CN109878713A - Miniature coaxial double-rotary wing unmanned plane - Google Patents
Miniature coaxial double-rotary wing unmanned plane Download PDFInfo
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- CN109878713A CN109878713A CN201910282651.7A CN201910282651A CN109878713A CN 109878713 A CN109878713 A CN 109878713A CN 201910282651 A CN201910282651 A CN 201910282651A CN 109878713 A CN109878713 A CN 109878713A
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- unmanned plane
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- 238000010586 diagram Methods 0.000 description 1
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Abstract
A kind of miniature coaxial double-rotary wing unmanned plane, comprising: coaxial double-rotary wing dynamical system, lightweight body and the steering tail vane system successively connected from top to bottom.Coaxial double-rotary wing dynamical system includes: coaxial upper rotor, lower rotor and bispin wing support, in which: upper rotor is set on bispin wing support, and lower rotor is set in bispin wing support.Lightweight body is streamlined intermediate engraved structure, and both ends are equipped with the fuselage curved surface of symmetric design.Turning to tail vane system includes: steering-engine, steering mechanism and the steering rudder wing, in which: steering-engine is set in steering mechanism, is turned to the rudder wing and is symmetrically disposed on steering mechanism two sides.The present invention passes through the design of lightweight body and coaxial double-rotary wing dynamical system, and light weight is small in size, and the load that can be born is big relative to fuselage weight ratio, and the angle of body can be adjusted flexibly, and makes unmanned plane by narrow space, is suitble to unmanned plane group of planes arrangement.
Description
Technical field
The present invention relates to a kind of technology in minute vehicle field, it is specifically a kind of can be in narrow transverse space
By miniature coaxial double-rotary wing unmanned plane.
Background technique
Miniature drone be frequently utilized for such as scouting, photography, ground survey, in cargo transport multiple use.But nobody
The characteristics of low cruise duration of machine itself and payload, limits unmanned plane at these using the upper practical effect that can be played.
Meanwhile existing civilian unmanned plane, based on quadrotor drone, it is excessive that there are horizontal areas, it is difficult to not by narrow space
Foot.
Summary of the invention
The present invention In view of the above shortcomings of the prior art, proposes a kind of miniature coaxial double-rotary wing unmanned plane.It whole
Body structure uses vertical structure, therefore its horizontal area is smaller, can pass through narrow horizontal space.This unmanned plane is using altogether
The improvement structure of axis DCB Specimen dynamical system and tail vane transfer counteracts positive and negative while generating lift vertically upward
The horizontal moment that paddle generates；By the steering tail vane device of the Three Degree Of Freedom of unique design, subtended angle and the level rotation of tail vane are adjusted
Indexable appearance, can neatly adjust the posture of body, and auxiliary unmanned plane turns to.Its light weight, small in size, the load that can be born
It is big relative to fuselage weight ratio, it is suitble to unmanned plane group of planes arrangement.Compared with currently used quadrotor drone, due to it
Horizontal area very little, it can be preferably narrow without neatly flying in open space, therefore can complete one well
A little scoutings, security protection task.
The present invention is achieved by the following technical solutions:
The present invention includes: the coaxial double-rotary wing dynamical system successively connected from top to bottom, lightweight body and steering tail vane
System.
The coaxial double-rotary wing dynamical system includes: coaxial upper rotor, lower rotor and bispin wing support, in which: on
Rotor is set on bispin wing support, and lower rotor is set in bispin wing support.
The upper rotor includes: right-handed screw paddle and the first DC brushless motor, in which: it is straight that right-handed screw paddle is set to first
It flows on brushless motor, the first DC brushless motor is set to DCB Specimen frame upper.
The lower rotor includes: counterpropeller and the second DC brushless motor, in which: it is straight that counterpropeller is set to second
It flows on brushless motor, the second DC brushless motor is set to bottom in bispin wing support.
The lightweight body is streamlined intermediate engraved structure, and both ends are equipped with the fuselage curved surface of symmetric design.
The steering tail vane system includes: steering-engine, steering mechanism and the steering rudder wing, in which: steering-engine setting
Steering mechanism two sides are symmetrically disposed in steering mechanism, turning to the rudder wing.
The steering mechanism includes: steering bracket, rudder wing steering engine and steering shaft, in which: rudder wing steering engine central symmetry is set
It is placed in steering bracket, rudder wing steering engine is connected by steering shaft with the rudder wing is turned to.
The steering-engine is equipped with the connecting bracket for connecting with lightweight body.
Technical effect
Compared with currently used quadrotor drone platform, the present invention passes through the longitudinal direction being more suitable through narrow space
The structure of design and the tail vane assisted diversion of Three Degree Of Freedom, have smaller horizontal area；Pass through lightweight body and coaxial pair
The design of rotor power system, light weight is small in size, and the load that can be born is big relative to fuselage weight ratio, can flexibly adjust
The angle of complete machine body makes unmanned plane by narrow space, is suitble to unmanned plane group of planes arrangement.
Detailed description of the invention
Fig. 1 is overall structure of the present invention；
Fig. 2 is main view of the present invention；
Fig. 3 is side view of the present invention；
Fig. 4 is that the present invention turns to tail vane system structure diagram；
In figure: coaxial double-rotary wing dynamical system 1, turns to tail vane system 3, right-handed screw paddle 4, the first direct current at lightweight body 2
Brushless motor 5, bispin wing support 6, fuselage curved surface 7, connecting bracket 8, steering-engine 9, steering bracket 10, steering shaft 11, the rudder wing
Steering engine 12 turns to the rudder wing 13, upper rotor 14, lower rotor 15, counterpropeller 16, the second DC brushless motor 17, steering mechanism 18.
Specific embodiment
As shown in Figure 1, for a kind of miniature coaxial double-rotary wing unmanned plane that the present embodiment is related to, wherein including: successively from upper
To the coaxial double-rotary wing dynamical system 1 of lower connection, lightweight body 2 and turn to tail vane system 3.
The coaxial double-rotary wing dynamical system 1 includes: the upper rotor 14 being set on same vertical axis, lower rotor 15
With bispin wing support 6, in which: upper rotor 14 is set on bispin wing support 6, and lower rotor 15 is set in bispin wing support 6.
The upper rotor 14 includes: right-handed screw paddle 4 and the first DC brushless motor 5, in which: right-handed screw paddle 4 is set to
In the shaft of first DC brushless motor 5, the first DC brushless motor 5 is set to 6 top of bispin wing support.
The lower rotor 15 includes: counterpropeller 16 and the second DC brushless motor 17, in which: counterpropeller 16 is arranged
In in the shaft of the second DC brushless motor 17, the second DC brushless motor 17 is set to bottom in bispin wing support 6.
The lightweight body 2 is streamlined intermediate engraved structure, and both ends are equipped with the fuselage curved surface of two valve symmetric designs
7。
The steering tail vane system 3 includes: steering-engine 9, steering mechanism 18 and the steering rudder wing 13, in which: turns to rudder
Machine 9 is set in steering mechanism 18, is turned to the rudder wing 13 and is symmetrically disposed on 18 two sides of steering mechanism.
The steering mechanism 18 includes: steering bracket 10, rudder wing steering engine 12 and steering shaft 11, in which: rudder wing steering engine 12
In in steering bracket 10, rudder wing steering engine 12 is connected by steering shaft 11 with the rudder wing 13 is turned to center symmetric setting.
The steering-engine 9 is equipped with the connecting bracket 8 for connecting with lightweight body.
Above-mentioned specific implementation can by those skilled in the art under the premise of without departing substantially from the principle of the invention and objective with difference
Mode carry out local directed complete set to it, protection scope of the present invention is subject to claims and not by above-mentioned specific implementation institute
Limit, each implementation within its scope is by the constraint of the present invention.
Claims (4)
1. a kind of miniature coaxial double-rotary wing unmanned plane characterized by comprising the coaxial double-rotary wing successively connected from top to bottom is dynamic
Force system, lightweight body and steering tail vane system；
The coaxial double-rotary wing dynamical system includes: coaxial upper rotor, lower rotor and bispin wing support, in which: upper rotor
It is set on bispin wing support, lower rotor is set in bispin wing support；
The steering tail vane system includes: steering-engine, steering mechanism and the steering rudder wing, in which: steering-engine, which is set to, to be turned
To in mechanism, turns to the rudder wing and be symmetrically disposed on steering mechanism two sides；
The upper rotor includes: right-handed screw paddle and the first DC brushless motor, in which: right-handed screw paddle be set to the first direct current without
In brush motor, the first DC brushless motor is set to DCB Specimen frame upper；
The lower rotor includes: counterpropeller and the second DC brushless motor, in which: counterpropeller be set to the second direct current without
In brush motor, the second DC brushless motor is set to bottom in bispin wing support.
2. miniature coaxial double-rotary wing unmanned plane according to claim 1, characterized in that the lightweight body is streamline
Engraved structure among type, both ends are equipped with the fuselage curved surface of symmetric design.
3. miniature coaxial double-rotary wing unmanned plane according to claim 1, characterized in that the steering mechanism includes: to turn
To bracket, rudder wing steering engine and steering shaft, in which: rudder wing steering engine center symmetric setting is in steering bracket, and rudder wing steering engine is by turning
It is connected to axis with the rudder wing is turned to.
4. miniature coaxial double-rotary wing unmanned plane according to claim 1, characterized in that the steering-engine, which is equipped with, to be used
In the connecting bracket being connect with 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 true CN109878713A (en) | 2019-06-14 |
| CN109878713B CN109878713B (en) | 2022-03-22 |
Family
ID=66936744
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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| CN (1) | CN109878713B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086136A (en) * | 2021-04-08 | 2021-07-09 | 哈尔滨工程大学 | Compound propulsion bionic jellyfish robot |
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| CN102211665A (en) * | 2010-04-07 | 2011-10-12 | 上海工程技术大学 | Micro dragonfly-imitating dual-flapping wing aircraft |
| US20140299708A1 (en) * | 2011-05-23 | 2014-10-09 | John Green | Rocket or ballistic launch rotary wing vehicle |
| CN105431352A (en) * | 2012-05-21 | 2016-03-23 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN105799925A (en) * | 2016-03-14 | 2016-07-27 | 石玉玉 | Unmanned aerial vehicle |
| US9517838B1 (en) * | 2014-10-03 | 2016-12-13 | John V. Howard | Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations |
| 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 |
| 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 |
| 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 |
| US20180215482A1 (en) * | 2017-01-30 | 2018-08-02 | Hanhui Zhang | Rotary wing unmanned aerial vehicle and pneumatic launcher |
-
2019
- 2019-04-10 CN CN201910282651.7A patent/CN109878713B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050051667A1 (en) * | 2001-12-21 | 2005-03-10 | Arlton Paul E. | Micro-rotorcraft surveillance system |
| CN102211665A (en) * | 2010-04-07 | 2011-10-12 | 上海工程技术大学 | Micro dragonfly-imitating dual-flapping wing aircraft |
| US20140299708A1 (en) * | 2011-05-23 | 2014-10-09 | John Green | Rocket or ballistic launch rotary wing vehicle |
| CN105431352A (en) * | 2012-05-21 | 2016-03-23 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| US9517838B1 (en) * | 2014-10-03 | 2016-12-13 | John V. Howard | Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations |
| CN105799925A (en) * | 2016-03-14 | 2016-07-27 | 石玉玉 | Unmanned aerial vehicle |
| 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 |
| US20180215482A1 (en) * | 2017-01-30 | 2018-08-02 | 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 |
| 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086136A (en) * | 2021-04-08 | 2021-07-09 | 哈尔滨工程大学 | Compound propulsion bionic jellyfish robot |
| CN113086136B (en) * | 2021-04-08 | 2022-04-05 | 哈尔滨工程大学 | Compound propulsion bionic jellyfish robot |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109878713B (en) | 2022-03-22 |
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