CN203623975U - Improved aircraft - Google Patents
Improved aircraft Download PDFInfo
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- CN203623975U CN203623975U CN201420009376.4U CN201420009376U CN203623975U CN 203623975 U CN203623975 U CN 203623975U CN 201420009376 U CN201420009376 U CN 201420009376U CN 203623975 U CN203623975 U CN 203623975U
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- drive mechanism
- load
- control circuit
- circuit device
- aircraft
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Abstract
The utility model discloses an improved aircraft. The improved aircraft comprises a load and a flight host body. The improved aircraft further comprises at least two adjustment devices and a control circuit device, wherein at least two telescopic rods are arrayed on the outer sidewall of the load and around the axial circumference thereof, and each of the adjustment devices comprises a lifting drive mechanism and a rotating drive mechanism; the lifting drive mechanism comprises a lifting rod provided with a joint bearing at the lower end, and the free ends of the telescopic rods are installed in the joint bearings of the corresponding lifting rods; the control circuit device is used for controlling the working states of the lifting drive mechanism and the rotating drive mechanism. The improved aircraft disclosed by the utility model is capable of adjusting the attitude of the load by virtue of the design of the lifting drive mechanism and the rotating drive mechanism, driving the load to rotate by virtue of the rotating drive mechanism so as to meet the needs of different working states of the load, maintaining the load in a horizontal state by virtue of the cooperation between the detection device and the control circuit device, and improving the working effect of the load.
Description
Technical field
The utility model relates to a kind of aircraft that improves.
Background technology
Aircraft is usually used in being with dynamic load to fly, with can high-efficient homework.For example, described load can be illumination equipment, control monitor unit or atomising installation etc., thereby can realize illumination, high-altitude monitoring, high-altitude spraying etc. on a large scale.But in the different mode of operation of load, in order to reach preferably working effect, described load need adopt different attitudes, for example be the level of state or heeling condition, but because this load is directly fixed on flight main body, cannot regulate the attitude of load, thereby affect its working effect.
Utility model content
In order to overcome the deficiencies in the prior art, the purpose of this utility model is to provide a kind of aircraft that improves, and it can regulate the attitude of load.
For addressing the above problem, the technical scheme that the utility model adopts is as follows:
A kind of aircraft that improves, comprises,
Load;
Flight main body;
This improvement aircraft also comprises,
At least two control apparatuss, show at least two expansion links around its axis circumferential row on the lateral wall of load, and the quantity of described control apparatus equates with the quantity of expansion link, and corresponding one by one; Described control apparatus comprises lift drive mechanism, is connected to the rotating drive mechanism on flight main body and for driving lift drive mechanism to rotate; Described lift drive mechanism comprises that lower end is provided with the lifting bar of oscillating bearing, and the free end of described expansion link is arranged in the oscillating bearing of corresponding lifting bar;
Control circuit device, for controlling the mode of operation of lift drive mechanism and rotating drive mechanism.
This improvement aircraft also comprises detecting device, and described detecting device is for detection of the deflection angle of load, and generates deflection wave and be sent to control circuit device; The deflection wave control lift drive mechanism that control circuit device provides according to detecting device and the mode of operation of rotating drive mechanism.
Described detecting device is obliquity sensor or the horizon sensor being arranged in load.
It is outer and be the rotor flying mechanism of circumferential arrangement that flight main body comprises that even number is looped around control circuit device; In each rotor flying mechanism, be provided with connecting arm, and be connected on control circuit device by this connecting arm; The quantity of described rotor flying mechanism equates with the quantity of control apparatus, and corresponding one by one; Described rotating drive mechanism is connected on corresponding connecting arm.
Described rotor flying mechanism comprises rotor, drive motor for driving rotor to rotate.
The lower end of described lifting bar is connected on the outer ring of oscillating bearing, and described expansion link is arranged in the inner ring of oscillating bearing.
Described load is illumination equipment and/or control monitor unit.
Lift drive mechanism is linear electric motors, the output shaft that described lifting bar is linear electric motors.
Rotating drive mechanism is a rotating machine, and the lower end of the rotating shaft of described rotating machine is connected with lift drive mechanism.
Each rotating drive mechanism synchronously rotates under the control action of control circuit device.
Compared to existing technology, the beneficial effects of the utility model are:
The utility model is by adopting the design of lift drive mechanism, rotating drive mechanism, can utilize different lift drive mechanisms to regulate the height of corresponding expansion link, by extremely different heeling condition or horizontalitys etc. of load adjustment, thereby can regulate the attitude of load; Meanwhile, also can utilize the dynamic load of rotating drive mechanism band to rotate, to meet the demand of different operating state of load; And, also can, by the cooperation of detecting device and control circuit device, load be maintained to horizontality, can improve the working effect of load; And its simple in structure, reliable working performance, is conducive to promote.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Wherein, 1, load; 2, rotor flying mechanism; 21, rotor; 22, drive motor; 3, control apparatus; 31, lift drive mechanism; 32, rotating drive mechanism; 33, expansion link; 34, oscillating bearing; 4, control circuit device.
The specific embodiment
Below, by reference to the accompanying drawings and the specific embodiment, the utility model is described further, understands the utility model technical thought required for protection so that clearer.
As shown in Figure 1, for a kind of aircraft that improves of the present utility model, comprise,
Load 1;
Flight main body, it is for being with the flight such as dynamic load 1, control apparatus 3;
This improvement aircraft also comprises,
At least two control apparatuss 3, show at least two expansion links 33 around its axis circumferential row on the lateral wall of load 1, and the quantity of described control apparatus 3 equates with the quantity of expansion link 33, and corresponding one by one; Described control apparatus 3 comprises lift drive mechanism 31, is connected to the rotating drive mechanism 32 on flight main body and for driving lift drive mechanism 31 to rotate; Described lift drive mechanism 31 is positioned at the below of rotating drive mechanism 32; Described lift drive mechanism 31 comprises that lower end is provided with the lifting bar of oscillating bearing 34, and the free end of described expansion link 33 is arranged in the oscillating bearing 34 of corresponding lifting bar; Concrete, the lower end of described lifting bar is connected on the outer ring of oscillating bearing 34, and described expansion link 33 is arranged in the inner ring of oscillating bearing 34.
Control circuit device 4, for controlling the mode of operation of lift drive mechanism 31 and rotating drive mechanism 32.Concrete, each rotating drive mechanism 32 synchronously rotates under the control action of control circuit device 4.
Preferably, this improvement aircraft also comprises detecting device, and described detecting device is for detection of the deflection angle of load 1, and generates deflection wave and be sent to control circuit device 4; The deflection wave control lift drive mechanism 31 that control circuit device 4 provides according to detecting device and the mode of operation of rotating drive mechanism 32.Described detecting device can be the obliquity sensor or the horizon sensor that are arranged in load 1, or other known devices for detection of deflection angle.In use, control circuit device 4 can be controlled lift drive mechanism 31 and rotating drive mechanism 32 according to the current deflection angle state of load 1, thereby load 1 is adjusted to various attitudes.Wherein, it can be level attitude that control circuit device 4 is set for the normal place of load 1, i.e. load 1 is parallel with horizontal surface all the time, also can be set as keeping certain angle with horizontal surface.
In use, can utilize different lift drive mechanism 31 to regulate the height of corresponding expansion link 33, load 1 is adjusted to different heeling condition or horizontality etc., thereby can regulate the attitude of load 1, and, also can utilize rotating drive mechanism 32 to drive lift drive mechanism 31 to rotate, now, expansion link 33 carries out beat and flexible under the induced effect of lifting bar, thus band dynamic load 1 rotate, to meet the demand of different operating state of load 1; In the course of the work, can also utilize the deflection angle of detecting device inductive load 1 and reference level surface, and deflection wave is fed back to control circuit device 4, afterwards, control circuit device 4 controls rotating drive mechanism 32 and lift drive mechanism 31 is worked, load 1 can be maintained to horizontality, to improve the working effect of load 1.
Wherein, described flight main body can adopt existing structure.Preferably, to comprise that even number is looped around control circuit device 4 outer and be the rotor flying mechanism 2 of circumferential arrangement for flight main body.In each rotor flying mechanism 2, be provided with connecting arm, and be connected on control circuit device 4 by connecting arm, the quantity of described rotor flying mechanism 2 equates with the quantity of control apparatus 3, and corresponding one by one; Described rotating drive mechanism 32 is connected on corresponding connecting arm.By adopting said structure, can be convenient to make, assemble, be conducive to reduce cost of manufacture.Wherein, the quantity of described rotor flying mechanism 2 can be set according to actual demand, and preferred, and this improvement aircraft comprises four rotor flying mechanisms 2, four control apparatuss 3, can, in the case of guaranteeing to improve the serviceability of aircraft, can also effectively control cost of manufacture.
Preferably, described rotor flying mechanism 2 comprises rotor 21, drive motor 22 for driving rotor 21 to rotate; Concrete, the output shaft of described drive motor 22 is fixedly inserted on the middle part of rotor 21.
Preferably, lift drive mechanism 31 is linear electric motors, the output shaft that described lifting bar is linear electric motors.Certainly, described lift drive mechanism 31 can also adopt the cooperation of motor, screw mandrel, nut to realize its elevating function, but lift drive mechanism 31 is set to linear electric motors, can simplify its fitting process, reduces assembly cost.
Preferably, rotating drive mechanism 32 is a rotating machine, and the lower end of the rotating shaft of described rotating machine is connected with lift drive mechanism 31.
Wherein, described expansion link 33 adopts existing structure, for example, comprises outer tube, the flexible inner tube of outer tube relatively.
Wherein, described load 1 can, according to actual demand, adopt illumination equipment, control monitor unit, atomising installation, or any cooperation of this three etc., to realize various functions etc.
Above-mentioned embodiment is only preferred implementation of the present utility model; the scope that can not limit with this utility model protection, the variation of any unsubstantiality that those skilled in the art does on basis of the present utility model and replacement all belong to the utility model scope required for protection.
Claims (10)
1. an improvement aircraft, comprises,
Load;
Flight main body;
It is characterized in that: this improvement aircraft also comprises,
At least two control apparatuss, show at least two expansion links around its axis circumferential row on the lateral wall of load, and the quantity of described control apparatus equates with the quantity of expansion link, and corresponding one by one; Described control apparatus comprises lift drive mechanism, is connected to the rotating drive mechanism on flight main body and for driving lift drive mechanism to rotate; Described lift drive mechanism comprises that lower end is provided with the lifting bar of oscillating bearing, and the free end of described expansion link is arranged in the oscillating bearing of corresponding lifting bar;
Control circuit device, for controlling the mode of operation of lift drive mechanism and rotating drive mechanism.
2. improvement aircraft as claimed in claim 1, is characterized in that: this improvement aircraft also comprises detecting device, and described detecting device is for detection of the deflection angle of load, and generates deflection wave and be sent to control circuit device; The deflection wave control lift drive mechanism that control circuit device provides according to detecting device and the mode of operation of rotating drive mechanism.
3. improvement aircraft as claimed in claim 2, is characterized in that: described detecting device is obliquity sensor or the horizon sensor being arranged in load.
4. improvement aircraft as claimed in claim 1, is characterized in that: it is outer and be the rotor flying mechanism of circumferential arrangement that flight main body comprises that even number is looped around control circuit device; In each rotor flying mechanism, be provided with connecting arm, and be connected on control circuit device by this connecting arm; The quantity of described rotor flying mechanism equates with the quantity of control apparatus, and corresponding one by one; Described rotating drive mechanism is connected on corresponding connecting arm.
5. improvement aircraft as claimed in claim 4, is characterized in that: described rotor flying mechanism comprises rotor, drive motor for driving rotor to rotate.
6. improvement aircraft as claimed in claim 1, is characterized in that: the lower end of described lifting bar is connected on the outer ring of oscillating bearing, and described expansion link is arranged in the inner ring of oscillating bearing.
7. improvement aircraft as claimed in claim 1, is characterized in that: described load is illumination equipment and/or control monitor unit.
8. improvement aircraft as claimed in claim 1, is characterized in that: lift drive mechanism is linear electric motors, the output shaft that described lifting bar is linear electric motors.
9. improvement aircraft as claimed in claim 1, is characterized in that: rotating drive mechanism is a rotating machine, and the lower end of the rotating shaft of described rotating machine is connected with lift drive mechanism.
10. improvement aircraft as claimed in claim 1, is characterized in that: each rotating drive mechanism synchronously rotates under the control action of control circuit device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420009376.4U CN203623975U (en) | 2014-01-01 | 2014-01-01 | Improved aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420009376.4U CN203623975U (en) | 2014-01-01 | 2014-01-01 | Improved aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203623975U true CN203623975U (en) | 2014-06-04 |
Family
ID=50810474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420009376.4U Expired - Fee Related CN203623975U (en) | 2014-01-01 | 2014-01-01 | Improved aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203623975U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691600A (en) * | 2015-12-31 | 2016-06-22 | 重庆楠婧琳科技开发有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107539464A (en) * | 2017-07-20 | 2018-01-05 | 袁锦红 | A kind of agricultural fog machine |
| CN107662706A (en) * | 2016-07-28 | 2018-02-06 | 深圳航天旭飞科技有限公司 | Deinsectization unmanned plane |
-
2014
- 2014-01-01 CN CN201420009376.4U patent/CN203623975U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691600A (en) * | 2015-12-31 | 2016-06-22 | 重庆楠婧琳科技开发有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107662706A (en) * | 2016-07-28 | 2018-02-06 | 深圳航天旭飞科技有限公司 | Deinsectization unmanned plane |
| CN107539464A (en) * | 2017-07-20 | 2018-01-05 | 袁锦红 | A kind of agricultural fog machine |
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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: 20140604 Termination date: 20200101 |