CN109878713B - Micro coaxial double-rotor unmanned aerial vehicle - Google Patents

Abstract

Translated fromChinese

一种微型共轴双旋翼无人机，包括：依次从上到下连接的共轴双旋翼动力系统、轻量化机体和转向尾舵系统。共轴双旋翼动力系统包括：共轴的上旋翼、下旋翼和双旋翼支架，其中：上旋翼设置于双旋翼支架上，下旋翼设置于双旋翼支架内。轻量化机体为流线型中间镂空结构，两端设有对称设计的机身曲面。转向尾舵系统包括：转向舵机、转向机构和转向舵翼，其中：转向舵机设置于转向机构上，转向舵翼对称设置于转向机构两侧。本发明通过轻量化机体和共轴双旋翼动力系统的设计，质量轻，体积小，可承受的负载相对于机身重量比例大，可以灵活调整机体的角度，使无人机通过狭窄的空间，适合无人机机群布置。

A miniature coaxial dual-rotor unmanned aerial vehicle comprises: a coaxial dual-rotor power system, a lightweight body and a steering tail rudder system which are sequentially connected from top to bottom. The coaxial dual-rotor power system includes: coaxial upper rotor, lower rotor and dual-rotor bracket, wherein: the upper rotor is arranged on the dual-rotor bracket, and the lower rotor is arranged in the dual-rotor bracket. The lightweight body is a streamlined middle hollow structure, with symmetrically designed body surfaces at both ends. The steering tail rudder system includes a steering steering gear, a steering mechanism and a steering rudder blade, wherein the steering steering gear is arranged on the steering mechanism, and the steering rudder blades are symmetrically arranged on both sides of the steering mechanism. Through the design of a lightweight body and a coaxial dual-rotor power system, the invention has the advantages of light weight, small volume, and a large proportion of the load that can be tolerated relative to the weight of the body, and the angle of the body can be flexibly adjusted, so that the drone can pass through a narrow space. Suitable for UAV fleet layout.

Description

Micro coaxial double-rotor unmanned aerial vehicle

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, alightweight machine body 2, a steeringtail vane system 3, apositive propeller 4, a first direct currentbrushless motor 5, a double-rotor support 6, a machine body curvedsurface 7, a connectingsupport 8, asteering engine 9, asteering support 10, asteering shaft 11, a rudderwing steering engine 12, asteering rudder wing 13, anupper rotor wing 14, alower rotor wing 15, areverse propeller 16, a second direct currentbrushless motor 17 and asteering 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, alightweight machine body 2 and a steeringtail 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 anddual rotor support 6, which are disposed on the same vertical axis, wherein: theupper rotor 14 is arranged on the dual-rotor bracket 6, and thelower rotor 15 is arranged in the dual-rotor bracket 6.

The upperrotary wing 14 includes: apositive propeller 4 and a first dcbrushless motor 5, wherein: thepositive propeller 4 is arranged on a rotating shaft of the first DCbrushless motor 5, and the first DCbrushless motor 5 is arranged on the upper part of the dual-rotor bracket 6.

Thelower rotor 15 includes: areverse propeller 16 and a second dcbrushless motor 17, wherein: thereverse propeller 16 is arranged on a rotating shaft of the second direct currentbrushless motor 17, and the second direct currentbrushless motor 17 is arranged at the bottom in the dual-rotor bracket 6.

Thelightweight engine body 2 is of a streamlined middle hollow structure, and two symmetrically designed engine bodycurved surfaces 7 are arranged at two ends of the lightweight engine body.

The steeringtail vane system 3 comprises:steering engine 9,steering mechanism 18 andsteering rudder wing 13, wherein: thesteering engine 9 is arranged on thesteering mechanism 18, and thesteering rudder wings 13 are symmetrically arranged on two sides of thesteering mechanism 18.

Thesteering mechanism 18 includes:steering support 10, rudderwing steering wheel 12 andsteering shaft 11, wherein: the rudderwing steering engines 12 are arranged in thesteering support 10 in a centrosymmetric manner, and the rudderwing steering engines 12 are connected with thesteering rudder wings 13 throughsteering shafts 11.

And a connectingbracket 8 used for being connected with the light-weight machine body is arranged on thesteering 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)

Translated fromChinese

1.一种微型共轴双旋翼无人机，其特征在于，包括：依次从上到下连接的共轴双旋翼动力系统、轻量化机体和转向尾舵系统；1. a miniature coaxial dual-rotor unmanned aerial vehicle, is characterized in that, comprises: the coaxial dual-rotor power system, lightweight body and steering tail rudder system connected successively from top to bottom;所述的共轴双旋翼动力系统包括：共轴的上旋翼、下旋翼和双旋翼支架，其中：上旋翼设置于双旋翼支架上，下旋翼设置于双旋翼支架内；The coaxial dual-rotor power system includes: a coaxial upper rotor, a lower rotor and a dual-rotor bracket, wherein: the upper rotor is arranged on the dual-rotor bracket, and the lower rotor is arranged in the dual-rotor bracket;所述的转向尾舵系统包括：转向舵机、转向机构和转向舵翼，其中：转向舵机设置于转向机构上，转向舵翼对称设置于转向机构两侧；The steering tail rudder system includes: a steering steering gear, a steering mechanism and a steering rudder blade, wherein: the steering steering gear is arranged on the steering mechanism, and the steering rudder blades are symmetrically arranged on both sides of the steering mechanism;所述的上旋翼包括：正螺旋桨和第一直流无刷电机，其中：正螺旋桨设置于第一直流无刷电机上，第一直流无刷电机设置于双旋翼支架上部；The upper rotor includes: a positive propeller and a first DC brushless motor, wherein: the positive propeller is arranged on the first DC brushless motor, and the first DC brushless motor is arranged on the upper part of the double rotor bracket;所述的下旋翼包括：反螺旋桨和第二直流无刷电机，其中：反螺旋桨设置于第二直流无刷电机上，第二直流无刷电机设置于双旋翼支架内底部；The lower rotor includes: an anti-propeller and a second DC brushless motor, wherein: the anti-propeller is arranged on the second DC brushless motor, and the second DC brushless motor is arranged on the inner bottom of the double rotor bracket;所述的转向机构包括：转向支架、舵翼舵机和转向轴，其中：舵翼舵机中心对称设置于转向支架内，舵翼舵机通过转向轴与转向舵翼相连。The steering mechanism includes a steering bracket, a rudder wing steering gear and a steering shaft, wherein the rudder wing steering gear is symmetrically arranged in the steering bracket in the center, and the rudder wing steering gear is connected to the steering rudder blade through the steering shaft.2.根据权利要求1所述的微型共轴双旋翼无人机，其特征是，所述的轻量化机体为流线型中间镂空结构，两端设有对称设计的机身曲面。2 . The miniature coaxial dual-rotor UAV according to claim 1 , wherein the lightweight body is a streamlined intermediate hollow structure, and both ends are provided with symmetrically designed body surfaces. 3 .3.根据权利要求1所述的微型共轴双旋翼无人机，其特征是，所述的转向舵机上设有用于与轻量化机体连接的连接支架。3 . The miniature coaxial dual-rotor UAV according to claim 1 , wherein the steering steering gear is provided with a connecting bracket for connecting with the lightweight body. 4 .

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