be reflexibie hold-down arm in described four hold-down arms, reflexibie hold-down arm is made up of support end and strut bar, and support end one end is fixedly connected with body, and the other end is connected with strut bar is reflexibie; Turning back respectively by the first motor and the second electric machine control of two reflexibie hold-down arms.
Described range finder module is ultrasonic distance measuring module or laser ranging module.
Described aerial transport system is lifting appliance.
Described networking permitted user system comprises wireless network card, by the server of wireless connections base station.
Described position fixing system adopt in GPRS or GPS or base station or satellite one or more realize positioning function.
Described emergency communication system connects antenna, for mobile communication relaying.
Described anti-tracking EVAC (Evacuation Network Computer Model) is interference protection device, by antenna transmission interfering signal.
Contrast prior art, the beneficial effects of the utility model are:
1, the utility model adopts coaxial double-rotary wing, and coaxial double-rotary wing provides rotary power by double-motor respectively, and four axles totally eight rotors produce lift, can produce larger lift, effectively improve aircraft load capacity; Simplify flight control system simultaneously.
2, adopt solar electrical energy generation and wireless charging to charge to Hi cell, improve flying power, realize long distance, flying for long time;
3, aircraft of the present utility model is integrated with range finding, shooting, location navigation, temperature detection, internet and transportation function, is applicable to rescue and relief work, harsh environment even military, improves the degree of utilization of aircraft.
Accompanying drawing explanation
Fig. 1 is the utility model Flight Vehicle Structure schematic diagram.
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 is the multifunction system block diagram of the utility model aircraft.
In figure: 1, body; 2, hold-down arm; 4, support end; 6, the first motor; 7, the second motor; 8, strut bar; 10, the first rotor; 11, the second rotor; 12, the first rotating shaft; 13, the second rotating shaft; 14, permanent seat; 15, the 3rd motor; 16, the 4th motor; 17, under-chassis bar; 18, under-chassis; 19, the 5th motor; 20, device of solar generating; 21, wireless charging device; 22, emergency communication system; 23, antenna; 24, range finder module; 25, core processor; 26, Hi cell; 27, aerial transport system; 28, pick up camera; 29, networking permitted user system; 30, position fixing system; 31, anti-tracking EVAC (Evacuation Network Computer Model); 32, temperature detecting module, 33, base station.
Detailed description of the invention
By reference to the accompanying drawings and specific embodiment, the utility model is described in further detail.Should be understood that these embodiments are only not used in restriction scope of the present utility model for illustration of the utility model.In addition should be understood that those skilled in the art can make various changes or modifications the utility model, and these equivalent form of values fall within the application's appended claims limited range equally after the content of having read the utility model instruction.
As depicted in figs. 1 and 2, multi-functional coaxial double-rotary wing four-axle aircraft, comprise the control system in body 1 and body 1, described body 1 there is the hold-down arm that four isometric, between adjacent two hold-down arms, angle is 90 degree, all there is the actuating device of connection control system each hold-down arm end, described actuating device comprises permanent seat 14, 3rd motor 15 and the 4th motor 16 are installed in permanent seat 14 respectively, permanent seat 14 there is the first coaxial turning cylinder 12 and the second turning cylinder 13, described second turning cylinder 12 is enclosed within outside the first turning cylinder 13, the first rotor 10 is installed at first turning cylinder 12 top, the second rotor 11 is installed at second turning cylinder 13 top, first rotor 10 is contrary with the second rotor 11 hand of rotation, the output of the 3rd motor 15 connects the second turning cylinder 13, the output of the 4th motor 16 connects the first turning cylinder 12, under-chassis bar 17 and under-chassis 18 use for aircraft landing.Same hold-down arm adopt double-motor to provide rotary power, and four hold-down arms totally eight rotors generation lift, larger lift can be produced in the aircraft of same volume, effectively improve aircraft load capacity.
Described control system comprises core processor 25;
As shown in Figure 3, described body there is multifunction system, comprises the range finder module 24, aerial transport system 27, pick up camera 28, networking permitted user system 29, position fixing system 30, temperature detecting module 32, emergency communication system 22, anti-tracking EVAC (Evacuation Network Computer Model) 31, device of solar generating 20 and the wireless charging device 21 that are connected with core processor 25 respectively;
Device of solar generating 20 is connected with Hi cell 26 respectively with wireless charging device 21, wireless charging device 21 and base station 33 wireless connections.
Two hold-down arms are had to be reflexibie hold-down arm in described four hold-down arms, these two reflexibie hold-down arms are on diagonal line, reflexibie hold-down arm is made up of support end 4 and strut bar 8, and support end 4 one end is fixedly connected with body 1, and the other end is connected with strut bar 8 is reflexibie; Turning back of two reflexibie hold-down arms is controlled by the first motor 6 and the second motor 7 respectively.Two reflexibie hold-down arms for change body 1 towards, realize body cw or rotate counterclockwise, maneuvering performance is good, effectively increases the stability and control of aircraft.Adopt reflexibie hold-down arm, the approach producing moment of torsion is simple, simplifies flight control system, is beneficial to simplification Flight Control Algorithm.
Described range finder module 24 is ultrasonic distance measuring module or laser ranging module.
Described aerial transport system 27 is lifting appliance, can realize lifting and the air transport of object.
Pick up camera 28, for gathering image, realizes image recognition, keeps away barrier and video record function.
Described networking permitted user system 29 comprises wireless network card, by the server of wireless connections base station, and accessing Internet.
Described position fixing system 30 adopt in GPRS or GPS or base station 33 or satellite one or more realize positioning function, realize locating and tracking or navigation.
Described emergency communication system 22 connects antenna 23, for mobile communication relaying.
Described anti-tracking EVAC (Evacuation Network Computer Model) 31 is interference protection device, launches interfering signal by antenna 23.
Claims (8)
1. multi-functional coaxial double-rotary wing four-axle aircraft, comprise the control system in body (1) and body (1), it is characterized in that: described body (1) has four hold-down arms, all there is actuating device each hold-down arm end, described actuating device comprises permanent seat (14), 3rd motor (15) and the 4th motor (16) are installed in permanent seat (14) respectively, permanent seat (14) there are coaxial the first turning cylinder (12) and the second turning cylinder (13), described second turning cylinder (13) is enclosed within the first turning cylinder (12) outward, the first rotor (10) is installed at first turning cylinder (12) top, the second rotor (11) is installed at second turning cylinder (13) top, first rotor (10) is contrary with the second rotor (11) hand of rotation, the output of the 3rd motor (15) connects the second turning cylinder (13), the output of the 4th motor (16) connects the first turning cylinder (12),
Described control system comprises core processor (25);
(1) has multifunction system to described body, comprises the range finder module (24), aerial transport system (27), pick up camera (28), networking permitted user system (29), position fixing system (30), temperature detecting module (32), emergency communication system (22), anti-tracking EVAC (Evacuation Network Computer Model) (31), device of solar generating (20) and the wireless charging device (21) that are connected with core processor (25) respectively;
Device of solar generating (20) is connected with Hi cell (26) respectively with wireless charging device (21), wireless charging device and base station (33) wireless connections.
2. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, it is characterized in that: in described four hold-down arms, have two hold-down arms to be reflexibie hold-down arm, reflexibie hold-down arm is made up of support end (4) and strut bar (8), support end (4) one end is fixedly connected with body (1), and the other end is connected with strut bar (8) is reflexibie; Turning back of two reflexibie hold-down arms is controlled by the first motor (6) and the second motor (7) respectively.
3. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described range finder module (24) is ultrasonic distance measuring module or laser ranging module.
4. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described aerial transport system (27) is lifting appliance.
5. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described networking permitted user system (29) comprises wireless network card, by the server of wireless connections base station.
6. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described position fixing system (30) adopt in GPRS or GPS or base station (33) or satellite one or more realize positioning function.
7. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described emergency communication system (22) connects antenna (23), for mobile communication relaying.
8. multi-functional coaxial double-rotary wing four-axle aircraft according to claim 1, is characterized in that: described anti-tracking EVAC (Evacuation Network Computer Model) (31) is interference protection device, launches interfering signal by antenna (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520469838.5U CN204822071U (en) | 2015-07-03 | 2015-07-03 | Multi -functional coaxial bispin wing four shaft air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520469838.5U CN204822071U (en) | 2015-07-03 | 2015-07-03 | Multi -functional coaxial bispin wing four shaft air vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204822071U true CN204822071U (en) | 2015-12-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520469838.5U Expired - Fee Related CN204822071U (en) | 2015-07-03 | 2015-07-03 | Multi -functional coaxial bispin wing four shaft air vehicle |
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| CN (1) | CN204822071U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104943858A (en) * | 2015-07-03 | 2015-09-30 | 广西大学 | Multifunctional coaxial double-rotor-wing four-shaft aircraft |
| WO2017215200A1 (en) * | 2016-06-17 | 2017-12-21 | 深圳市元征科技股份有限公司 | Wirelessly-chargeable unmanned aerial vehicle |
| CN109154815A (en) * | 2017-11-30 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Maximum temperature point-tracking method, device and unmanned plane |
-
2015
- 2015-07-03 CN CN201520469838.5U patent/CN204822071U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104943858A (en) * | 2015-07-03 | 2015-09-30 | 广西大学 | Multifunctional coaxial double-rotor-wing four-shaft aircraft |
| WO2017215200A1 (en) * | 2016-06-17 | 2017-12-21 | 深圳市元征科技股份有限公司 | Wirelessly-chargeable unmanned aerial vehicle |
| CN109154815A (en) * | 2017-11-30 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Maximum temperature point-tracking method, device and unmanned plane |
| US11153494B2 (en) | 2017-11-30 | 2021-10-19 | SZ DJI Technology Co., Ltd. | Maximum temperature point tracking method, device and unmanned aerial vehicle |
| US11798172B2 (en) | 2017-11-30 | 2023-10-24 | SZ DJI Technology Co., Ltd. | Maximum temperature point tracking method, device and 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151202 Termination date: 20160703 |