CN209441629U - A kind of compact unmanned plane - Google Patents
A kind of compact unmanned plane Download PDFInfo
- Publication number
- CN209441629U CN209441629U CN201720095233.3U CN201720095233U CN209441629U CN 209441629 U CN209441629 U CN 209441629U CN 201720095233 U CN201720095233 U CN 201720095233U CN 209441629 U CN209441629 U CN 209441629U
- Authority
- CN
- China
- Prior art keywords
- rotor
- unmanned plane
- driving motor
- fuselage cradle
- propeller hub
- Prior art date
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model provides a kind of unmanned plane, belongs to aircraft field, specially a kind of compact unmanned plane.Power output shaft including being connected to rotor driving motor below propeller hub, the rotor being mounted on propeller hub, propeller hub, rotor driving motor is placed on fuselage cradle, flight control system, the speed setting controller of rotor driving motor and battery are installed in inside fuselage cradle, at least there are two the both ends that rotor is respectively arranged in fuselage cradle, and two rotors do not form height shape distribution up and down in same level.The structure size of unmanned plane is reduced on the whole, and the volumetric spaces after storage are further reduced using the Managed Solution of folding storage formula, the unmanned plane for generating the mode of lap by using two rotors are formed under different height again, reach the overall dimensions for further reducing unmanned plane, in the case where not influencing the lifting flight balance ability of unmanned plane, it is portable to achieve the purpose that provide smaller volume for further compact designed.
Description
Technical field
The utility model provides a kind of unmanned plane, belongs to aircraft field, specially a kind of compact unmanned plane.
Background technique
Unmanned plane is the not manned aircraft using radio robot and the presetting apparatus provided for oneself manipulation.From technology
Angle definition can be divided into: unmanned helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol
Deng.Unmanned plane press application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.
For the unmanned plane of civilian aspect, the typically unmanned plane of quadrotor structure, such unmanned plane is bulky, takes
Band is inconvenient, it is even more impossible to carry out transportation, the unmanned plane that can store at present and quadrotor it is more, only for rotation
Alar part folds, but due to quadrotor, folded volume is also very big, is unfavorable for carrying, and current unmanned plane machine
Body complicated integral structure, volume are big, at high cost.
Utility model content
In view of the deficiency of the prior art, the purpose of the utility model is to provide a kind of conducive to portable tight
Gather type unmanned plane, the scientific realization simplicity from structure reduces the cost of unmanned plane using the design of few rotor on the whole
And structure size, and the volumetric spaces after storage are further reduced using the Managed Solution of folding storage formula, meanwhile, for the first time
The unmanned plane by the way of forming two rotors under different height and generating lap of innovation formula, this overlapping can have
The unmanned plane that further reduces of effect is carrying the overall dimensions in placing and transporting, flat in the lifting flight for not influencing unmanned plane
Under weighing apparatus ability, it is compact to achieve the purpose that provide smaller volume for further compact designed.
The utility model is realized in this way: a kind of compact unmanned plane including propeller hub (1), is mounted on propeller hub (1)
The power output shaft of rotor driving motor (3) is connected to below rotor (2), propeller hub (1), rotor driving motor (3) is placed in fuselage
On frame (4), flight control system (5), the speed setting controller (6) of rotor driving motor (3) and battery (7) are installed in fuselage cradle (4)
Inside, at least there are two the both ends that rotor (2) are respectively arranged in fuselage cradle (4), and two rotors (2) are not in same level
Height shape is distributed up and down for upper formation.
Further, the range of described two rotor (2) coverings has juxtaposition part (8) on positive 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 driving motor (3) is mounted on rotor driving motor bracket (9), rotor driving motor
One end of bracket (9) is connected by installing swivel bearing (14) with fuselage cradle (4), the other end of rotor driving motor bracket (9)
It is connected on the power output shaft of Servo-controller (10), Servo-controller (10) is mounted on the servorudder being fixed on fuselage cradle (4)
On machine support (11), rotor driving motor bracket (9) can be on swivel bearing (14) under the power effect of Servo-controller (10)
It rotates left and right.
Further, the rotor (2) is to be connected and composed by two rotation paddles (12) in "-" type, and two rotation paddles (12) are with can
Fold collapse 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 opposite.
Further, there are the convex-segment (13) to raise upward, both ends on a both ends at least end for the fuselage cradle (4)
There is convex-segment (13), then the height of two convex-segments (13) is different, and rotor (2) is mounted on convex-segment (13).
The working principle introduction of the utility model: a kind of compact unmanned plane, including propeller hub (1), be mounted on propeller hub (1)
Rotor (2), the power output shafts of rotor driving motor (3) is connected to below propeller hub (1), rotor driving motor (3) is placed in machine
On stature (4), flight control system (5), the speed setting controller (6) of rotor driving motor (3) and battery (7) are installed in fuselage cradle
(4) internal, at least there are two the both ends that rotor (2) are respectively arranged in fuselage cradle (4), and two rotors (2) are not in same water
Height shape distribution up and down is formed in plane, and the range of two rotors (2) covering has juxtaposition part on vertical view face
(8).Rotor (2) is not on the same horizontal plane, then the range of possible described two rotors (2) coverings has on positive vertical view face
Juxtaposition part (8), the widest part length of the juxtaposition part (8) account for the 0%~50% of rotor (2) diameter length, because
This, reduces the volume size of unmanned plane from overall structure, changes into bispin from traditional quadrotor (2) or more rotors (2)
The wing (2), meanwhile, by misplacing up and down, therefore it can guarantee the part with an overlapping between rotor (2), it in this way can be
Reduced in terms of the length of unmanned plane, achievees the purpose that reduce length, reduces volume and reach compact；Meanwhile by rotor liter
The principle of power distribution is it is found that the useful lift that the edge of rotor and the region at bosom provide acts on minimum, such knot
Structure feature but also height distribution two rotors between there is no the conflict of interaction force and influences, i.e., will not be because of rotation
The height of the wing is distributed and influences the level stability of unmanned plane entirety, therefore, acts on the smallest fringe region using lift and carries out phase
Mutually overlapping, can effectively reduce the length dimension of unmanned plane entirety under the premise of not losing whole lift, reach and maintain
While effect lift does not subtract and can maintain overall stability, the effect of the carrying volume of unmanned plane is reduced；
The rotor driving motor (3) is mounted on rotor driving motor bracket (9), rotor driving motor bracket (9)
One end is connected by installing swivel bearing (14) with fuselage cradle (4), and the other end of rotor driving motor bracket (9) is connected to servo
On the power output shaft of steering engine (10), Servo-controller (10) is mounted on the Servo-controller bracket (11) being fixed on fuselage cradle (4)
On, rotor driving motor bracket (9) can rotate left and right under the power effect of Servo-controller (10) on swivel bearing (14), from
And drive rotor (2) that can tilt.Rotor (2) can tilt under the drive of rotor driving motor bracket (9) and
Opposite direction, i.e. differentiated inclination, realize steering, balance reaction torque and the roll of unmanned plane, and rotor (2) turns to without front and back, leads to
Cross the next real underriding pitching function of revolving speed acquisition lift difference for changing two motors.
The rotor (2) is to be connected and composed by two rotation paddles (12) in "-" type, and two rotations are with foldable gathering or can
The fixed form of disassembly installation is fixed on propeller hub (1).The distribution of rotor (2) upper layer and lower layer can not reduce rotor (2) diameter
Under conditions of shorten body volume mitigate weight.Rotor (2) reaches after folding to be reduced in unmanned plane carrying placement and transport
Volume increases convenience, folds, the frame mode that the mechanism that stretching, extension and disassembly are installed is existing means is constituted；
The direction of rotation of two groups of rotors (2) is opposite.To offset the reaction force of rotor (2).
There is the convex-segment (13) to raise upward, there is convex-segment at both ends on a both ends at least end for the fuselage cradle (4)
(13), then the height of two convex-segments (13) is different, and rotor (2) is mounted on convex-segment (13).Protrusion convex-segment (13) be in order to
Rotor (2) is raised to imitate with the distance of fuselage to improve paddle；
In conclusion portable compact unmanned plane provided by the utility model, scientific structure it is reasonable, using DCB Specimen
(2) design is reduced the structure size of unmanned plane on the whole, and is further decreased using the Managed Solution of folding storage formula
Volumetric spaces after storage, then by using the mode for forming under different height two rotors (2) and generating lap
Unmanned plane reaches the overall dimensions further reduced in unmanned plane carrying placement and transport, in the liter for not influencing unmanned plane
It drops under flight balance ability, it is compact to achieve the purpose that provide smaller volume for further compact designed.
Detailed description of the invention
Fig. 1 is the structural front view of portable compact unmanned plane；
Fig. 2 is that the movement of portable compact unmanned plane rotor deflects schematic diagram；
Fig. 3 is the schematic diagram that portable compact unmanned plane revolves paddle folding storage；
Fig. 4 is portable compact unmanned plane rotor coverage area top view；
Wherein: 1-propeller hub, 2-rotors, 3-rotor driving motors, 4-fuselage cradles, 5-flight control systems, 6-speed regulation controls
Device processed, 7-batteries, 8-juxtaposition parts, 9-rotor driving motor brackets, 10-Servo-controllers, 11-Servo-controller branch
Frame, 12-rotation paddles, 13-convex-segments, 14-swivel bearings.
Specific embodiment
Embodiment 1: as shown in Figure 1 to 4, a kind of compact unmanned plane, including propeller hub 1, the rotor being mounted on propeller hub 1
2, the power output shaft of rotor driving motor 3 is connected to below propeller hub 1, rotor driving motor 3 is placed on fuselage cradle 4, flies control system
System 5, the speed setting controller 6 of rotor driving motor 3 and battery 7 are installed in inside fuselage cradle 4, and at least there are two rotors 2 to distinguish
The both ends of fuselage cradle 4 are installed on, and two rotors 2 do not form height shape distribution up and down, and this two in same level
The range that rotor 2 covers has juxtaposition part 8 on vertical view face.Rotor 2 is not on the same horizontal plane, then described in possibility
The range of two rotors 2 covering has juxtaposition part 8, the widest part length of the juxtaposition part 8 on positive vertical view face
The 15% of 2 diameter length of rotor is accounted for, therefore, the volume size of unmanned plane is reduced from overall structure, from traditional more rotors 2
DCB Specimen 2 is changed into, meanwhile, by misplacing up and down, therefore it can guarantee the part with an overlapping between rotor 2, in this way
It can be reduced in terms of the length of unmanned plane, achieve the purpose that reduce length, reduce volume and reach compact；
The rotor driving motor 3 is mounted on rotor driving motor bracket 9, and one end of rotor driving motor bracket 9 is logical
It crosses installation swivel bearing 14 to be connected with fuselage cradle 4, the other end of rotor driving motor bracket 9 is connected to the power of Servo-controller 10
On output shaft, Servo-controller 10 is mounted on the Servo-controller bracket 11 being fixed on fuselage cradle 4, rotor driving motor bracket 9
It can be rotated left and right on swivel bearing 14 under the power effect of Servo-controller 10, to drive rotor 2 that can tilt.Rotation
The wing 2 can tilt under the drive of rotor driving motor bracket 9 and opposite direction, i.e. differentiated inclination, realizes unmanned plane
It turns to, balance reaction torque and roll, rotor 2 are showed without front and back steering by changing the revolving speed acquisition lift difference of two motors
Real underriding pitching function.
The rotor 2 is to be connected and composed by two rotation paddles 12 in "-" type, 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, folding and extension means
It is constituted for the frame mode of existing means；
The direction of rotation of two groups of rotors 2 is opposite.To offset the reaction force of rotor 2.
There is the convex-segment 13 to raise upward on at least end of the both ends of the fuselage cradle 4, there is convex-segment 13 at both ends,
Then the height of two convex-segments 13 is different, and rotor 2 is mounted in convex-segment 13.The convex-segment 13 of protrusion is to raise rotor 2 with fuselage
Distance come improve paddle effect.
Claims (2)
1. a kind of compact unmanned plane, including being connected to below propeller hub (1), the rotor (2) being mounted on propeller hub (1), propeller hub (1)
The power output shaft of rotor driving motor (3), rotor driving 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 dynamic motor (3) are installed in fuselage cradle (4), it is characterised in that: there are two rotors
(2) both ends of fuselage cradle (4) are respectively arranged in, and two rotors (2) do not form height shape point up and down in same level
Cloth；
The rotor driving motor (3) is mounted on rotor driving motor bracket (9), one end of rotor driving motor bracket (9)
It is connected by installation swivel bearing (14) with fuselage cradle (4), the other end of rotor driving motor bracket (9) is connected to Servo-controller
(10) on power output shaft, Servo-controller (10) is mounted on the Servo-controller bracket (11) being fixed on fuselage cradle (4), rotation
Wing driving motor bracket (9) can rotate left and right under the power effect of Servo-controller (10) on swivel bearing (14), thus band
Dynamic rotor (2) can tilt；Rotor (2) is turned to without front and back, and the revolving speed by changing two rotor driving motors (3) obtains
It obtains lift difference and carrys out real underriding pitching function；The range of described two rotor (2) coverings has juxtaposition on positive vertical view face
Partially (8), the widest part length of the juxtaposition part (8) account for the 0%~50% of rotor (2) diameter length；
The rotor (2) is to be connected and composed by two rotation paddles (12) in "-" type, and two rotation paddles (12) are with foldable gathering or fastly
The mounting means that quick-mounting unloads is fixed on propeller hub (1)；
The direction of rotation of two groups of rotors (2) is opposite.
2. a kind of compact unmanned plane according to claim 1, which is characterized in that the both ends of the fuselage cradle (4) are at least
Having has the convex-segment (13) to raise upward on an end, there is convex-segment (13) at both ends, then the height of two convex-segments (13) is different,
Rotor (2) is mounted on convex-segment (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720095233.3U CN209441629U (en) | 2017-01-22 | 2017-01-22 | A kind of compact unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720095233.3U CN209441629U (en) | 2017-01-22 | 2017-01-22 | A kind of compact unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209441629U true CN209441629U (en) | 2019-09-27 |
Family
ID=68007445
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720095233.3U Active CN209441629U (en) | 2017-01-22 | 2017-01-22 | A kind of compact unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209441629U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113120232A (en) * | 2021-04-26 | 2021-07-16 | 苏州喜全软件科技有限公司 | Unmanned aerial vehicle capable of realizing attitude adjustment by folding rotating propellers |
| CN114802731A (en) * | 2022-05-24 | 2022-07-29 | 西北工业大学 | Overlapping type rotor wing structure system of multi-rotor wing unmanned aerial vehicle with different steering directions and optimization design method thereof |
-
2017
- 2017-01-22 CN CN201720095233.3U patent/CN209441629U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113120232A (en) * | 2021-04-26 | 2021-07-16 | 苏州喜全软件科技有限公司 | Unmanned aerial vehicle capable of realizing attitude adjustment by folding rotating propellers |
| CN114802731A (en) * | 2022-05-24 | 2022-07-29 | 西北工业大学 | Overlapping type rotor wing structure system of multi-rotor wing unmanned aerial vehicle with different steering directions and optimization design method thereof |
| CN114802731B (en) * | 2022-05-24 | 2023-06-20 | 西北工业大学 | Multi-rotor unmanned aerial vehicle overlapped rotor wing structure system with different steering directions and optimal design method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106585975A (en) | Compact unmanned aerial vehicle | |
| CN204822069U (en) | Four rotor unmanned aerial vehicle configurations of duct | |
| CN107042884A (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN108275264A (en) | A kind of foldable coaxial dual-rotor helicopter and its control method | |
| CN104787317B (en) | Aircraft and its control method | |
| CN209441629U (en) | A kind of compact unmanned plane | |
| CN110155316A (en) | A kind of coaxial twin screw vertically taking off and landing flyer of Moving mass control and its control method | |
| CN109941432A (en) | A kind of logistics distribution unmanned plane with regulatory function having a smooth flight | |
| CN104743107A (en) | Multi-rotor type aircraft | |
| CN207072429U (en) | One kind vertical lift tilting rotor wing unmanned aerial vehicle | |
| CN107161332A (en) | A kind of double-deck eight rotor wing unmanned aerial vehicle | |
| CN206511116U (en) | A kind of agricultural anti-oscillating multi-rotor unmanned aerial vehicle | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| CN206968973U (en) | A kind of eight rotor wing unmanned aerial vehicles of bilayer | |
| CN204383745U (en) | A kind of engine installation of unmanned plane | |
| US10392110B2 (en) | Solar cell module for unmanned aerial vehicle | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN103991540A (en) | Conical rotary flapping wing aircraft | |
| CN112093044A (en) | Variable wheelbase type power arm of vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN207683776U (en) | Power system and control system disconnect-type aircraft | |
| CN107757898A (en) | One kind is taken photo by plane folding wings unmanned plane | |
| CN207631475U (en) | It is a kind of can self-adjusting balance plant protection drone | |
| CN208134626U (en) | An a kind of axis disc-shaped flying craft | |
| CN205931255U (en) | Spherical unmanned aerial vehicle based on ARM | |
| CN207292418U (en) | A kind of unmanned plane can auto-folder windmill wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210913 Address after: No. 0807, unit 1, building C, commercial and residential building, Beichen wealth center, Panlong District, Kunming, Yunnan 650217 Patentee after: YUNNAN YOUHANG UNMANNED PLANE TECHNOLOGY Co.,Ltd. Address before: 650000 floor 20, Diamond Plaza, intersection of Xiba and Xihua North Road, Kunming, Yunnan Patentee before: YUNNAN JIYOU TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right |