CN204548494U - Five axle aircraft - Google Patents
Five axle aircraft Download PDFInfo
- Publication number
- CN204548494U CN204548494U CN201520237212.1U CN201520237212U CN204548494U CN 204548494 U CN204548494 U CN 204548494U CN 201520237212 U CN201520237212 U CN 201520237212U CN 204548494 U CN204548494 U CN 204548494U
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- center
- rotor
- deflecting plate
- unit
- sidespin wing
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- 238000005096 rolling process Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 8
- 238000009434 installation Methods 0.000 description 7
- 230000005611 electricity Effects 0.000 description 2
- 230000005021 gait Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
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Abstract
The utility model relates to a kind of five axle aircraft, and it comprises frame and 4 sidespin wing unit of the center rotor unit that is installed in frame and the periphery that is distributed in center rotor unit; Center rotor unit comprises center rotor, and sidespin wing unit comprises the sidespin wing, and the quantity of center rotor and the sidespin wing is one; Turning to of the sidespin wing of two sidespin wing unit positioned opposite is identical, and turning to of the sidespin wing of the sidespin wing unit of adjacent layout is contrary.This aircraft, when the actuating device of center rotor unit breaks down and stops, can, by the rotating speed of the rotor of adjustment 4 sidespin wing unit, prevent aircraft from occurring rolling aloft, improve the flight safety performance of aircraft.
Description
Technical field
The utility model relates to a kind of Multi-axis aircraft, specifically, relates to a kind of five axle aircraft.
Background technology
Multi-axis aircraft, generally includes frame and the control unit that is installed in frame and plural rotor unit.The rotor that rotor unit generally includes engine installation and driven by this engine installation, the angle of the blade of its rotor is definite value, in flight course, is adjusted the flight attitude of aircraft by the relative rotation speed changed between different rotor.Control unit generally includes detecting sensor, control circuit board and electricity and adjusts, and electricity calls the rotating speed in adjustment rotor; Control unit is used for the flight attitude of sense aircraft and regulation and control engine installation to control the attitude of advancing of aircraft, direct of travel and gait of march etc.
Publication No. is disclose a kind of many rotor unmanned aircrafts in the patent documentation of CN103625640A, it comprises fuselage, the center of fuselage is provided with center duct unit, the periphery of this center duct unit is evenly equipped with the flight support arm of more than 3 radially, the center rotor that center duct unit comprises center rotor motor and is connected with the output shaft of center rotor motor, center rotor motor is fixedly installed in the center of fuselage, each flight support arm is all provided with periphery rotor unit, the periphery rotor that this periphery rotor unit comprises periphery rotor motor and is connected with the output shaft of periphery rotor motor, periphery rotor motor is installed on flight support arm, the size of center rotor is greater than the size of periphery rotor, turning to of center rotor is contrary with turning to of periphery rotor.Because the hand of rotation of the periphery rotor of this multi-rotor aerocraft is contrary with the hand of rotation of center rotor, the reactive torque that the reactive torque that periphery rotor wing rotation produces produces for offsetting center rotor wing rotation, enables this aircraft hover aloft, stable and reliable.But when center rotor motor occurs stopping due to fault, whole aircraft, by constantly rolling aloft, easily causes crash.
Summary of the invention
Main purpose of the present utility model is to provide five high axle aircraft of a kind of safety.
In order to realize above-mentioned main purpose, the utility model provides a kind of five axle aircraft, and it comprises frame and 4 sidespin wing unit of the center rotor unit that is installed in frame and the periphery that is distributed in center rotor unit; Center rotor unit comprises center rotor, and sidespin wing unit comprises the sidespin wing, and the quantity of center rotor and the sidespin wing is one; The rotation direction of the sidespin wing of two sidespin wing unit positioned opposite is identical, namely two rotors positioned opposite are all left-handed rotor or are all dextrorotation rotor, the rotation direction of the sidespin wing of two sidespin wing unit of adjacent layout is contrary, i.e. a left-handed rotor, another is dextrorotation rotor.
From above scheme, by adjusting the rotating speed of 4 sidespin wings, thus the total reactive torque making 4 side rotor wing rotations produce can be used for the reactive torque that counteracting center rotor wing rotation produces, when the actuating device of center rotor unit occurs stopping because of fault, by adjusting the rotating speed of 4 sidespin wings, the reactive torque that 4 sidespin wings are produced is cancelled out each other, thus ensure aircraft can not because of centered by the parking of rotor unit and rolling aloft, improve the flight safety performance of this aircraft.
Centered by concrete scheme, the plane of rotation of rotor is higher than the plane of rotation of the sidespin wing.This can reduce the interference in air flow between center rotor and the sidespin wing, improves pneumatic efficiency.
A preferred scheme is that sidespin wing unit also comprises the side duct be installed in frame, and the sidespin wing is placed in this side duct, the axis of the sidespin wing and the center line conllinear of side duct.Side duct provides periphery to protect for the sidespin wing and provides guiding for its downwash flow.
Centered by preferred scheme, rotor unit also comprises the center duct on installation frame, in the rotor centering duct of center, and the axis of center rotor and the center line conllinear of this center duct.Centered by the duct of center, rotor provides peripheral protection and provides guiding for its downwash flow.
Preferred scheme is for also to comprise reactive torque control unit and control unit of advancing again; Wherein, reactive torque control unit comprises the first deflecting plate and second deflecting plate at the lower lip place being located at center duct, the first deflecting plate S. A. that the center line of the first deflecting plate and the second deflecting plate Ke Raoyu center duct is respectively orthogonal rotates, and the first deflecting plate and the second deflecting plate are arranged symmetrically with about the median centre of center duct; Control unit of advancing comprises the 3rd deflecting plate at the lower lip place being located at center duct, and the second deflecting plate S. A. that the center line of the 3rd deflecting plate Ke Raoyu center duct is orthogonal rotates.Be convenient to aircraft roll dress and direct of travel control.
Centered by another preferred scheme, rotor unit also comprises the center duct on installation frame, the center line conllinear of the spin axis Xian Yugai center duct of center rotor, in the rotor centering duct of center.
Centered by preferred scheme, the oar footpath of rotor equals the oar footpath of the sidespin wing.
Centered by another preferred scheme, the propeller pitch angle of rotor is greater than the propeller pitch angle of the sidespin wing.
Centered by another preferred scheme, the blade quantity of rotor is greater than the blade quantity of the sidespin wing.
Another preferred scheme be the axes intersect of the axis of the sidespin wing and center rotor in same intersection point, this intersection point is positioned at the top of center rotor.
Accompanying drawing explanation
Fig. 1 is the block diagram of the utility model first embodiment;
Fig. 2 is the front view of the utility model first embodiment;
Fig. 3 is the rotation direction schematic diagram of the utility model first embodiment each rotor in flight course;
Fig. 4 is the block diagram of the utility model second embodiment;
Fig. 5 is the block diagram of the utility model the 3rd embodiment;
Fig. 6 is the STRUCTURE DECOMPOSITION figure of the utility model the 3rd embodiment;
Fig. 7 is the block diagram of sidespin wing unit connecting element in the utility model the 3rd embodiment;
Fig. 8 is the block diagram of reactive torque control unit in the utility model the 3rd embodiment;
Fig. 9 is the block diagram of control unit of advancing in the utility model the 3rd embodiment;
Figure 10 is the relative position schematic diagram of the second deflecting plate S. A. and the 3rd deflecting plate in the utility model the 4th embodiment.
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Detailed description of the invention
First embodiment
See Fig. 1, aircraft 1 is made up of frame 10, center rotor unit 11, first sidespin wing unit 12, second sidespin wing unit 13, first sidespin wing unit 14, second sidespin wing unit 15, power supply, control unit and installation storehouse 101, and power supply and control unit are located at and are installed in storehouse 101; Frame 10 is a cross-shaped configuration, and by mounting center and from mounting center to extension, 4 raw hold-down arms are formed.Center rotor unit 11 is made up of centre-driven motor 112 and the center rotor 111 that driven by centre-driven motor 112, first sidespin wing unit 12 is made up of the first drive motor 122 and the first sidespin wing 121 that driven by the first drive motor 122, second sidespin wing unit 13 is made up of the second drive motor 132 and the second sidespin wing 131 that driven by the second drive motor 132, first sidespin wing unit 14 is made up of the first drive motor 142 and the first sidespin wing 141 that driven by the first drive motor 142, second sidespin wing unit 15 is made up of the second drive motor 152 and the second sidespin wing 151 that driven by the second drive motor 152.Center rotor unit 11 and installation storehouse 101 are installed on the mounting center place of frame 10, center rotor unit 11 is positioned to be installed directly over storehouse 101, four sidespin wing unit are installed on the free end of four hold-down arms successively, thus make the first sidespin wing unit 12, second sidespin wing unit 13, first sidespin wing unit 14 and the second sidespin wing unit 15 be distributed in the periphery of center rotor unit 11 successively.The plane of revolution of the first sidespin wing 121, the second sidespin wing 131, the first sidespin wing 141 and the second sidespin wing 151 is coplanar and the oar footpath of four is identical.Be positioned at the below of the first sidespin wing unit 12,14, second sidespin wing unit 13,15, the free end of four hold-down arms be provided with strut bar 102 successively, when aircraft 1 lands, aircraft 1 be supported in ground.
See Fig. 2, the plane of revolution of center rotor 111 is positioned at the top of the plane of revolution of the first sidespin wing 121 and the oar footpath of the two is identical.The plane of revolution of rotor is the plane that the blade root mid point in the axial direction of its blade is formed in rotary course.
See Fig. 3, aircraft 1 is in flight course, center rotor 111, the first sidespin wing 121 and the first sidespin wing 141 are around its S. A. clickwise, and the second sidespin wing 131 and the second sidespin wing 151 are around its S. A. left-hand revolution, are aircraft 1 and provide lift.The rotating speed of the second sidespin wing is higher than the rotating speed of the first sidespin wing, and total reactive torque that the second sidespin wing and the first sidespin wing produce in rotary course offsets center rotor 111 because rotating the reactive torque produced by being used for.
Second embodiment
As the explanation to the utility model second embodiment, only the difference with above-mentioned first embodiment is described below.
See Fig. 4, the first sidespin wing 221,241, the second sidespin wing 231,251 of aircraft 2 and the plane of revolution of center rotor 211 coplanar.
3rd embodiment
See Fig. 5 and Fig. 6, aircraft 3 is by frame, and power supply, control unit, center rotor unit, reactive torque control unit 14, advance control unit 15 and 4 sidespin wing unit are formed.Center rotor unit is made up of the center rotor 311 in center duct 30 and centering duct 30 and drive motor thereof; 4 sidespin wing unit are the first sidespin wing unit 32, second sidespin wing unit 33, first sidespin wing unit 34 and the second sidespin wing unit 35 being distributed in center duct 30 periphery equably, sidespin wing unit is formed by side duct and the rotor be placed in the duct of side and drive motor, centrally the axis of rotor 311 is from up to down overlooked, first rotor of sidespin wing unit 32,34 and turning to as conter clockwise of center rotor 311, and the rotor of the second sidespin wing unit 33,35 turn to as cw; Center duct 30 internal fixtion has a cross mounting bracket 302, and the drive motor of center rotor 311 is installed on mounting bracket 302 by fixed support, the axis of center rotor 311 and the center line conllinear of center duct 30; First sidespin wing unit 32,34 and second sidespin wing unit 33,35 is fixed on the lateral wall of center duct 30 respectively by sidespin wing unit connecting element 301; The fixed support of mounting bracket 302, drive motor and sidespin wing unit connecting element 301 form the frame of the present embodiment.
See Fig. 7, sidespin wing unit connecting element 301, by can two semicircular cylinders 3011 of folding form, semicircular cylinder 3011 is welded with the fixed support 30110 for being fixed on by sidespin wing unit connecting element 301 on the lateral wall of center duct 30.
See Fig. 8, reactive torque control unit 36 is by two first deflecting plate S. A.s 3601,3602, and two piece of first deflecting plate 361,362, two piece of second deflecting plate 363,364, two first connecting rods 365 and two first connecting rods 366 are formed.First deflecting plate S. A. 3601 and the first deflecting plate S. A. 3602 are fixed on the lower lip place of center duct 30 abreast, first deflecting plate S. A. 3601 and the first deflecting plate S. A. 3602 are arranged symmetrically with about the median centre of center duct 30, first deflecting plate 361 and the second deflecting plate 363 can be installed on the first deflecting plate S. A. 3601 around the first deflecting plate S. A. 3601 rotatably, first deflecting plate 362 and the second deflecting plate 364 can be installed on the first deflecting plate S. A. 3602 around the first deflecting plate S. A. 3602 rotatably, two first connecting rods 365 are connected on the two ends of the first deflecting plate 361 and the first deflecting plate 362, the two is made to rotate around the first deflecting plate S. A. with same rotating speed, two first connecting rods 366 are connected on the two ends of the second deflecting plate 363 and the second deflecting plate 364, the two is made to revolve around the first deflecting plate S. A. with same rotating speed.First deflecting plate 361 and the second deflecting plate 364 are arranged symmetrically with about the median centre of center duct 30, first deflecting plate 362 and the second deflecting plate 363 are arranged symmetrically with about the median centre of center duct 30, thus the first deflecting plate and the second deflecting plate are arranged symmetrically with about the median centre of center duct 30.Aircraft 3 is in flight course, centrally the axis of rotor 311 is from up to down overlooked, center rotor 311 is around its S. A. left-hand revolution, by the orientation mode of the first deflecting plate and the second deflecting plate in adjustment reactive torque control unit 36, to reach the adjustment to aircraft 3 roll mode in flight course, namely control the lower end of the first deflecting plate 361,362 respectively around the first deflecting plate S. A. 3601,3602 rotating forward towards Y-axis by control unit; The lower end of the second deflecting plate 363,364 rotates with the negative sense of equal rotating speed along Y-axis around the first deflecting plate S. A. 3601,3602 respectively simultaneously, the reactive torque size that the size of the anglec of rotation is offset as required and determining, thus can the roll attitude of aircraft 3 be adjusted; If aircraft 3 needs to move towards a direction, the reactive torque that only need be produced on aircraft 3 by adjustment reactive torque control unit makes aircraft 3 rotate an angle to around the center line of center duct 30 the normal direction projection in the horizontal plane that this direction is the 3rd deflecting plate 371.
See Fig. 9, control unit 37 of advancing is made up of two second deflecting plate S. A.s, 3701,3702, two piece of the 3rd deflecting plate, 371,372 and two third connecting rods 373.3rd deflecting plate 371 can be installed on the second deflecting plate S. A. 3701 around the second deflecting plate S. A. 3701 rotatably, 3rd deflecting plate 372 can be installed on the second deflecting plate S. A. 3702 around the second deflecting plate S. A. 3702 rotatably, two third connecting rods 373 are connected to the two ends of the 3rd deflecting plate 371 and the 3rd deflecting plate 372, make the two rotate around the second deflecting plate S. A. with same rotating speed.Second deflecting plate S. A. 3701,3702 is arranged symmetrically with about the median centre of center duct 30, and the 3rd deflecting plate 371,372 is arranged symmetrically with about the median centre of center duct 30.For the control of the gait of march of aircraft 3, such as aircraft 3 needs to change towards the speed of X-axis forward movement in the horizontal direction, then can control the lower end of the 3rd deflecting plate 371,372 respectively around the negative sense rotation equal angular of the second deflecting plate S. A. 3701,3702 towards X-axis by control unit, under the airflow function washed and the 3rd deflecting plate 371 and the 3rd deflecting plate 372 pairs of aircraft produce the thrust of X-axis forward on one day, aircraft is moved towards X-axis forward; Control for aircraft 3 change of flight direction is the anglec of rotation by changing the first deflecting plate 351,352 and second deflecting plate 353,354, and center duct 30 is rotated around its center line, the heading of aircraft 3 is produced and changes.
In above-mentioned control method, when control unit detects that rolling situation appears in center duct 30, control unit controls the first deflecting plate and rotates to an angle in the opposite direction with identical rotating speed with the second deflecting plate and offset corresponding reactive torque to center duct 30 stops rolling.
In order to carry transported thing, can arrange a gondola in the below of center duct, in order to reduce the resistance of gondola to downwash flow, gondola has fleetline body skin and the top of contiguous center duct 30 is provided with fairing.
In this example, the propeller pitch angle of center rotor 311 is greater than the propeller pitch angle of the rotor of sidespin wing unit, and the first deflecting plate S. A. 3601 is orthogonal with the second deflecting plate S. A. 3701.
4th embodiment
As the explanation to the utility model the 4th embodiment, only the difference with above-mentioned 3rd embodiment is described below.
See Figure 10, the quantity of the 3rd deflecting plate 471 is one, the middle part of one end of the middle line parallel of the 3rd deflecting plate 471 Zhong Yu center duct is formed with a through hole along the center line direction being parallel to the second deflecting plate S. A. 4701, second deflecting plate S. A. 4701 and this via clearance are ordinatedly through this through hole, advancing in control unit working process, 3rd deflecting plate 471 rotates around the center line of this through hole, in rotary course, the air-flow washed under in the duct of center is to the midline of the point of resultant force of the power that it produces at this through hole, can not change around the rotation of the second deflecting plate S. A. 4701 with the 3rd deflecting plate 471.
5th embodiment
As the explanation to the utility model the 5th embodiment, only the difference with above-mentioned first embodiment is described below.
Adopt oil machine to substitute motor and drive rotor.
Claims (10)
1. five axle aircraft, comprise frame and 4 sidespin wing unit of the center rotor unit that is installed in described frame and the periphery that is distributed in described center rotor unit;
Described center rotor unit comprises center rotor, and the quantity of described center rotor is one;
Described sidespin wing unit comprises the sidespin wing;
It is characterized in that:
The rotation direction of positioned opposite two the described sidespin wings is identical, and the rotation direction of two described sidespin wings of adjacent layout is contrary.
2. five axle aircraft according to claim 1, is characterized in that:
The plane of rotation of described center rotor is higher than the plane of rotation of the described sidespin wing.
3. five axle aircraft according to claim 1 or 2, is characterized in that:
Described sidespin wing unit also comprises the side duct be installed in described frame, and the described sidespin wing is placed in the duct of described side, the axis of the described sidespin wing and the center line conllinear of described side duct.
4. five axle aircraft according to claim 3, is characterized in that:
Described center rotor unit also comprises the center duct installed in described frame, and described center rotor is placed in the duct of described center, the axis of described center rotor and the center line conllinear of described center duct.
5. five axle aircraft according to claim 4, is characterized in that:
The oar footpath of described center rotor equals the oar footpath of the described sidespin wing.
6. five axle aircraft according to claim 1 or 2, is characterized in that:
Described center rotor unit also comprises the center duct installed in described frame, and described center rotor is placed in the duct of described center, the axis of described center rotor and the center line conllinear of described center duct.
7. five axle aircraft according to claim 6, is characterized in that:
Also comprise reactive torque control unit and control unit of advancing;
Described reactive torque control unit comprises the first deflecting plate and second deflecting plate at the lower lip place being located at described center duct, described first deflecting plate and described second deflecting plate can rotate around the first deflecting plate S. A. orthogonal with described center line respectively, and described first deflecting plate and described second deflecting plate are arranged symmetrically with about described median centre;
Described control unit of advancing comprises the 3rd deflecting plate at the lower lip place being located at described center duct, and described 3rd deflecting plate can rotate around the second deflecting plate S. A. orthogonal with described center line.
8. five axle aircraft according to claim 1 or 2, is characterized in that:
The propeller pitch angle of described center rotor is greater than the propeller pitch angle of the described sidespin wing.
9. five axle aircraft according to claim 1 or 2, is characterized in that:
The blade quantity of described center rotor is greater than the blade quantity of the described sidespin wing.
10. five axle aircraft according to claim 1 or 2, is characterized in that:
The axis of the described sidespin wing and the axes intersect of described center rotor are in same intersection point, and described intersection point is positioned at the top of described center rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520237212.1U CN204548494U (en) | 2015-04-17 | 2015-04-17 | Five axle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520237212.1U CN204548494U (en) | 2015-04-17 | 2015-04-17 | Five axle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204548494U true CN204548494U (en) | 2015-08-12 |
Family
ID=53823638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520237212.1U Expired - Fee Related CN204548494U (en) | 2015-04-17 | 2015-04-17 | Five axle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204548494U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017197603A1 (en) * | 2016-05-18 | 2017-11-23 | 深圳市创客工场科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108622420A (en) * | 2018-07-02 | 2018-10-09 | 广州天翔航空科技有限公司 | Electronic multi-rotor aerocraft and control method |
| CN108773481A (en) * | 2018-07-02 | 2018-11-09 | 广州天翔航空科技有限公司 | Electronic Manned Flying System |
| CN109229351A (en) * | 2018-09-11 | 2019-01-18 | 林荣东 | A kind of quadrotor drone using the self-holding weighing apparatus of additional rotor double infection |
| CN112631321A (en) * | 2020-10-12 | 2021-04-09 | 北京理工大学 | Multi-shaft rotor unmanned aerial vehicle and flight control method thereof |
-
2015
- 2015-04-17 CN CN201520237212.1U patent/CN204548494U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017197603A1 (en) * | 2016-05-18 | 2017-11-23 | 深圳市创客工场科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108622420A (en) * | 2018-07-02 | 2018-10-09 | 广州天翔航空科技有限公司 | Electronic multi-rotor aerocraft and control method |
| CN108773481A (en) * | 2018-07-02 | 2018-11-09 | 广州天翔航空科技有限公司 | Electronic Manned Flying System |
| CN108773481B (en) * | 2018-07-02 | 2024-05-21 | 深圳市翔农创新科技有限公司 | Electric manned flight system |
| CN109229351A (en) * | 2018-09-11 | 2019-01-18 | 林荣东 | A kind of quadrotor drone using the self-holding weighing apparatus of additional rotor double infection |
| CN112631321A (en) * | 2020-10-12 | 2021-04-09 | 北京理工大学 | Multi-shaft rotor unmanned aerial vehicle and flight control method thereof |
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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: 20170421 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: 20150812 |
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| CF01 | Termination of patent right due to non-payment of annual fee |