CN203005746U - Composite type multi-rotor aircraft - Google Patents
Composite type multi-rotor aircraft Download PDFInfo
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- CN203005746U CN203005746U CN 201220708839 CN201220708839U CN203005746U CN 203005746 U CN203005746 U CN 203005746U CN 201220708839 CN201220708839 CN 201220708839 CN 201220708839 U CN201220708839 U CN 201220708839U CN 203005746 U CN203005746 U CN 203005746U
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Abstract
本实用新型提供了一种复合式多旋翼飞行器，所述在机体上面安装有偶数个姿态旋翼组件和一个中心共轴双桨旋翼组件，姿态旋翼组件主要用于飞行器的姿态控制，中心共轴双桨旋翼组件采用共轴双桨结构，两个螺旋桨互为反向转动，共轴双桨旋翼组件无反扭矩，提供整个飞行器的主要升力。每个姿态旋翼组件包含旋翼电机和旋翼螺旋桨，姿态旋翼组件对称分布于机体四周。飞行控制器以及电池安装于机体中。本实用新型外形布局新颖，中心采用共轴双桨结构，共轴双桨高速旋转具有很强的陀螺效应，能够提高整个飞行器的动态稳定性，并且姿态旋翼组件和中心共轴组件各有分工协同配合，能够大大提高整个飞行器的安全可靠性。
The utility model provides a composite multi-rotor aircraft, wherein an even number of attitude rotor assemblies and a central coaxial double-blade rotor assembly are installed on the airframe, the attitude rotor assembly is mainly used for the attitude control of the aircraft, and the center coaxial dual The paddle-rotor assembly adopts a coaxial double-blade structure, and the two propellers rotate in opposite directions. The coaxial dual-blade rotor assembly has no counter torque and provides the main lift of the entire aircraft. Each attitude rotor assembly includes a rotor motor and a rotor propeller, and the attitude rotor assemblies are symmetrically distributed around the body. The flight controller and battery are installed in the airframe. The utility model has a novel shape and layout, and the center adopts a coaxial double propeller structure. The high-speed rotation of the coaxial double propellers has a strong gyro effect, which can improve the dynamic stability of the entire aircraft, and the attitude rotor assembly and the central coaxial assembly have their own division of labor and coordination. Cooperation can greatly improve the safety and reliability of the entire aircraft.
Description
Technical field
The utility model relates to a kind of multi-rotor aerocraft, and a kind of combined type multi-rotor aerocraft that even number attitude rotor assemblies and center coaxial double-oar rotor assemblies consist of specifically is installed on body.
Background technology
The many rotors of existing routine are all generally that the rotor assemblies by a plurality of distribution body surroundings consists of, and the rotor of surrounding not only will provide the attitude of aircraft to control, but also whole load-carrying lift of aircraft will be provided, and the force of conventional many rotors is dispersed in surrounding.
Summary of the invention
The purpose of this utility model is: a kind of combined type multi-rotor aerocraft is provided.
The technical scheme that the utility model adopts is: in the body surrounding, even number attitude rotor assemblies and center coaxial double-oar rotor assemblies are installed, the attitude rotor assemblies is mainly used in the attitude of aircraft and controls, center coaxial double-oar rotor assemblies adopts the coaxial double-oar structure, two screw propellers are backward rotation each other, the coaxial double-oar rotor assemblies mainly provides the active force lift of whole aircraft without anti-twisted power.Each attitude rotor assemblies comprises rotor motor and propeller aircraft, and the rotor motor is fixed on above the body arm, and propeller aircraft is arranged in the rotating shaft of rotor motor and by the rotor motor-driven; All even number attitude rotor assemblies are symmetrically distributed in the body surrounding.Flight controller and battery are installed in body.Flight controller mainly provides the attitude of whole aircraft to control, and battery provides the energy supply of whole aircraft.
The beneficial effects of the utility model are: the utility model profile layout is novel, the coaxial double-oar structure is adopted at the center, the coaxial double-oar High Rotation Speed has very strong gyro effect, can improve the dynamic stability of whole aircraft, and the coaxial assembly in attitude rotor assemblies and the center coordinated of having one's own work to do can improve the safe reliability of whole aircraft greatly.
Description of drawings
Fig. 1: the utility model is faced structural representation
Fig. 2: the utility model plan structure schematic diagram
Fig. 3: TV structure schematic diagram at the bottom of the utility model
In figure, nomenclature is as follows:
In Fig. 1, Fig. 2 and Fig. 3,1 is many rotors body, and 2 is the attitude rotor assemblies, and 3 is the coaxial double-rotary airfoil assembly, and 4 is flight controller, and 5 is battery, and 6 is the rotor motor, and 7 is propeller aircraft, and 8 is coaxial motor, and 9 is coaxial screw propeller.
The specific embodiment
The utility model is described in further detail below in conjunction with the drawings and specific embodiments.
Shown in accompanying drawing embodiment: in body 1 surrounding, even number attitude rotor assemblies 2 is installed, body 1 center is equipped with coaxial double-oar rotor assemblies 3, and attitude rotor assemblies 2 is mainly used in the attitude of aircraft and controls, and flight controller 4 and battery 5 are installed in body 1; Center coaxial double-oar rotor assemblies 3 adopts the coaxial double-oar structure, and center coaxial double-oar rotor assemblies 3 comprises coaxial motor 8 and coaxial screw propeller 9; Each attitude rotor assemblies 2 comprises rotor motor 6 and propeller aircraft 7, and flight controller 4 and battery 5 are installed in body 1, and flight controller 4 mainly provides the attitude of whole aircraft to control, and battery 5 provides the energy of whole aircraft.
Claims (1)
1. combined type multi-rotor aerocraft, comprise body, attitude rotor assemblies, coaxial double-oar rotor assemblies, flight controller, battery, it is characterized in that: in the body surrounding, even number attitude rotor assemblies is installed, body center is equipped with the coaxial double-oar rotor assemblies, the attitude rotor assemblies is mainly used in the attitude of aircraft and controls, and body is equipped with flight controller and battery; Center coaxial double-oar rotor assemblies adopts the coaxial double-oar structure, and center coaxial double-oar rotor assemblies comprises coaxial motor and coaxial screw propeller; Each attitude rotor assemblies comprises rotor motor and propeller aircraft, and flight controller and battery are installed in body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220708839 CN203005746U (en) | 2012-12-20 | 2012-12-20 | Composite type multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220708839 CN203005746U (en) | 2012-12-20 | 2012-12-20 | Composite type multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203005746U true CN203005746U (en) | 2013-06-19 |
Family
ID=48597364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220708839 Expired - Lifetime CN203005746U (en) | 2012-12-20 | 2012-12-20 | Composite type multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203005746U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103359284A (en) * | 2013-06-29 | 2013-10-23 | 天津大学 | Petrol-electric hybrid four-rotor unmanned aerial vehicle |
| CN103625640A (en) * | 2013-10-25 | 2014-03-12 | 南京航空航天大学 | Multi-rotor unmanned aerial vehicle |
| WO2015027359A1 (en) * | 2013-09-02 | 2015-03-05 | Kang Jian | Automatically piloted rotorcraft |
| CN104760696A (en) * | 2015-04-22 | 2015-07-08 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
| CN104943857A (en) * | 2015-06-29 | 2015-09-30 | 哈尔滨盛世特种飞行器有限公司 | Petrol-electric hybrid five-rotor unmanned aerial vehicle |
| CN105438460A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Dual-power synergistically driven unmanned aerial vehicle |
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| WO2016054863A1 (en) * | 2014-10-11 | 2016-04-14 | 杨华东 | Multi-rotor air vehicle |
| CN105620765A (en) * | 2015-12-29 | 2016-06-01 | 苏州妙旋无人机应用有限公司 | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system |
| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
| CN106927028A (en) * | 2016-11-03 | 2017-07-07 | 刘森磊 | Lift oar separates the electronic multiple wing unmanned plane dynamic structure of layout with gesture stability oar |
| CN110040243A (en) * | 2019-04-10 | 2019-07-23 | 东北大学 | The combined type multi-rotor unmanned aerial vehicle rotor system at data-oriented center |
| CN110294114A (en) * | 2019-05-07 | 2019-10-01 | 前海微蜂创联科技(深圳)合伙企业(有限合伙) | Attitude control system of a coaxial double propeller aircraft |
| CN112340000A (en) * | 2019-08-06 | 2021-02-09 | 贯月航空技术(杭州)有限公司 | Electric coaxial multi-rotor helicopter based on contra-rotating dual-rotor motor |
-
2012
- 2012-12-20 CN CN 201220708839 patent/CN203005746U/en not_active Expired - Lifetime
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103359284A (en) * | 2013-06-29 | 2013-10-23 | 天津大学 | Petrol-electric hybrid four-rotor unmanned aerial vehicle |
| WO2015027359A1 (en) * | 2013-09-02 | 2015-03-05 | Kang Jian | Automatically piloted rotorcraft |
| CN103625640A (en) * | 2013-10-25 | 2014-03-12 | 南京航空航天大学 | Multi-rotor unmanned aerial vehicle |
| WO2016054863A1 (en) * | 2014-10-11 | 2016-04-14 | 杨华东 | Multi-rotor air vehicle |
| WO2016169176A1 (en) * | 2015-04-22 | 2016-10-27 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
| CN104760696A (en) * | 2015-04-22 | 2015-07-08 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
| CN104760696B (en) * | 2015-04-22 | 2016-07-27 | 深圳市艾特航空科技股份有限公司 | A kind of multi-rotor aerocraft |
| CN104943857A (en) * | 2015-06-29 | 2015-09-30 | 哈尔滨盛世特种飞行器有限公司 | Petrol-electric hybrid five-rotor unmanned aerial vehicle |
| CN105438460A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Dual-power synergistically driven unmanned aerial vehicle |
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| CN105620765A (en) * | 2015-12-29 | 2016-06-01 | 苏州妙旋无人机应用有限公司 | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system |
| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
| CN106927028A (en) * | 2016-11-03 | 2017-07-07 | 刘森磊 | Lift oar separates the electronic multiple wing unmanned plane dynamic structure of layout with gesture stability oar |
| CN110040243A (en) * | 2019-04-10 | 2019-07-23 | 东北大学 | The combined type multi-rotor unmanned aerial vehicle rotor system at data-oriented center |
| CN110294114A (en) * | 2019-05-07 | 2019-10-01 | 前海微蜂创联科技(深圳)合伙企业(有限合伙) | Attitude control system of a coaxial double propeller aircraft |
| CN110294114B (en) * | 2019-05-07 | 2023-09-01 | 桐乡市乌镇鹰航科技有限公司 | Attitude control system of a coaxial double propeller aircraft |
| CN112340000A (en) * | 2019-08-06 | 2021-02-09 | 贯月航空技术(杭州)有限公司 | Electric coaxial multi-rotor helicopter based on contra-rotating dual-rotor motor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130619 |