CN208715473U - Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula - Google Patents
Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula Download PDFInfo
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- CN208715473U CN208715473U CN201821324447.4U CN201821324447U CN208715473U CN 208715473 U CN208715473 U CN 208715473U CN 201821324447 U CN201821324447 U CN 201821324447U CN 208715473 U CN208715473 U CN 208715473U
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Abstract
The utility model discloses a kind of non-homogeneous ten rotor wing unmanned aerial vehicles of power arrangement formula, comprising: fuselage；Horn is circumferentially laid out along fuselage, and one end is fixing end to the horn along its length, and one end is free end；The fixing end of horn is fixed on fuselage, and the free end of horn is equipped with aviation mechanism；Center coaxial double-oar aviation mechanism is additionally provided with below fuselage；Coaxial double-oar aviation mechanism is mounted on the underface of fuselage geometric center by foot prop connector, and space is rationally utilized, and load-carrying ability is strong, and flight efficiency is high, compact-sized.
Description
Technical field
The utility model relates to unmanned plane fields, and in particular to a kind of non-homogeneous ten rotor wing unmanned aerial vehicle of layout type.
Background technique
Multi-rotor unmanned aerial vehicle mostly uses greatly lithium battery as power, has simple structure, flight stability, easily controllable etc. excellent
The UAV system such as land mapping, agricultural plant protection, fire-fighting, the forest fire protection that point is developed based on multi-rotor unmanned aerial vehicle are a wide range of
It promotes and applies.
Big load, long endurance are the important directions of unmanned air vehicle technique development, and load-carrying can be improved by increasing rotor quantity
Ability.Common big load multi-rotor unmanned aerial vehicle mostly uses greatly the forms such as the more rotors of conventional single layer, coaxial double-oar bilayer layout.It is conventional
Eight rotor of single layer is common structure type, has many advantages, such as that good flight stability, high reliablity, wind resistance be good, power effect is than high；
In order to further increase load-carrying ability, some units have developed 12 rotor of single layer, 16 using the method for increasing rotor quantity
Rotor structure, this structure can only increase frame dimensions by increase unmanned plane wheelbase to realize, and the central area of rack
There is larger area not covered by rotor wind field, so that space utilization rate is not high, operational support is inconvenient.It is another common coaxial
Double paddle bilayer layout structures, greatly improve space utilization rate, so that frame structure is more compact, but due to coaxial two paddles up and down
Between air-flow generate interference, make capable effect than reducing, generally than normal arrangement formula reduction by 15% or so.
Summary of the invention
The utility model aim is to provide a kind of non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula, and load-carrying ability is strong,
Flight efficiency is high, compact-sized.
For this purpose, providing a kind of non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula, comprising: fuselage, fuselage include fuselage frame
Frame, equipment compartment and foot prop, equipment compartment are mounted on fuselage ring, are connected with vertical foot prop below fuselage ring；Eight horns,
It is circumferentially laid out along fuselage, and one end is fixing end to the horn along its length, and one end is free end, and the fixing end of horn is fixed
Aviation mechanism is separately installed in the free end of fuselage, horn；Center coaxial double-oar aviation mechanism is additionally provided with below fuselage.
Optionally, the fuselage ring connects into square structure, eight horns by fuselage connector by four square tubes
It is fixed on four angles of fuselage ring by fuselage connector, fuselage ring and horn in same plane and form " well " font
Shape.Fuselage ring is the main stressed member of entire unmanned plane, and the utility model is set as square structure, and stability is good, can
Bear biggish load.
Further, the horn includes horn connector and horn bar, and horn bar is connected by horn connector and fuselage
The foldable connection of fitting.Optionally, horn length is identical as foot prop length, and horn can be folded down 90 degree, after folding, can fix
On foot prop, the portability of entire unmanned aerial vehicle body is improved.
Further, four vertical foot props are connected separately at four angles of fuselage ring.
Further, the aviation mechanism includes that motor, motor cabinet, electricity tune controller and rotor, the rotor can be rotated
Be fixed on motor, motor with electricity adjust controller be connected, motor is installed on motor cabinet, the free end phase of motor cabinet and horn
Even.The motor is brushless motor, and electricity adjusts flight control system and brushless motor in controller connection equipment compartment, according to flight control system
Control signal control motor speed, rotor is rotated together with brushless motor, for providing lift.
Further, the center coaxial double-oar aircraft systems include coaxial connector, upper motor and lower motor, upper rotor
It with lower rotor, powers on and controller and lower electricity is adjusted to adjust controller, upper motor connection powers on tune controller, the lower lower electricity regulation of motor connection
The output shaft of device processed, upper motor and lower motor on the same axis, and it is opposed be mounted on coaxial connector, upper rotor can be rotated
Ground is fixed on the output shaft of motor to rotate to a direction, lower rotor be rotatably fixed on the output shaft of lower motor with
Just the direction opposite with upper rotor rotates, and the coaxial connector is connected on foot prop by foot prop connector, foot prop connector
One end is connect with foot prop, and the other end is connected to coaxial connector, and plane where plane where foot prop connector and fuselage ring is flat
Row powers on and controller and lower electricity is adjusted to adjust controller using same model, and uses the same input signal, coaxial upper to ensure
Motor is cancelled out each other with the revolving speed of lower motor absolutely consistent, torque.
Further, the center coaxial double-oar aviation mechanism is one, and coaxial double-oar aviation mechanism is mounted on fuselage
The underface of geometric center, the axis of center coaxial double-oar aviation mechanism passes through the geometric center of fuselage, for providing center liter
Power.
It optionally, further include foot prop connector, foot prop connector one end is connect with foot prop, and the other end is connected to coaxial connection
Part, plane is parallel with plane where fuselage ring where foot prop connector.
Further, flight control system, GPS system, image delivering system, load control system are installed in the equipment compartment
System, power-supply management system and lithium battery.
UAV system flight theory described in the utility model is as follows:
Take off it is ready after, first start center coaxial double-oar aviation mechanism, throttle is opened into 50%~60% level, makes
It obtains aircraft and obtains certain lift, then start flight by the program of common eight-rotary wing aircraft；In flight course, center is coaxial
Double paddle aviation mechanisms remain uniform power output, and eight aviation mechanisms being circumferentially laid out are responsible for providing the liter that flight needs
Power is landed when aircraft needs to land by normal procedure, after coming to a complete stop, closing center's coaxial double-oar aviation mechanism.
Using above-mentioned technical proposal, the utility model has the following beneficial effects:
1. load-carrying ability is strong, center coaxial double-oar aviation mechanism constitutes ten rotor flying systems together with eight aviation mechanisms
System, in the reasonable situation of dynamical system type selecting, single-blade can bear the take-off weight of 10kg, take-off weight about 100kg；
2. flight efficiency is high, the efficiency only with center coaxial double-oar aviation mechanism is slightly lower, eight flights being circumferentially laid out
Mechanism in one plane, does not interfere with air-flow, and whole flight efficiency is higher；
3. relying on, the aviation mechanism that eight are circumferentially laid out carries out the posture of unmanned plane and direction is stablized, stability, wind resistance
It is suitable with common eight axis aircraft of single layer, it is better than four axis, six axis mechanisms；
4. coaxial double-oar aviation mechanism is mounted on the underface of fuselage geometric center by foot prop connector, rationally it is utilized
Space, entire unmanned plane is compact-sized, is convenient for logistics support.
Detailed description of the invention
Fig. 1 is the overall structure diagram of non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula of the utility model embodiment；
Fig. 2 is partial enlarged view at A in Fig. 1；
Fig. 3 is partial enlarged view at B in Fig. 1.
Appended drawing reference: 1 fuselage ring, 2 fuselage connectors, 3 equipment compartments, 4 foot props, 5 horns, 6 horn connectors, 7 flights
Mechanism, 8 electricity adjust controllers, 9 motors, 10 rotors, 11 motor cabinets, 12 foot prop connectors, 13 coaxial connectors, motor on 14, and 15
Upper rotor.
Specific embodiment
The embodiments of the present invention are described in detail below with reference to the accompanying drawings, those of ordinary skill in the art are held
It changes places and realizes them.However, the utility model can also be implemented in many different forms, and it is not limited to implementation as described herein
Example.For the sake of clarity, the part unrelated with description the utility model is omitted in the accompanying drawings.Unless otherwise indicated, this paper institute
Term has common meaning in the art.Herein, joined using descriptions such as term "left", "right", "upper", "lower"
The relative position for examining each component of attached drawing, using the same or similar different components of the difference such as term " first ", " second " function.
The use of these terms and similar terms is only used for facilitating description, but should not be understood as limitation the scope of the utility model.
Referring to Fig.1, a kind of non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula, comprising: fuselage, fuselage include fuselage ring 1
With equipment compartment 3 and foot prop, equipment compartment 3 is mounted on fuselage ring 1, and vertical foot prop 4 is connected with below fuselage ring 1；It is described
Flight control system, GPS system, image delivering system, load control system, power-supply management system and lithium electricity are installed in equipment compartment 3
Pond (not shown)；Eight horns 5, along fuselage circumferentially be laid out, the horn 5 along its length one end be fixing end, one
End is free end, and the fixing end of horn 5 is fixed on fuselage, and the free end of horn 5 is separately installed with aviation mechanism 7；Under fuselage
Side is additionally provided with center coaxial double-oar aviation mechanism.
Optionally, the fuselage ring 1 connects into square structure by fuselage connector 2 by four carbon fiber square tubes,
The load of 100kg or more can be born, eight horns 5 are fixed on four angles of fuselage ring 1 by fuselage connector 2, fuselage
Frame 1 and horn 5 in same plane and form " well " word shape.Fuselage ring 1 is the main stressed member of entire unmanned plane, this
Utility model is set as square structure, and stability is good, can bear biggish load.
The horn 5 includes horn connector 6 and horn bar, and horn bar can by horn connector 6 and fuselage connector 2
Fold connection.Fuselage connector 2 and two adjacent horn connectors 6 form a five-way structure, 5 length of horn and foot prop 4
Length is identical, and horn can be folded down 90 degree, after folding, can be fixed on foot prop 4, improves the portable of entire unmanned aerial vehicle body
Property.Four vertical foot props 4 are connected separately at four angles of fuselage ring 1, foot prop 4 is four isometric carbon fiber bars.
Referring to Fig. 2, the aviation mechanism 7 includes motor 9, motor cabinet 11, electricity tune controller 8 and rotor 10, the rotor
10 are rotatably fixed on motor 9, and motor 9 adjusts controller 11 to be connected with electricity, and motor 9 is installed on motor cabinet 11, motor cabinet
11 are connected with the free end of horn 5.The motor 9 be brushless motor, electricity adjust controller connection equipment compartment in flight control system and
Brushless motor controls motor speed according to the control signal of flight control system, and rotor is rotated together with brushless motor, for providing
Lift.The wheelbase of eight aviation mechanisms is 2250mm, and rotor specification is 32mm × 11mm, and single aviation mechanism maximum pull is about
20kg, take-off weight are less than 10kg；
Referring to Figure 1 and Figure 3, the center coaxial double-oar aircraft systems include coaxial connector 13, upper motor 14 and lower electricity
Machine, upper rotor 15 and lower rotor, power on and controller and lower electricity are adjusted to adjust controller, and the upper connection of motor 14 powers on tune controller, lower electricity
On the same axis, axis passes through fuselage center to the output shaft of the lower electricity tune controller of machine connection, upper motor 14 and lower motor, and right
It sets and is mounted on coaxial connector 13, upper rotor 15 is rotatably mounted to the output shaft of motor 14 to revolve to a direction
Turn, lower rotor is fixed on the output shaft of lower motor rotatably so that the direction opposite with upper rotor rotates.Power on tune controller
It adjusts controller to use same model with lower electricity, and uses the same input signal, to ensure coaxial upper motor 14 and lower motor
Revolving speed is absolutely consistent, torque is cancelled out each other.Coaxial connector 13 is connected on foot prop 4 by foot prop connector 12, and foot prop connects
12 one end of fitting is connect with foot prop 4, and the other end is connected to coaxial connector 13,12 place plane of foot prop connector and fuselage ring
1 place plane is parallel.
Center coaxial double-oar aviation mechanism be one, coaxial double-oar aviation mechanism be mounted on the geometric center of fuselage just under
Side, the axis of center coaxial double-oar aviation mechanism passes through the geometric center of fuselage, for providing center lift.
To make center coaxial double-oar aviation mechanism provide bigger lift, so that the load-carrying ability of entire flying platform reaches
To maximum, using following design principle: select upper rotor and lower rotor to be dimensioned slightly smaller than the cornerwise size of foot prop first, so that
Space layout is rationally compact；On this basis, the brushless motor to match with upper rotor and lower rotor size is matched, it is preferred that
The upper motor of the coaxial aviation mechanism in center and lower power of motor are greater than the motor of circumferential eight aviation mechanisms；Upper rotor and lower rotor
Direction of rotation it is opposite.Upper rotor and lower rotor are having a size of 35mm × 12mm, maximum pull about 40kg, operating point in practical flight
For 20kg.
The certain most preferred embodiments and other embodiments for realizing the utility model are described in detail above, but answer
Understand, the effect of these embodiments is only that citing, and do not lie in limit in any way the scope of the utility model, it is applicable or
Construction.The protection scope of the utility model is limited by appended claims and its equivalent way.Those skilled in the art can be
Many changes are made to foregoing embodiments under the introduction of the utility model, these changes each fall within the protection model of the utility model
It encloses.
Claims (10)
1. a kind of non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula, comprising: fuselage, fuselage include fuselage ring (1) and equipment compartment
(3), equipment compartment (3) is mounted on fuselage ring (1)；Eight horns (5) are circumferentially laid out along fuselage, and the horn (5) is along length
Degree direction one end is fixing end, and one end is free end, and the fixing end of horn (5) is fixed on fuselage, and the free end of horn is pacified respectively
Equipped with aviation mechanism (7)；It is characterized in that, being additionally provided with center coaxial double-oar aviation mechanism below fuselage ring (1).
2. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the fuselage ring
(1) You Sigen square tube connects into square structure by fuselage connector, and eight horns (5) are fixed by fuselage connector (2)
On four angles of fuselage ring (1), fuselage ring (1) and horn (5) in same plane and form " well " word shape.
3. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the horn (5)
Including horn connector (6) and horn bar, horn bar passes through horn connector (6) and fuselage connector (2) foldable connection.
4. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the aviation mechanism
It (7) include that motor (9), motor cabinet (11), electricity tune controller (8) and rotor (10), the rotor (10) are rotatably fixed on
On motor (9), motor (9) adjusts controller (8) to be connected with electricity, and motor (9) is installed on motor cabinet (11), motor cabinet (11) and machine
The free end of arm (5) is connected.
5. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the fuselage ring
(1) lower section is also connected with vertical foot prop (4), and the center coaxial double-oar aircraft systems include coaxial connector (13), are powered on
Machine (14) and lower motor, upper rotor (15) and lower rotor power on and adjust controller and lower electricity tune controller, in upper motor (14) connection
Electricity adjusts controller, and the lower electricity of lower motor connection adjusts controller, and the output shaft of upper motor (14) and lower motor is on the same axis, and right
It sets and is mounted on coaxial connector (13), upper rotor (15) is rotatably mounted to the output shaft of motor (14) so as to one
Direction rotates, and lower rotor is fixed on the output shaft of lower motor rotatably so that the direction opposite with upper rotor rotates, described total
Shaft coupling piece (13) is connected on foot prop (4) by foot prop connector (12), and foot prop connector (12) one end and foot prop (4) are even
It connects, the other end is connected to coaxial connector (13), and plane where plane where foot prop connector (12) and fuselage ring (1) is flat
Row.
6. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the center is coaxial
Double paddle aviation mechanisms are one, and coaxial double-oar aviation mechanism is mounted on the underface of the geometric center of fuselage, center coaxial double-oar
The axis of aviation mechanism passes through the geometric center of fuselage.
7. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 2, which is characterized in that in fuselage ring
(1) four vertical foot props (4) are connected separately at four angles.
8. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the equipment compartment
(3) inner that flight control system, GPS system, image delivering system, load control system, power-supply management system and lithium battery are installed.
9. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the horn (5)
Length and foot prop (4) height are identical.
10. non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula according to claim 1, which is characterized in that the fuselage frame
The material of frame (1) and foot prop (4) is carbon fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821324447.4U CN208715473U (en) | 2018-08-16 | 2018-08-16 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821324447.4U CN208715473U (en) | 2018-08-16 | 2018-08-16 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
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| Publication Number | Publication Date |
|---|---|
| CN208715473U true CN208715473U (en) | 2019-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821324447.4U Expired - Fee Related CN208715473U (en) | 2018-08-16 | 2018-08-16 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| CN111994271A (en) * | 2020-09-02 | 2020-11-27 | 哈尔滨工业大学 | Many rotor unmanned aerial vehicle platforms of big working range arm |
-
2018
- 2018-08-16 CN CN201821324447.4U patent/CN208715473U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| CN111994271A (en) * | 2020-09-02 | 2020-11-27 | 哈尔滨工业大学 | Many rotor unmanned aerial vehicle platforms of big working range arm |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190409 Termination date: 20200816 |
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| CF01 | Termination of patent right due to non-payment of annual fee |