CN205168881U - Multiaxial flying machine - Google Patents
Multiaxial flying machine Download PDFInfo
- Publication number
- CN205168881U CN205168881U CN201520863856.1U CN201520863856U CN205168881U CN 205168881 U CN205168881 U CN 205168881U CN 201520863856 U CN201520863856 U CN 201520863856U CN 205168881 U CN205168881 U CN 205168881U
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- rotating mechanism
- electric rotating
- control module
- axis
- aircraft
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Abstract
The utility model provides a multiaxial flying machine. Multiaxial flying machine includes the main support, connects branch, power unit and slewing mechanism, connects the one end of branch and connects on the main support, the other end is connected slewing mechanism's one end, slewing mechanism's the other end and power unit are connected. The utility model discloses a set up slewing mechanism among the multiaxial flying machine between connection branch and power unit, slewing mechanism adjusts power unit's angle, and then makes the rotation plane of rotor change to reduce the windage to the influence of aircraft flight, required energy when reducing the aircraft and resisting the windage, thus reduce the electric energy that the motor consumed, can also guarantee the stabilized flight of aircraft. Further preferred, adopt the rotation plane of electronic slewing mechanism real time control adjustment rotor, guarantee that the aircraft flies more steadily. Addding wind sensor and angle sensor, controlling slewing mechanism's turned angle more accurately, the rotation plane's of rotor adjustment is more accurate.
Description
Technical field
The utility model relates to vehicle technology field, especially Multi-axis aircraft.
Background technology
Because Multi-axis aircraft structure is simple, and the control of Multi-axis aircraft is also comparatively simple, and its airworthiness is all more stable, makes Multi-axis aircraft be easy to miniaturization, and application popularization speed in recent years improves greatly.Now common Multi-axis aircraft is two axles, three axles, four axles, five axles, six axles and eight axle aircraft, also has the Multi-axis aircraft of more multiaxis.
At present, Multi-axis aircraft comprises hardware and software two parts substantially, and hardware comprises mainframe, one end of connection pole is connected on mainframe, and the other end connects actuating unit.Actuating unit generally comprises motor, rotating shaft and rotor, and rotating shaft is connected to the mouth of motor, and rotor is fixed in rotating shaft, and the plane of rotation of rotor is fixing, generally in horizontal surface.Therefore, rotor can not adjust according to the factor such as wind direction, wind-force, effectively can not utilize the extraneous power-assisteds such as wind-force in flight course.
Utility model content
The purpose of this utility model is to provide Multi-axis aircraft, and the plane of rotation solving the rotor of existing Multi-axis aircraft is fixed, the technical matters that can not change.
In order to achieve the above object, the utility model provides following technical scheme:
Multi-axis aircraft, comprise main support, connect pole, actuating unit and rotating mechanism, one end of described connection pole is connected on described main support, and the other end connects one end of described rotating mechanism; The other end of described rotating mechanism is connected with described actuating unit.
Further, described Multi-axis aircraft also comprises control module, and described rotating mechanism is electric rotating mechanism, the control end of described electric rotating mechanism and the mouth control linkage of described control module.Realize adjusting the plane of rotation of rotor in flight course.
Further, described Multi-axis aircraft also comprises wind sensor, and described wind sensor is fixed on described Multi-axis aircraft, and mouth is connected with described control module; The induction end of described wind sensor responds to wind direction in aircraft flight process and wind-force in real time, control module accepts wind direction and wind-force signal, control signal is sent to electric rotating mechanism, controls electric rotating mechanism and rotate, realize adjustment rotor wing rotation plane in real time.
Further, also comprise angular transducer, the induction end of described angular transducer is arranged on described electric rotating mechanism, and mouth is connected with described control module; The induction end of described angular transducer responds to the rotational angle of described electric rotating mechanism, when rotational angle is consistent with the rotational angle that control module exports, controls described electric rotating mechanism and stops operating.
Further, described electric rotating mechanism adopts double-axis tracking device, the control end of described double-axis tracking device and described control module control linkage.The input end of control module receive external control signal (as, the output signal of wind sensor, the control signal etc. of remote controller), control adjustment is carried out to the rotational angle of double-axis tracking device, thus drives actuating unit to rotate, and then realize the adjustment of plane of rotation of rotor.
In Multi-axis aircraft of the present utility model, rotating mechanism is set between connection pole and actuating unit, the angle of actuating unit adjusts by rotating mechanism, and then the plane of rotation of rotor is changed, to reduce the impact of windage on aircraft flight, energy required during reduction aircraft opposing windage, thus reduce the electric energy of electrical consumption, the stabilized flight of aircraft can also be ensured.Further preferably, adopt electric rotating mechanism to control to adjust the plane of rotation of rotor in real time, ensure that aircraft more stably flies.Set up wind sensor and angular transducer, control the rotational angle of rotating mechanism more accurately, the adjustment of the plane of rotation of rotor is more accurate.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of the utility model Multi-axis aircraft.
Detailed description of the invention
Below in conjunction with accompanying drawing of the present utility model, be clearly and completely described the technical solution of the utility model, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
According to Fig. 1, Multi-axis aircraft of the present utility model is described, comprise main support 1, connect pole 2, actuating unit 3 and rotating mechanism 4, one end of described connection pole 2 is connected on described main support 1, and the other end connects one end (fixed part of rotating mechanism) of described rotating mechanism 4; The other end (rotation section of rotating mechanism) of described rotating mechanism 4 is connected with described actuating unit 3.Described actuating unit 3 comprises motor 31, rotating shaft 32 and rotor 33, and rotating shaft 32 is connected to the mouth of motor 31, and rotor 33 is fixed in rotating shaft.
Described rotating mechanism 4 can adopt Manual revolving gear, as the rotating mechanism of buckle-type, actuating unit 3 is rotated relative to connection pole 2, thus changes the plane of rotation of rotor.Adjust the plane of rotation of rotor in advance according to wind direction situation before Multi-axis aircraft flight.
But wind direction and wind-force can change in flight course, therefore, in order to the plane of rotation of rotor can be adjusted in real time, the preferred technical scheme of the utility model is, described Multi-axis aircraft also comprises control module (not shown), described rotating mechanism is electric rotating mechanism, the control end of described electric rotating mechanism and the mouth control linkage of described control module.Realize adjusting the plane of rotation of rotor in flight course.Particularly, described electric rotating mechanism can adopt the structure of stepping motor driven rotary axle, realizes the rotation controlling actuating unit 3.
The rotation of described actuating unit 3 can adopt axial and/or vertical two kinds of rotation modes, arranges the rotating mechanism 3 that difference turns to.When realizing the rotation of axial and vertical both direction, rotating mechanism 3 in the utility model specifically can adopt double-axis tracking device, this double-axis tracking device is normal in solar energy photovoltaic system employing, as long as the control end of described double-axis tracking device and described control module control linkage.The input end of control module receive external control signal (as, the output signal of wind sensor, the control signal etc. of remote controller), control adjustment is carried out to the rotational angle of double-axis tracking device, thus drives actuating unit to rotate, and then realize the adjustment of plane of rotation of rotor.
Further, in order to control the adjustment angle of the plane of rotation of rotor more accurately, the utility model has also set up wind sensor (not shown), and described wind sensor is fixed on described Multi-axis aircraft, and mouth is connected with described control module; The induction end of described wind sensor responds to wind direction in aircraft flight process and wind-force in real time, control module accepts wind direction and wind-force signal, control signal is sent to electric rotating mechanism 3, controls electric rotating mechanism and rotate, realize adjustment rotor wing rotation plane in real time.
Further, in order to control the adjustment angle of the plane of rotation of rotor more accurately, the utility model has also set up angular transducer (not shown), and the induction end of described angular transducer is arranged on described electric rotating mechanism, and mouth is connected with described control module; The induction end of described angular transducer responds to the rotational angle of described electric rotating mechanism, when rotational angle is consistent with the rotational angle that control module exports, controls described electric rotating mechanism and stops operating.The rotational angle that described control module exports can manually be inputted by remote controllers, the anglec of rotation that also can be control module obtain according to wind-force and the wind direction signals of the wind sensor output received.
Multi-axis aircraft of the present utility model can be two axles of existing routine, three axles, four axles, five axles, six axles and eight axle aircraft.
The above; be only detailed description of the invention of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; change can be expected easily or replace, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should described be as the criterion with the protection domain of claim.
Claims (6)
1. Multi-axis aircraft, is characterized in that, comprise main support, connect pole, actuating unit and rotating mechanism, one end of described connection pole is connected on described main support, and the other end connects one end of described rotating mechanism; The other end of described rotating mechanism is connected with described actuating unit.
2. Multi-axis aircraft according to claim 1, is characterized in that, described Multi-axis aircraft also comprises control module, and described rotating mechanism is electric rotating mechanism, the control end of described electric rotating mechanism and the mouth control linkage of described control module.
3. Multi-axis aircraft according to claim 2, is characterized in that, described Multi-axis aircraft also comprises wind sensor, and described wind sensor is fixed on described Multi-axis aircraft, and mouth is connected with described control module; The induction end of described wind sensor responds to wind direction in aircraft flight process and wind-force in real time, control module accepts wind direction and wind-force signal, control signal is sent to electric rotating mechanism, controls electric rotating mechanism and rotate, realize adjustment rotor wing rotation plane in real time.
4. the Multi-axis aircraft according to claim 2 or 3, is characterized in that, also comprise angular transducer, and the induction end of described angular transducer is arranged on described electric rotating mechanism, and mouth is connected with described control module; The induction end of described angular transducer responds to the rotational angle of described electric rotating mechanism, when rotational angle is consistent with the rotational angle that control module exports, controls described electric rotating mechanism and stops operating.
5. Multi-axis aircraft according to claim 4, is characterized in that, described electric rotating mechanism adopts double-axis tracking device, the control end of described double-axis tracking device and described control module control linkage.
6. the Multi-axis aircraft according to claim 2 or 3, is characterized in that, described electric rotating mechanism adopts double-axis tracking device, the control end of described double-axis tracking device and described control module control linkage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520863856.1U CN205168881U (en) | 2015-10-30 | 2015-10-30 | Multiaxial flying machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520863856.1U CN205168881U (en) | 2015-10-30 | 2015-10-30 | Multiaxial flying machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168881U true CN205168881U (en) | 2016-04-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520863856.1U Expired - Fee Related CN205168881U (en) | 2015-10-30 | 2015-10-30 | Multiaxial flying machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168881U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394892A (en) * | 2016-12-07 | 2017-02-15 | 四川天辰智创科技有限公司 | Unmanned aerial vehicle |
| CN108341050A (en) * | 2017-12-06 | 2018-07-31 | 广东康云多维视觉智能科技有限公司 | A kind of multiple propeller unmanned plane |
| CN109901599A (en) * | 2017-12-09 | 2019-06-18 | 杜也兵 | The wind resistance method of unmanned helicopter and unmanned helicopter with wind-proof device |
| CN110466761A (en) * | 2019-08-22 | 2019-11-19 | 国网四川省电力公司信息通信公司 | A kind of unmanned plane and unmanned plane increase steady method |
| CN111038690A (en) * | 2019-12-03 | 2020-04-21 | 诚邦测绘信息科技(浙江)有限公司 | Multi-rotor unmanned aerial vehicle for surveying and mapping, control method and storage medium |
-
2015
- 2015-10-30 CN CN201520863856.1U patent/CN205168881U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394892A (en) * | 2016-12-07 | 2017-02-15 | 四川天辰智创科技有限公司 | Unmanned aerial vehicle |
| CN108341050A (en) * | 2017-12-06 | 2018-07-31 | 广东康云多维视觉智能科技有限公司 | A kind of multiple propeller unmanned plane |
| CN109901599A (en) * | 2017-12-09 | 2019-06-18 | 杜也兵 | The wind resistance method of unmanned helicopter and unmanned helicopter with wind-proof device |
| CN110466761A (en) * | 2019-08-22 | 2019-11-19 | 国网四川省电力公司信息通信公司 | A kind of unmanned plane and unmanned plane increase steady method |
| CN111038690A (en) * | 2019-12-03 | 2020-04-21 | 诚邦测绘信息科技(浙江)有限公司 | Multi-rotor unmanned aerial vehicle for surveying and mapping, control method and storage medium |
| CN111038690B (en) * | 2019-12-03 | 2023-01-03 | 诚邦测绘信息科技(浙江)有限公司 | Multi-rotor unmanned aerial vehicle for surveying and mapping, control method and storage medium |
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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: 20160420 Termination date: 20161030 |