公开(公告)号：EP3147210A2

公开(公告)日：2017-03-29

申请号：EP16190742.3

申请日：2016-09-27

Applicant: Ewatt Technology Co., Ltd.

Inventor： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

IPC: B64C27/04 ,  B64C27/82 ,  B64C39/02 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08

CPC classification number: B64D33/02 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/141 ,  B64C2201/146 ,  B64D27/08 ,  B64D33/06 ,  B64D33/08 ,  B64D2033/0246 ,  B64D2033/028

Abstract: The present invention discloses an unmanned helicopter, and belongs to the technical field of unmanned aerial vehicles. The unmanned helicopter includes an air inlet system, an exhaust system, a cooling system and a dynamic balance system. The air inlet system is fixed on a second side; the exhaust system is fixed on a third side; and the cooling system is fixed on a first side, and the dynamic balance system is fixed on a tail. The airflow at the outside of the unmanned helicopter flows into the air inlet system smoothly, quickly and efficiently under the action of its own flow velocity relative to the unmanned helicopter, therefore the technical problem in the prior art that the air entering the fuselage with a unit volume is burnt insufficiently, which generates adverse effects on the normal flight of the unmanned helicopter, is solved.

Abstract translation: 本发明公开了一种无人直升机，属于无人驾驶飞行器技术领域。 无人直升机包括进气系统，排气系统，冷却系统和动平衡系统。 进气系统固定在第二侧; 排气系统固定在第三侧; 冷却系统固定在第一侧，动平衡系统固定在尾部。 无人直升机外部的气流在相对于无人驾驶直升机的自身流速的作用下，平稳，快速而有效地流入，因此现有技术中的技术问题是空气进入机身的空气 单位体积燃烧不足，对无人直升机的正常飞行产生不利影响，得到解决。

公开(公告)号：EP3181449A3

公开(公告)日：2017-09-13

申请号：EP16201250.4

申请日：2016-11-29

Applicant: Ewatt Technology Co.

Inventor： ZHAO, Guocheng ,  FAN, Hui ,  CHEN, Fangfang

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C27/32 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/20

Abstract: The present invention discloses a multi-rotor structure applied to an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle includes a fuselage, first rotors, second rotors and rotor shafts; and the multi-rotor structure includes first rotary connecting pieces and second rotary connecting pieces. The first rotary connecting piece includes a first motor (41) and a first dismounting thread group, the first rotor (21) is detachably connected with the first motor through the first dismounting thread group to achieve the mounting or dismounting between the first rotor and the first motor by rotating the first rotor; the second rotary connecting piece includes a second motor and a second dismounting thread group, and the second rotor is detachably connected with the second motor through the second dismounting thread group to achieve the mounting or dismounting between the second rotor and the second motor by rotating the second rotor. The present invention has the advantages of being fast, portable and high in working efficiency.

Abstract translation: 本发明公开了一种应用于无人机的多转子结构，属于无人机技术领域。 无人机包括机身，第一转子，第二转子和转子轴; 多转子结构包括第一旋转连接件和第二旋转连接件。 第一旋转连接件包括第一马达和第一拆卸线组，第一转子通过第一拆卸线组可拆卸地与第一电机连接，实现第一转子与第一拆卸线组之间的安装或拆卸， 通过旋转第一转子来驱动第一电动机 所述第二旋转连接件包括第二电机和第二拆卸线组，所述第二转子通过所述第二拆卸线组与所述第二电机可拆卸连接，实现所述第二转子与所述第二电机之间的安装或拆卸， 第二转子。 本发明具有快速，便携和工作效率高的优点。

公开(公告)号：EP3279087A1

公开(公告)日：2018-02-07

申请号：EP17182959.1

申请日：2017-07-25

Applicant: Ewatt Technology Co., Ltd.

Inventor： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

IPC: B64C27/08 ,  B64C27/12 ,  B64C27/59 ,  B64D35/04

CPC classification number: F02B61/04 ,  B64C27/08 ,  B64C27/12 ,  B64C27/14 ,  B64C27/59 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64D35/04 ,  F02B67/06 ,  F02B73/00 ,  F02B75/16 ,  F16H1/222 ,  F16H7/02 ,  F16H37/065

Abstract: The present invention discloses a multi-shaft power source unmanned flight equipment, and belongs to the technical field of unmanned aerial vehicles. The multi-shaft power source unmanned flight equipment comprises a frame (1), a plurality of rotor sets (2) and a power device (3). The plurality of rotor sets (2) are rotatably fixed on the frame (1), and the power device (3) is correspondingly movably connected with each rotor set (2) respectively. Power is provided for flight of the unmanned flight equipment by the power device (3) with oil drive characteristics, mechanical kinetic energy is generated by burning a combustion material pre-injected in the power device (3), and rotors (21) in each rotor set (2) correspondingly connected with the power device are driven to rotate, thereby replacing the traditional electric multi-rotor unmanned aerial vehicle structure adopting electric modes such as batteries, electronic speed controllers and the like to supply power and provide power for the rotation of the rotors (21); and the unmanned flight equipment has the characteristics of long duration and strong loading capacity.

Abstract translation: 本发明公开了一种多轴动力源无人飞行器，属于无人机技术领域。 该多轴动力源无人飞行器包括机架（1），多个转子组（2）和动力装置（3）。 多个转子组（2）可转动地固定在机架（1）上，动力装置（3）分别与每个转子组（2）对应活动连接。 动力装置（3）为具有油驱特性的无人飞行装备提供动力，通过燃烧预先注入动力装置（3）中的燃烧材料产生机械动能，并且每个转子（21）中的转子 驱动与动力装置对应连接的转子组（2）旋转，从而代替采用电池，电子调速器等电动模式的传统电动多旋翼无人机结构为旋转动力提供动力并提供动力 的转子（21）; 无人飞行器具有持续时间长，载重能力强的特点。

公开(公告)号：EP3181449B1

公开(公告)日：2019-06-12

申请号：EP16201250.4

申请日：2016-11-29

Applicant: Ewatt Technology Co.

Inventor： ZHAO, Guocheng ,  FAN, Hui ,  CHEN, Fangfang

IPC: B64C39/02 ,  B64C27/00 ,  B64C27/32

公开(公告)号：EP3147210B1

公开(公告)日：2018-11-14

申请号：EP16190742.3

申请日：2016-09-27

Applicant: Ewatt Technology Co., Ltd.

Inventor： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

IPC: B64C27/04 ,  B64C27/82 ,  B64C39/02 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08

CPC classification number: B64D33/02 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/141 ,  B64C2201/146 ,  B64D27/08 ,  B64D33/06 ,  B64D33/08 ,  B64D2033/0246 ,  B64D2033/028

Abstract: The present invention discloses an unmanned helicopter, and belongs to the technical field of unmanned aerial vehicles. The unmanned helicopter includes an air inlet system, an exhaust system, a cooling system and a dynamic balance system. The air inlet system is fixed on a second side; the exhaust system is fixed on a third side; and the cooling system is fixed on a first side, and the dynamic balance system is fixed on a tail. The airflow at the outside of the unmanned helicopter flows into the air inlet system smoothly, quickly and efficiently under the action of its own flow velocity relative to the unmanned helicopter, therefore the technical problem in the prior art that the air entering the fuselage with a unit volume is burnt insufficiently, which generates adverse effects on the normal flight of the unmanned helicopter, is solved.

公开(公告)号：EP3181449A2

公开(公告)日：2017-06-21

申请号：EP16201250.4

申请日：2016-11-29

Applicant: Ewatt Technology Co.

Inventor： ZHAO, Guocheng ,  FAN, Hui ,  CHEN, Fangfang

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C27/32 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/20

Abstract: The present invention discloses a multi-rotor structure applied to an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle includes a fuselage, first rotors, second rotors and rotor shafts; and the multi-rotor structure includes first rotary connecting pieces and second rotary connecting pieces. The first rotary connecting piece includes a first motor (41) and a first dismounting thread group, the first rotor (21) is detachably connected with the first motor through the first dismounting thread group to achieve the mounting or dismounting between the first rotor and the first motor by rotating the first rotor; the second rotary connecting piece includes a second motor and a second dismounting thread group, and the second rotor is detachably connected with the second motor through the second dismounting thread group to achieve the mounting or dismounting between the second rotor and the second motor by rotating the second rotor. The present invention has the advantages of being fast, portable and high in working efficiency.

Abstract translation: 本发明公开了一种应用于无人机的多转子结构，属于无人驾驶飞行器技术领域。 无人机包括机身，第一转子，第二转子和转子轴; 并且多转子结构包括第一旋转连接件和第二旋转连接件。 第一旋转连接件包括第一电动机（41）和第一拆卸螺纹组，第一转子（21）通过第一拆卸螺纹组与第一电动机可拆卸地连接，以实现第一转子和第二转子之间的安装或拆卸 第一电机通过旋转第一转子; 所述第二旋转连接件包括第二电动机和第二拆卸螺纹组，所述第二转子通过所述第二拆卸螺纹组与所述第二电动机可拆卸地连接，以通过旋转所述第二转子和所述第二电动机来实现所述第二转子和所述第二电动机之间的安装或拆卸 第二转子。 本发明具有快速便携，工作效率高的优点。

公开(公告)号：EP3147210A3

公开(公告)日：2017-05-10

申请号：EP16190742.3

申请日：2016-09-27

Applicant: Ewatt Technology Co., Ltd.

Inventor： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

IPC: B64C27/04 ,  B64C27/82 ,  B64C39/02 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08

CPC classification number: B64D33/02 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/141 ,  B64C2201/146 ,  B64D27/08 ,  B64D33/06 ,  B64D33/08 ,  B64D2033/0246 ,  B64D2033/028

Abstract: The present invention discloses an unmanned helicopter, and belongs to the technical field of unmanned aerial vehicles. The unmanned helicopter includes an air inlet system, an exhaust system, a cooling system and a dynamic balance system. The air inlet system is fixed on a second side; the exhaust system is fixed on a third side; and the cooling system is fixed on a first side, and the dynamic balance system is fixed on a tail. The airflow at the outside of the unmanned helicopter flows into the air inlet system smoothly, quickly and efficiently under the action of its own flow velocity relative to the unmanned helicopter, therefore the technical problem in the prior art that the air entering the fuselage with a unit volume is burnt insufficiently, which generates adverse effects on the normal flight of the unmanned helicopter, is solved.

Abstract translation: 本发明公开了一种无人直升机，属于无人机技术领域。 无人直升机包括进气系统，排气系统，冷却系统和动态平衡系统。 进气系统固定在第二侧， 排气系统固定在第三侧， 冷却系统固定在第一侧，动平衡系统固定在尾部。 无人直升机外侧的气流在相对于无人直升机自身流速的作用下平稳，快速，有效地流入进气系统，因此现有技术中空气进入机身的技术问题 解决了单位体积燃烧不足，对无人直升机正常飞行造成不利影响的问题。