CN109878713B - Micro coaxial double-rotor unmanned aerial vehicle - Google Patents
Micro coaxial double-rotor unmanned aerial vehicle Download PDFInfo
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- CN109878713B CN109878713B CN201910282651.7A CN201910282651A CN109878713B CN 109878713 B CN109878713 B CN 109878713B CN 201910282651 A CN201910282651 A CN 201910282651A CN 109878713 B CN109878713 B CN 109878713B
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Abstract
A miniature coaxial dual rotor drone, comprising: the coaxial dual-rotor power system, the lightweight airframe and the steering tail vane system are connected in sequence from top to bottom. Coaxial dual rotor power system includes: coaxial upper rotor, lower rotor and dual rotor pylon wherein: the upper rotor wing is arranged on the double-rotor support, and the lower rotor wing is arranged in the double-rotor support. The lightweight organism is streamlined middle hollow out construction, and both ends are equipped with the fuselage curved surface of symmetric design. The steering tail vane system includes: turn to steering wheel, steering mechanism and turn to the rudder wing, wherein: the steering engine is arranged on the steering mechanism, and the steering rudder wings are symmetrically arranged on two sides of the steering mechanism. The invention has the advantages of light weight, small volume, large weight ratio of bearable load to the weight of the airframe and flexible adjustment of the angle of the airframe by the design of the light airframe and the coaxial double-rotor power system, so that the unmanned aerial vehicle passes through a narrow space and is suitable for the arrangement of the unmanned aerial vehicle cluster.
Description
Technical Field
The invention relates to the technology in the field of miniature aircrafts, in particular to a miniature coaxial dual-rotor unmanned aerial vehicle capable of passing through a narrow transverse space.
Background
Micro-drones are often used in a variety of applications such as reconnaissance, photography, ground exploration, cargo transportation, and the like. However, the low endurance and payload characteristics of the drone itself limit the practical role that the drone can actually play in these applications. Simultaneously, current civilian unmanned aerial vehicle uses four rotor unmanned aerial vehicle as leading, has the horizontal area too big, is difficult to through the not enough in narrow space.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a micro coaxial dual-rotor unmanned aerial vehicle. The whole structure of the device adopts a longitudinal structure, so that the device has a small transverse area and can pass through a narrow transverse space. The unmanned aerial vehicle adopts an improved structure of a coaxial double-rotor power system and a tail vane steering device, and the horizontal moment generated by a positive oar and a negative oar is offset while the vertical upward lift force is generated; by the uniquely designed three-degree-of-freedom steering tail vane device, the opening angle and the horizontal rotation pose of the tail vane are adjusted, the posture of the unmanned aerial vehicle body can be flexibly adjusted, and the unmanned aerial vehicle is assisted to steer. The unmanned aerial vehicle is light in weight, small in size, large in weight ratio of bearable load to the body, and suitable for arrangement of unmanned aerial vehicle clusters. Compared with the existing commonly used quad-rotor unmanned aerial vehicle, the unmanned aerial vehicle can fly flexibly in narrow and not wide space better due to small transverse area, and therefore some reconnaissance and security tasks can be well completed.
The invention is realized by the following technical scheme:
the invention comprises the following steps: the coaxial dual-rotor power system, the lightweight airframe and the steering tail vane system are connected in sequence from top to bottom.
The coaxial dual-rotor power system comprises: coaxial upper rotor, lower rotor and dual rotor pylon wherein: the upper rotor wing is arranged on the double-rotor support, and the lower rotor wing is arranged in the double-rotor support.
The upper rotor includes: positive screw and first direct current brushless motor, wherein: the positive propeller is arranged on the first direct current brushless motor, and the first direct current brushless motor is arranged on the upper portion of the double-rotor support.
The lower rotor includes: reverse screw and second direct current brushless motor, wherein: the reverse propeller is arranged on the second direct current brushless motor, and the second direct current brushless motor is arranged at the bottom in the double-rotor support.
The lightweight engine body is of a streamlined middle hollow structure, and the two ends of the lightweight engine body are provided with symmetrically designed engine body curved surfaces.
The steering tail vane system comprises: turn to steering wheel, steering mechanism and turn to the rudder wing, wherein: the steering engine is arranged on the steering mechanism, and the steering rudder wings are symmetrically arranged on two sides of the steering mechanism.
The steering mechanism comprises: steering support, rudder wing steering wheel and steering shaft, wherein: the rudder wing steering engines are arranged in the steering support in a centrosymmetric manner and are connected with the steering rudder wing through a steering shaft.
The steering engine is provided with a connecting bracket used for being connected with the light-weight machine body.
Technical effects
Compared with the existing commonly used quad-rotor unmanned aerial vehicle platform, the unmanned aerial vehicle platform has a smaller transverse area by a longitudinally designed structure more suitable for a narrow space and three-degree-of-freedom tail rudder assisted steering; through lightweight organism and coaxial two rotor driving system's design, the quality is light, and is small, and the load that can bear is big for fuselage weight proportion, can adjust the angle of organism in a flexible way, makes unmanned aerial vehicle pass through constrictive space, is fit for the unmanned aerial vehicle cluster to arrange.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a side view of the present invention;
FIG. 4 is a schematic structural diagram of a steering tail vane system of the present invention;
in the figure: the steering system comprises a coaxial double-rotor power system 1, a lightweight machine body 2, a steering tail vane system 3, a positive propeller 4, a first direct current brushless motor 5, a double-rotor support 6, a machine body curved surface 7, a connecting support 8, a steering engine 9, a steering support 10, a steering shaft 11, a rudder wing steering engine 12, a steering rudder wing 13, an upper rotor wing 14, a lower rotor wing 15, a reverse propeller 16, a second direct current brushless motor 17 and a steering mechanism 18.
Detailed Description
As shown in fig. 1, the present embodiment relates to a micro coaxial dual-rotor drone, which includes: the coaxial dual-rotor power system comprises a coaxial dual-rotor power system 1, a lightweight machine body 2 and a steering tail vane system 3 which are connected from top to bottom in sequence.
The coaxial dual-rotor power system 1 comprises: upper rotor 14, lower rotor 15 and dual rotor support 6, which are disposed on the same vertical axis, wherein: the upper rotor 14 is arranged on the dual-rotor bracket 6, and the lower rotor 15 is arranged in the dual-rotor bracket 6.
The upper rotary wing 14 includes: a positive propeller 4 and a first dc brushless motor 5, wherein: the positive propeller 4 is arranged on a rotating shaft of the first DC brushless motor 5, and the first DC brushless motor 5 is arranged on the upper part of the dual-rotor bracket 6.
The lower rotor 15 includes: a reverse propeller 16 and a second dc brushless motor 17, wherein: the reverse propeller 16 is arranged on a rotating shaft of the second direct current brushless motor 17, and the second direct current brushless motor 17 is arranged at the bottom in the dual-rotor bracket 6.
The lightweight engine body 2 is of a streamlined middle hollow structure, and two symmetrically designed engine body curved surfaces 7 are arranged at two ends of the lightweight engine body.
The steering tail vane system 3 comprises: steering engine 9, steering mechanism 18 and steering rudder wing 13, wherein: the steering engine 9 is arranged on the steering mechanism 18, and the steering rudder wings 13 are symmetrically arranged on two sides of the steering mechanism 18.
The steering mechanism 18 includes: steering support 10, rudder wing steering wheel 12 and steering shaft 11, wherein: the rudder wing steering engines 12 are arranged in the steering support 10 in a centrosymmetric manner, and the rudder wing steering engines 12 are connected with the steering rudder wings 13 through steering shafts 11.
And a connecting bracket 8 used for being connected with the light-weight machine body is arranged on the steering engine 9.
The foregoing embodiments may be modified in many different ways by those skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and all changes that come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (3)
1. A miniature coaxial dual rotor unmanned aerial vehicle, comprising: the coaxial double-rotor power system, the light-weight machine body and the steering tail vane system are sequentially connected from top to bottom;
the coaxial dual-rotor power system comprises: coaxial upper rotor, lower rotor and dual rotor pylon wherein: the upper rotor wing is arranged on the double-rotor support, and the lower rotor wing is arranged in the double-rotor support;
the steering tail vane system comprises: turn to steering wheel, steering mechanism and turn to the rudder wing, wherein: the steering engine is arranged on the steering mechanism, and the steering rudder wings are symmetrically arranged on two sides of the steering mechanism;
the upper rotor includes: positive screw and first direct current brushless motor, wherein: the positive propeller is arranged on the first direct current brushless motor, and the first direct current brushless motor is arranged on the upper part of the double-rotor bracket;
the lower rotor includes: reverse screw and second direct current brushless motor, wherein: the reverse propeller is arranged on the second direct current brushless motor, and the second direct current brushless motor is arranged at the bottom in the double-rotor bracket;
the steering mechanism comprises: steering support, rudder wing steering wheel and steering shaft, wherein: the rudder wing steering engines are arranged in the steering support in a centrosymmetric manner and are connected with the steering rudder wing through a steering shaft.
2. The micro coaxial dual-rotor unmanned aerial vehicle as claimed in claim 1, wherein the lightweight airframe is a streamlined hollow structure with symmetrically designed airframe curved surfaces at both ends.
3. The micro coaxial dual-rotor unmanned aerial vehicle as claimed in claim 1, wherein the steering actuator is provided with a connecting bracket for connecting with a lightweight body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910282651.7A CN109878713B (en) | 2019-04-10 | 2019-04-10 | Micro coaxial double-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910282651.7A CN109878713B (en) | 2019-04-10 | 2019-04-10 | Micro coaxial double-rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109878713A CN109878713A (en) | 2019-06-14 |
| CN109878713B true CN109878713B (en) | 2022-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910282651.7A Expired - Fee Related CN109878713B (en) | 2019-04-10 | 2019-04-10 | Micro coaxial double-rotor unmanned aerial vehicle |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113086136B (en) * | 2021-04-08 | 2022-04-05 | 哈尔滨工程大学 | Compound propulsion bionic jellyfish robot |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211665A (en) * | 2010-04-07 | 2011-10-12 | 上海工程技术大学 | Micro dragonfly-imitating dual-flapping wing aircraft |
| CN108128448A (en) * | 2018-01-08 | 2018-06-08 | 浙江大学 | The coaxial tilting rotor wing unmanned aerial vehicle of double shoe formulas and its control method |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050051667A1 (en) * | 2001-12-21 | 2005-03-10 | Arlton Paul E. | Micro-rotorcraft surveillance system |
| GB2491129B (en) * | 2011-05-23 | 2014-04-23 | Blue Bear Systems Res Ltd | Air vehicle |
| RU2648502C2 (en) * | 2012-05-21 | 2018-03-26 | Пол Э. АРЛТОН | Rotorcraft |
| US9517838B1 (en) * | 2014-10-03 | 2016-12-13 | John V. Howard | Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations |
| CN105799925B (en) * | 2016-03-14 | 2018-01-16 | 石玉玉 | A kind of unmanned plane |
| CN205891232U (en) * | 2016-07-08 | 2017-01-18 | 上海工程技术大学 | Urgent safe launching appliance of four rotor unmanned aerial vehicle |
| US10293957B2 (en) * | 2017-01-30 | 2019-05-21 | Hanhui Zhang | Rotary wing unmanned aerial vehicle and pneumatic launcher |
| CN206984348U (en) * | 2017-06-21 | 2018-02-09 | 中电科芜湖钻石飞机制造有限公司 | Electronic double coaxial tiltrotor aircrafts |
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2019
- 2019-04-10 CN CN201910282651.7A patent/CN109878713B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211665A (en) * | 2010-04-07 | 2011-10-12 | 上海工程技术大学 | Micro dragonfly-imitating dual-flapping wing aircraft |
| CN108128448A (en) * | 2018-01-08 | 2018-06-08 | 浙江大学 | The coaxial tilting rotor wing unmanned aerial vehicle of double shoe formulas and its control method |
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| Publication number | Publication date |
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| CN109878713A (en) | 2019-06-14 |
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Granted publication date: 20220322 |