CN106585975A - Compact unmanned aerial vehicle - Google Patents
Compact unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106585975A CN106585975A CN201710053971.6A CN201710053971A CN106585975A CN 106585975 A CN106585975 A CN 106585975A CN 201710053971 A CN201710053971 A CN 201710053971A CN 106585975 A CN106585975 A CN 106585975A
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- Prior art keywords
- rotor
- rotors
- unmanned plane
- unmanned aerial
- aerial vehicle
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 4
- 230000009471 action Effects 0.000 claims description 4
- 230000005611 electricity Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- NOQGZXFMHARMLW-UHFFFAOYSA-N Daminozide Chemical group CN(C)NC(=O)CCC(O)=O NOQGZXFMHARMLW-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000000481 breast Anatomy 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
- B64C27/41—Rotors having articulated joints with flapping hinge or universal joint, common to the blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention provides an unmanned aerial vehicle, specifically a compact unmanned aerial vehicle, which belongs to the field of aircrafts. The compact unmanned aerial vehicle comprises a propeller hub, rotors and a power output shaft, wherein the rotors are mounted on the propeller hub; and the power output shaft is positioned under the propeller hub and connected with a rotor driving motor. The rotor driving motor is placed on a vehicle frame; a flight control system, a speed regulation controller of the rotor driving motor and a battery are all mounted within the vehicle frame; at least two rotors are respectively mounted at two ends of the vehicle frame; and the two rotors are distributed in the same horizontal plane up and down in high and low forms. The structure size of the unmanned aerial vehicle is integrally reduced; the volume space of the folded unmanned aerial vehicle is further reduced by using a foldable management scheme; by using the unmanned aerial vehicle which adopts a mode of forming the two rotors at different heights to generate an overlapped part, the integral size of the unmanned aerial vehicle is further reduced; without affecting lifting flight balance capacity of the unmanned aerial vehicle, compact design is further performed to provide small volume so as to achieve a portable purpose.
Description
Technical field
The invention provides a kind of unmanned plane, belongs to aircraft field, specially a kind of compact unmanned plane.
Background technology
Unmanned plane is the not manned aircraft manipulated using radio robot and the presetting apparatus provided for oneself.From technology
Angle definition can be divided into：Depopulated helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol
Deng.Unmanned plane press application, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.
It is bulky for the unmanned plane of civilian aspect, the typically all unmanned plane of four rotor structures, such unmanned plane, take
Band inconvenience, cannot more carry out storage carrying, the unmanned plane that can be received at present, and four rotors is more, be only for rotation
Alar part is folded, but due to four rotors, the volume after folding is also very big, is unfavorable for carrying with, and current unmanned plane machine
Body complicated integral structure, volume are big, high cost.
The content of the invention
For the deficiency that above-mentioned prior art is present, it is an object of the present invention to provide a kind of beneficial to portable compact
Unmanned plane, from structure, the design realized simplicity, adopt few rotor of science, reduces the cost and knot of unmanned plane on the whole
Structure size, and the Managed Solution using folding storage formula further reduces the volumetric spaces after storage, meanwhile, innovate first
The unmanned plane by the way of two rotors generation laps are formed under differing heights of formula, this overlap can be effective
Further reduce unmanned plane and carrying the overall dimensions in the middle of placing and transporting, do not affect the lifting flight balance energy of unmanned plane
Under power, further compact designed, there is provided less volume is reaching compact purpose.
What the present invention was realized in：A kind of compact unmanned plane, including propeller hub (1), the rotor on propeller hub (1)
(2) power output shaft of rotor motor (3), is connected to below propeller hub (1), rotor motor (3) is placed in fuselage cradle (4)
On, flight control system (5), the speed setting controller (6) of rotor motor (3) and battery (7) are installed in fuselage cradle (4) inside,
At least two rotors (2) are respectively arranged in the two ends of fuselage cradle (4), and two rotors (2) not shape in same level
It is distributed into height shape up and down.
Further, the scope that described two rotors (2) cover has juxtaposition part (8) on just vertical view face, should
The widest part length of juxtaposition part (8) accounts for the 0%～50% of rotor (2) diameter length.
Further, the rotor motor (3) is on rotor motor support (9), rotor motor
One end of support (9) is connected with fuselage cradle (4) by installing swivel bearing (14), the other end of rotor motor support (9)
It is connected on the power output shaft of Servo-controller (10), Servo-controller (10) is installed in the servorudder being fixed on fuselage cradle (4)
On machine support (11), rotor motor support (9) can be on swivel bearing (14) under the dynamic action of Servo-controller (10)
Left rotation and right rotation.
Further, the rotor (2) is connected and composed in yi word pattern by two rotations oar (12), and two rotations oar (12) are with can
Fold draw in or can the mounting means of quick despatch be fixed on propeller hub (1).
Further, the direction of rotation of two groups of rotors (2) is contrary.
Further, there are on a two ends at least termination of the fuselage cradle (4) convex-segment (13) for raising up, two ends
There is convex-segment (13), then the height of two convex-segments (13) is different, and rotor (2) is in convex-segment (13).
The operation principle introduction of the present invention：A kind of compact unmanned plane, including propeller hub (1), the rotation on propeller hub (1)
The power output shaft of rotor motor (3) is connected to below the wing (2), propeller hub (1), rotor motor (3) is placed in fuselage cradle
(4), on, flight control system (5), the speed setting controller (6) of rotor motor (3) and battery (7) are installed in fuselage cradle (4)
Portion, at least two rotors (2) are respectively arranged in the two ends of fuselage cradle (4), and two rotors (2) are not in same level
Height shape distribution up and down is formed, and the scope that two rotors (2) cover has juxtaposition part (8) on vertical view face.Rotation
Not on same horizontal plane, then the scope that possible described two rotors (2) cover has on just vertical view face intersects weight to the wing (2)
Folded part (8), the widest part length of the juxtaposition part (8) account for the 0%～50% of rotor (2) diameter length, therefore, from whole
The volume size of unmanned plane is reduced in body structure, DCB Specimen (2) is changed into from traditional four rotors (2) or many rotors (2), together
When, by misplacing up and down, therefore the part with an overlap between rotor (2) is can ensure that, so can be in unmanned plane
Reduced in terms of length, reach reduction length, reduce volume and reach compact purpose；Meanwhile, it is distributed by rotor lift
Principle understands that the useful lift effect that the region at the edge and bosom of rotor provides is minimum, such construction featuress
So that be not in the conflict and impact of interaction force between two rotors of height distribution, i.e., will not be because of the height of rotor
The level stability for being distributed and affecting unmanned plane overall, therefore, acting on minimum marginal area using lift carries out overlapped, energy
It is enough effectively to reduce the overall length dimension of unmanned plane on the premise of overall lift is not lost, reach holding useful lift and do not subtract
While with stability in the large can be maintained, the effect of the carrying volume of unmanned plane is reduced；
The rotor motor (3) on rotor motor support (9), rotor motor support (9)
One end is connected with fuselage cradle (4) by installing swivel bearing (14), and the other end of rotor motor support (9) is connected to servo
On the power output shaft of steering wheel (10), Servo-controller (10) is installed in the Servo-controller support (11) being fixed on fuselage cradle (4)
On, rotor motor support (9) under the dynamic action of Servo-controller (10) can on swivel bearing (14) left rotation and right rotation, from
And drive rotor (2) tilt.Rotor (2) can tilt under the drive of rotor motor support (9) and
Rightabout, i.e. differentiated inclination, realize steering, balance reaction torque and the roll of unmanned plane, and rotor (2) leads to without the need for turning in front and back
Cross the next real underriding pitching function of rotating speed acquisition lift difference for changing two motors.
The rotor (2) is connected and composed in yi word pattern by two rotations oar (12), and two rotations are with foldable gathering or can
The fixed form for removing and installing is fixed on propeller hub (1).Two-layer distribution can not reduce rotor (2) diameter to rotor (2) up and down
Under conditions of shorten body volume mitigate weight.Rotor (2) fold after reach reduce unmanned plane carry place and transport in the middle of
Volume, increases convenience, and the mechanism for folding, stretch and removing and installing is that the frame mode of existing means is constituted；
The direction of rotation of two groups of rotors (2) is contrary.To offset the counteracting force of rotor (2).
There is on a two ends at least termination of the fuselage cradle (4) convex-segment (13) for raising up, there is convex-segment at two ends
(13), then the height of two convex-segments (13) is different, and rotor (2) is in convex-segment (13).Raised convex-segment (13) be in order to
Rotor (2) is raised with the distance of fuselage to improve oar effect；
In sum, the present invention provide portable compact unmanned plane, scientific structure it is reasonable, using DCB Specimen (2)
Design, reduce the structure size of unmanned plane on the whole, and the Managed Solution using folding storage formula further reduce
Volumetric spaces after storage, then the nothing by way of adopting and two rotors (2) generation laps are formed under differing heights
It is man-machine, the overall dimensions for further reducing that unmanned plane carrying is placed and transport is central are reached, in the lifting for not affecting unmanned plane
Under flight balance ability, further compact designed, there is provided less volume is reaching compact purpose.
Description of the drawings
Structural front views of the Fig. 1 for portable compact unmanned plane；
Motion deflection schematic diagrams of the Fig. 2 for portable compact unmanned plane rotor；
Fig. 3 is the schematic diagram that portable compact unmanned plane revolves oar folding storage；
Fig. 4 is portable compact unmanned plane rotor coverage top view；
Wherein：1-propeller hub, 2-rotor, 3-rotor motor, 4-fuselage cradle, 5-flight control system, 6-speed governing control
Device processed, 7-battery, 8-juxtaposition part, 9-rotor motor support, 10-Servo-controller, 11-Servo-controller
Frame, 12-rotation oar, 13-convex-segment, 14-swivel bearing.
Specific embodiment
Embodiment 1：As shown in Figure 1 to 4, a kind of compact unmanned plane, including propeller hub 1, the rotor on propeller hub 1
2nd, the power output shaft of rotor motor 3 is connected to below propeller hub 1, rotor motor 3 is placed on fuselage cradle 4, flies control system
The system 5, speed setting controller 6 of rotor motor 3 and battery 7 are installed in inside fuselage cradle 4, and at least two rotors 2 are distinguished
The two ends of fuselage cradle 4 are installed on, and two rotors 2 in same level do not form height shape up and down and are distributed, and this two
The scope that rotor 2 is covered has juxtaposition part 8 on vertical view face.Rotor 2, then may be described not on same horizontal plane
The scope of two coverings of rotor 2 has juxtaposition part 8, the widest part length of the juxtaposition part 8 on just vertical view face
Account for the 15% of 2 diameter length of rotor, therefore, the volume size of unmanned plane is reduced from overall structure, from traditional many rotors 2
DCB Specimen 2 is changed into, meanwhile, by misplacing up and down, therefore the part with an overlap between rotor 2 is can ensure that, so
Can be reduced in terms of the length of unmanned plane, reach reduction length, reduce volume and reach compact purpose；
The rotor motor 3 is arranged on rotor motor support 9, and one end of rotor motor support 9 leads to
Cross installation swivel bearing 14 to be connected with fuselage cradle 4, the other end of rotor motor support 9 is connected to the power of Servo-controller 10
On output shaft, Servo-controller 10 is arranged on the Servo-controller support 11 being fixed on fuselage cradle 4, rotor motor support 9
Under the dynamic action of Servo-controller 10 can on swivel bearing 14 left rotation and right rotation, so as to drive rotor 2 tilt.Rotation
The wing 2 can tilt and rightabout under the drive of rotor motor support 9, i.e. differentiated inclination, realize unmanned plane
Turn to, balance reaction torque and roll, rotor 2 obtains lift difference to show by the rotating speed of two motors of change without the need for turn in front and back
Real underriding pitching function.
The rotor 2 is connected and composed in yi word pattern by two rotation oars 12, and two rotations are with the connection side of foldable gathering
Formula is fixed on propeller hub 1.Rotor 2 reaches the carrying volume for reducing unmanned plane after folding, increase convenience, folds and extension means
Frame mode for existing means is constituted；
The direction of rotation of two groups of rotors 2 is contrary.To offset the counteracting force of rotor 2.The two ends of the fuselage cradle 4 are extremely
There is on a rare termination convex-segment 13 for raising up, there is convex-segment 13 at two ends, then the height of two convex-segments 13 is different, rotor
2 are arranged in convex-segment 13.Raised convex-segment 13 is improving oar effect in order to raise rotor 2 with the distance of fuselage.
Claims (6)
1. a kind of compact unmanned plane, including propeller hub (1), the rotor (2) on propeller hub (1), propeller hub are connected to below (1)
The power output shaft of rotor motor (3), rotor motor (3) are placed on fuselage cradle (4), and flight control system (5), rotor drive
It is internal that the speed setting controller (6) and battery (7) of galvanic electricity machine (3) is installed in fuselage cradle (4), it is characterised in that：At least two
Rotor (2) is respectively arranged in the two ends of fuselage cradle (4), and two rotors (2) are not formed up and down just in same level
Shape is distributed.
2. a kind of compact unmanned plane according to claim 1, it is characterised in that the model that described two rotors (2) cover
It is trapped among on just vertical view face and there are juxtaposition part (8), the widest part length of the juxtaposition part (8) accounts for rotor (2) diameter
The 0%～50% of length.
3. a kind of compact unmanned plane according to claim 1, it is characterised in that the rotor motor (3) is installed
On rotor motor support (9), one end of rotor motor support (9) is by installing swivel bearing (14) and fuselage cradle
(4) it is connected, the other end of rotor motor support (9) is connected on the power output shaft of Servo-controller (10), Servo-controller
(10) installed in the Servo-controller support being fixed on fuselage cradle (4)
(11), on, rotor motor support (9) can be left on swivel bearing (14) under the dynamic action of Servo-controller (10)
Right rotation.
4. a kind of compact unmanned plane according to claim 1, it is characterised in that the rotor (2) is by two rotation oars
(12) connect and compose in yi word pattern, two rotations oar (12) with foldable gathering or can the mounting means of quick despatch be fixed on propeller hub
(1) on.
5. a kind of compact unmanned plane according to claim 1, it is characterised in that the rotation side of two groups of rotors (2)
To contrary.
6. a kind of compact unmanned plane according to claim 1, it is characterised in that the two ends of the fuselage cradle (4) are at least
Have and there is on a termination convex-segment (13) for raising up, there is convex-segment (13) at two ends, then the height of two convex-segments (13) is different,
Rotor (2) is in convex-segment (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710053971.6A CN106585975A (en) | 2017-01-22 | 2017-01-22 | Compact unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710053971.6A CN106585975A (en) | 2017-01-22 | 2017-01-22 | Compact unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106585975A true CN106585975A (en) | 2017-04-26 |
Family
ID=58585974
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710053971.6A Pending CN106585975A (en) | 2017-01-22 | 2017-01-22 | Compact unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106585975A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107953990A (en) * | 2017-12-25 | 2018-04-24 | 卫旭阳 | VTOL flight instruments and fixed-wing unmanned plane |
| CN108639320A (en) * | 2018-06-05 | 2018-10-12 | 河南三和航空工业有限公司 | A kind of DCB Specimen unmanned helicopter |
| CN108974353A (en) * | 2017-05-31 | 2018-12-11 | 尚皇科技有限公司 | The control method of remotely-piloted vehicle heading |
| CN109677600A (en) * | 2018-08-16 | 2019-04-26 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
| CN110770123A (en) * | 2017-07-05 | 2020-02-07 | 深圳市大疆创新科技有限公司 | Portable integrated UAV |
| WO2021155532A1 (en) * | 2020-02-06 | 2021-08-12 | XDynamics Limited | An unmanned aerial vehicle |
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| WO2015143098A2 (en) * | 2014-03-18 | 2015-09-24 | Joby Aviation, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
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| CN106081083A (en) * | 2016-06-28 | 2016-11-09 | 赵新宁 | The dynamic cross-arranging type four rotor agricultural plant protection depopulated helicopter of oil |
| CN205738073U (en) * | 2016-04-19 | 2016-11-30 | 倪德玉 | A kind of helicopter of VTOL horizontal flight |
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2017
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| US6089501A (en) * | 1998-06-22 | 2000-07-18 | Frost; Stanley A. | Tandem-rotor gyroplane |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| WO2015143098A2 (en) * | 2014-03-18 | 2015-09-24 | Joby Aviation, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974353A (en) * | 2017-05-31 | 2018-12-11 | 尚皇科技有限公司 | The control method of remotely-piloted vehicle heading |
| CN110770123A (en) * | 2017-07-05 | 2020-02-07 | 深圳市大疆创新科技有限公司 | Portable integrated UAV |
| CN107953990A (en) * | 2017-12-25 | 2018-04-24 | 卫旭阳 | VTOL flight instruments and fixed-wing unmanned plane |
| CN108639320A (en) * | 2018-06-05 | 2018-10-12 | 河南三和航空工业有限公司 | A kind of DCB Specimen unmanned helicopter |
| CN109677600A (en) * | 2018-08-16 | 2019-04-26 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
| WO2021155532A1 (en) * | 2020-02-06 | 2021-08-12 | XDynamics Limited | An unmanned aerial vehicle |
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Application publication date: 20170426 |