CN204660023U - Aircraft - Google Patents
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- Publication number
- CN204660023U CN204660023U CN201520280392.1U CN201520280392U CN204660023U CN 204660023 U CN204660023 U CN 204660023U CN 201520280392 U CN201520280392 U CN 201520280392U CN 204660023 U CN204660023 U CN 204660023U
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- Prior art keywords
- horn
- aircraft
- rotor
- disk assembly
- drive
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- 238000009434 installation Methods 0.000 claims abstract description 6
- 230000005540 biological transmission Effects 0.000 claims description 35
- 230000007246 mechanism Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 239000002283 diesel fuel Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000000059 patterning Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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Abstract
The aircraft that the utility model provides, comprise at least plural rotor, rotor is driven by engine installation, and engine installation is fixed on corresponding horn, and horn is connected with mainframe, and mainframe is provided with propulsion source and control setup; Be connected rotationally by driver train between horn with mainframe, the barycenter of aircraft is positioned at outside the center shaft swinging plane of rotor.This aircraft variable volume is little, turns to more flexible, fly more steady at flight course.
Description
Technical field
The utility model relates to a kind of aircraft, particularly relates to a kind of aircraft with rotor.
Background technology
Four-axle aircraft (Quadrotor) is a kind of Multi-axis aircraft of four rotors, also known as quadrotor, four-rotor helicopter, is called for short four axles, four rotors.
As shown in Figure 1, Multi-axis aircraft 100 is a kind of aircraft with four rotors 122.Multi-axis aircraft 100 has mainframe 110, be arranged on the power supply on mainframe 110, control circuit, electricity tune and erecting frame 111, every root erecting frame 111 end is respectively arranged with motor 121, and motor 121 drives the rotor 122 be fixed in motor 121 rotating shaft to rotate, thus obtains flying power.Usual rotor is evenly arranged on mainframe, so that aircraft balance controls.The direction of arrow is the hand of rotation of rotor shaft 101, and rotor shaft 101 is vertically arranged usually, and fixes with the relative position of mainframe 110, the propeller pitch angle of rotor 122 is also fixing, by changing rotating speed, the moment of torsion of propulsive force can be changed, thus control the running orbit of aircraft 100.
This Multi-axis aircraft, rotor is fixed in same working face space usually, and aircraft not only volume is large, and turns to dumb, is difficult to rapid flight in small space, turns to flight resistance larger.
Summary of the invention
It is little that main purpose of the present utility model is to provide a kind of variable volume, and turn to more flexible at flight course, fly aircraft more stably.
For realizing above-mentioned main purpose, the aircraft that the utility model provides, comprises at least plural rotor, for driving the engine installation of rotor wing rotation, for installing the horn of rotor, and the mainframe be connected with horn and control setup; Be connected rotationally by driver train between horn with mainframe, the barycenter of aircraft is positioned at outside the center shaft swinging plane of rotor.
In technique scheme, be connected rotationally between horn with mainframe, when needs carry or store, horn can be folded, reduce the volume of aircraft, make to carry and store more aspect, in addition, controlled by the rotational angle of actuating device to horn, rotor can be made to rotate at an angle, the power that rotor wing rotation produces is decomposed into a component vertically upward and a horizontal component of force, when each gyroplane rotate speed is identical, horizontal component of force is well-distributed, aircraft flight can be made more steady, and by increasing or reduce the rotating speed of a certain rotor, just can control the size of certain level component, aircraft not only can be made to obtain one and larger to turn to propulsive effort, make to turn to more flexible, and work as in outdoor flight, when there is horizontal natural wind, can by regulating the size of horizontal component of force, maintain the smooth flight of aircraft.
Preferably, the aircraft that the utility model provides, its horn drives rotor to rotate to the direction near aircraft axis under driver train drives.
In this technical scheme, horn rotates predetermined angular, and the horizontal component of force that rotor is produced points to the axis of aircraft, better ensure that the stability of aircraft.
Further, the aircraft that the utility model provides, its driver train comprises drive element and drive disk assembly; The body of drive element is fixed on mainframe, and the drive end of drive element is connected with one end of drive disk assembly, and the other end of drive disk assembly is connected with horn.
In this design plan, driver train also comprises drive disk assembly, can by the control to drive disk assembly, and the angle that horn is rotated is more accurate; In addition, drive element is arranged on mainframe, is conducive to the load alleviating horn, makes the rotation of horn more flexible.
Further, the aircraft that the utility model provides, drive disk assembly comprises the first transmission arm and the second transmission arm; One end of first transmission arm is fixedly connected with drive end, and the other end is connected with one end of the second transmission arm is rotating; The other end of the second transmission arm is connected with horn is rotating.
The drive disk assembly that this technical scheme provides, structure is simple, easy to operate, reliable.
Selectable, the aircraft that the utility model provides, drive disk assembly comprises transmission arm and sliding sleeve; One end of transmission arm is fixedly connected with drive end, and the other end is connected with sliding sleeve is rotating; Sliding sleeve is slidably socketed on horn.
This technical scheme provides the structure of another alternative drive disk assembly, according to the difference of main frame structure, can select this type of transmission device.
Selectable, the aircraft that the utility model provides, driver train comprises drive element and drive disk assembly; The body of drive element is fixed on horn, and the drive end of drive element is connected with one end of drive disk assembly, and the other end of drive disk assembly is connected with mainframe.
In this technical scheme, drive element is arranged on horn, and being conducive to the volume and the load that reduce mainframe, under specific circumstances, is a kind of alternative technology scheme.
Selectable, the aircraft that the utility model provides, drive disk assembly comprises gear mechanism; Drive end drives horn to rotate by gear mechanism; Or drive disk assembly comprises tape handler; Drive end drives horn to rotate by tape handler.
Technique scheme provides other replacement schemes alternative of transmission device, can meet the demand of different client.
Accompanying drawing explanation
Fig. 1 is four axle flying machine schematic diagrams of prior art;
Fig. 2 is the schematic diagram of the utility model aircraft first embodiment;
Fig. 3 is the front elevation of aircraft first embodiment in Fig. 2;
Fig. 4 is the schematic diagram of the utility model aircraft second embodiment.
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Detailed description of the invention
Following examples introduce in process for concrete structure or parts, only understand referential illustration of the present utility model as those skilled in the art, those skilled in the art, under the enlightenment of embodiment description technique scheme, can also to design or patterning is not exceeded the various equivalent or similar technical characteristics of the technical scope of the utility model or technical spirit.Thus, if it is unfavorable for limiting with this exemplary illustration the protection domain that the utility model claim includes.Be equal to or be similar to the protection domain that the technical solution of the utility model still belongs to the utility model claim.
First embodiment:
As shown in Figure 2, the aircraft 10 in this embodiment has four rotors 11, is respectively provided with motor 12 below each rotor 11, and motor 12 drives rotor 11 to rotate.Motor 12 is fixed on one end of horn 13, and the other end of horn 13 is connected with the mainframe 14 of " one " font is rotating.At mainframe 14, the position of horn 13 is provided with motor 15, the axle of motor 15 and one end of transmission wall 16 connect also relative fixing, to drive transmission arm 16 to rotate; The other end of transmission arm 16 is connected with sliding sleeve 17, is rotating hinged between them; Sliding sleeve 17 is socketed on horn 13, and can relatively slide by horn 13.In the present embodiment, rotor 11, motor 12, horn 13, motor 15, transmission arm 16 and sliding sleeve 17 are four.Mainframe 14 inside is provided with battery and control setup (invisible in figure), and battery is used for providing power for motor 12 and motor 15, and control setup is for the rotational angle of the rotating speed and motor 15 that control motor 12.
In the present embodiment, motor 15 can drive transmission arm 16 to rotate, transmission arm 16 drives sliding sleeve 17 to slide along horn 13, in sliding process, sliding sleeve 17 can drive horn 13 upwards to rotate, as shown in Figure 3, now, shape a in an angle between the center shaft meeting of rotor 11 and the center shaft A-A of aircraft 10, rotor 11 in rotary course, can produce one upwards, inside power F.Due to the existence of angle a, power F is decomposed into the component F2 of a component F1 upwards and level; Component F1 is the power that aircraft provides rising; And component F2 is horizontal direction, by controlling the size of angle a, can the size of level of control component F2, thus control heading and the flare maneuver of aircraft 10 rapidly.Such as, in figure 3, when aircraft 10 needs to fly left, control setup sends instruction, control the rotation larger angle of right motor 15, thus regulate right side horn 13 to rotate larger angle a by transmission arm 16 and sliding sleeve 17, like this, the horizontal component of force left that right side rotor 11 produces is comparatively large, thus promote rapidly aircraft 10 left-handed turning to.Again such as, when the angle a of four horns is identical, the size of horizontal component of force F2 is identical, now, little when the volume of aircraft 10 can be 0 compared to angle a, more easily passes through narrow space; Meanwhile, due to the existence of horizontal component of force F2, the flight of aircraft 10 also will be more steady.
In addition, the barycenter of aircraft 10 is positioned at outside the center shaft swinging plane of rotor 11, outside the plane that namely mass center of aircraft 10 center shaft that is arranged in rotor 11 is formed in rotor 11 swing process.Further, the distance between the axis that swings of rotor 11 center shaft and horn 13 is 1.1 times of rotor 11 radius to 1.5 times.
When needs storage or when carrying aircraft 10, horn 13 inwardly can be rotated to maximum angle by the driving of motor 15, now, horn 13 is in the state of being adjacent to, and the volume of aircraft 10 is minimum, is easy to carry and stores.
Second embodiment
As shown in Figure 4, the aircraft 20 of this embodiment has four rotors 21, rotor 21 drives rotation by the motor 22 below it, motor 22 is fixed on one end of horn 23, the other end of horn 23 and the mainframe 24 of similar " work " font rotating hinged, be provided with one in the middle part of mainframe 24 for installing the install bin 28 of battery and controller.Have motor 25 at four end winding support of mainframe 24, the axle of motor 25 is fixedly connected with one end of transmission arm 26, the other end of transmission arm 26 and one end of transmission arm 27 rotating hinged, the other end and the horn 23 of transmission arm 27 are rotating hinged.
In the present embodiment, motor 25 can drive transmission arm 26 to rotate, and transmission arm 26 promotes transmission arm 27 and moves up, and transmission arm 27 drives horn 13 to rotate up certain angle, thus between the center shaft making rotor 22 center shaft and aircraft 20 shape is at an angle.The operation and control method of the present embodiment is identical with the first embodiment.
In a further embodiment, transmission arm and sliding sleeve composition transmission device also can with gear mechanism or tape handler substitute; For simplified structure, the parts such as transmission arm and sliding sleeve can omit, and the anglec of rotation of horn can directly by driven by motor.
In other embodiments, rotor can also be directly installed on horn, is driven by modes such as Chain conveyer, gear transmission, V belt translation by the motor be arranged on mainframe or horn.Or, rotor is arranged on outside duct, is namely set with a duct outward at rotor.
Better, the aircraft that the utility model provides, engine installation and drive element are motor, can reduce the volume and weight of aircraft; Certainly, the combustion engine that engine installation also can be is fuel with gases such as the bunker oil such as gasoline, diesel oil or natural fuelses, because combustion engine flying power is strong, powerful, compared with being applicable to, volume is large, the aircraft of Heavy Weight.
In addition, if aircraft volume is comparatively large, heavier-weight, the motor as rotor wing rotation power also can be replaced by oil machine, and also can be replaced by motivation mechanisms such as hydraulic stems as the motor of horn rotary power.
Claims (10)
1. aircraft, comprises plural rotor, for driving the engine installation of described rotor wing rotation, for installing the horn of described rotor, and the mainframe be connected with described horn, and control setup;
It is characterized in that:
Be connected rotationally by driver train between described horn with described mainframe, the barycenter of described aircraft is positioned at outside the center shaft swinging plane of described rotor.
2. aircraft according to claim 1, is characterized in that:
Described horn drives described rotor to rotate to the direction near described aircraft axis under described driver train drives.
3. aircraft according to claim 2, is characterized in that:
Described driver train comprises drive element and drive disk assembly;
The body of described drive element is fixed on described mainframe, and the drive end of described drive element is connected with one end of described drive disk assembly, and the other end of described drive disk assembly is connected with described horn.
4. aircraft according to claim 3, is characterized in that:
Described drive disk assembly comprises the first transmission arm and the second transmission arm;
One end of described first transmission arm is fixedly connected with described drive end, and the other end is connected with one end of described second transmission arm is rotating;
The other end of described second transmission arm is connected with described horn is rotating.
5. aircraft according to claim 3, is characterized in that:
Described drive disk assembly comprises transmission arm and sliding sleeve;
One end of described transmission arm is fixedly connected with described drive end, and the other end is connected with described sliding sleeve is rotating;
Described sliding sleeve is slidably socketed on described horn.
6. aircraft according to claim 2, is characterized in that:
Described driver train comprises drive element and drive disk assembly;
The body of described drive element is fixed on described horn, and the drive end of described drive element is connected with one end of described drive disk assembly, and the other end of described drive disk assembly is connected with described mainframe.
7. the aircraft according to claim 3 or 6, is characterized in that:
Described drive disk assembly comprises gear mechanism;
Described drive end drives described horn to rotate by described gear mechanism.
8. the aircraft according to claim 3 or 6, is characterized in that:
Described drive disk assembly comprises tape handler;
Described drive end drives described horn to rotate by described tape handler.
9. the aircraft according to claim 1 to 6 any one, is characterized in that:
Duct is set with outside described rotor.
10. aircraft according to claim 7, is characterized in that:
Distance between the axis that described rotor centers axle and described horn swing is 1.1 times of described rotor radius to 1.5 times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520280392.1U CN204660023U (en) | 2015-04-30 | 2015-04-30 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520280392.1U CN204660023U (en) | 2015-04-30 | 2015-04-30 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204660023U true CN204660023U (en) | 2015-09-23 |
Family
ID=54130439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520280392.1U Expired - Fee Related CN204660023U (en) | 2015-04-30 | 2015-04-30 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204660023U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292468A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned aircraft |
| CN105292454A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned plane |
| CN105539834A (en) * | 2016-01-12 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing unmanned aerial vehicle |
| CN105564641A (en) * | 2016-01-29 | 2016-05-11 | 珠海市磐石电子科技有限公司 | Vector aircraft |
| CN106379514A (en) * | 2016-09-30 | 2017-02-08 | 深圳市高智尚创新科技有限公司 | Portable foldable multi-rotor unmanned aerial vehicle |
| CN106585967A (en) * | 2016-12-13 | 2017-04-26 | 成都聚智工业设计有限公司 | Strengthened unmanned aerial vehicle for aerial photography |
| CN106915434A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | The horn of aircraft |
| CN107826244A (en) * | 2017-11-15 | 2018-03-23 | 安徽工程大学 | A kind of six shaft rotating devices of aircraft |
| US10793270B2 (en) | 2016-05-28 | 2020-10-06 | SZ DJI Technology Co., Ltd. | Foldable UAV |
| CN113911326A (en) * | 2016-02-22 | 2022-01-11 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
-
2015
- 2015-04-30 CN CN201520280392.1U patent/CN204660023U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292454A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned plane |
| CN105292468A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned aircraft |
| CN106915434A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | The horn of aircraft |
| CN105539834A (en) * | 2016-01-12 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing unmanned aerial vehicle |
| CN105564641A (en) * | 2016-01-29 | 2016-05-11 | 珠海市磐石电子科技有限公司 | Vector aircraft |
| CN113911326A (en) * | 2016-02-22 | 2022-01-11 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| US10793270B2 (en) | 2016-05-28 | 2020-10-06 | SZ DJI Technology Co., Ltd. | Foldable UAV |
| US11124298B2 (en) | 2016-05-28 | 2021-09-21 | SZ DJI Technology Co., Ltd. | Foldable UAV |
| CN106379514A (en) * | 2016-09-30 | 2017-02-08 | 深圳市高智尚创新科技有限公司 | Portable foldable multi-rotor unmanned aerial vehicle |
| CN106379514B (en) * | 2016-09-30 | 2019-08-20 | 深圳市高智尚创新科技有限公司 | A kind of portable folding multi-rotor unmanned aerial vehicle |
| CN106585967A (en) * | 2016-12-13 | 2017-04-26 | 成都聚智工业设计有限公司 | Strengthened unmanned aerial vehicle for aerial photography |
| CN107826244A (en) * | 2017-11-15 | 2018-03-23 | 安徽工程大学 | A kind of six shaft rotating devices of aircraft |
| CN107826244B (en) * | 2017-11-15 | 2021-03-09 | 安徽工程大学 | Six rotary device of aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170424 Address after: 519000 Guangdong city of Zhuhai province Hengqin Baohua Road No. 6, room 105 -14724 Patentee after: ZHUHAI PANLEI INTELLIGENT TECHNOLOGY Co.,Ltd. Address before: 519000 Guangdong city of Zhuhai province Xiangzhou martyrs Road No. 2 Building 2 Tong En Culture Communication Co. Ltd. Patentee before: He Chunwang |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150923 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |