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Multi-axis manned aircraft

A technology of aircraft and rotor, applied in the field of multi-axis manned aircraft, can solve the problems of single application and easy damage of multi-axis manned aircraft, and achieve the effects of low production cost, weight reduction and stable structure

Inactive Publication Date: 2015-12-16
SUN HAWK HENAN AVIATION IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a multi-axis manned aircraft with a large load, long endurance, and various applications, so as to solve the technical problem that the existing multi-axis manned aircraft is applicable to a single and easily damaged

Method used

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Embodiment 1

[0049] Such as figure 1 The structural representation of the multi-axis manned aircraft provided by the invention, figure 2 As shown in the schematic structural view of the rotor device of the multi-axis manned aircraft provided by the present invention, the multi-axis manned aircraft is characterized in that it includes a frame 1 and a power unit 4 and a transmission device 42 installed on the frame 1 , rotor device 2, pitch changing device, seat 5 and control device 6, wherein,

[0050] The transmission device 42 connects the power device 4 and the rotor device 2;

[0051] The rotor device 2 includes a rotor head 21 and a propeller 22, the rotor head 21 is symmetrically installed on the frame 1, the propeller 22 is installed on the rotor head 21, the rotor head 21 and the propeller 22 The number of is at least three groups;

[0052] The pitch changing device, the pitch changing device is connected to the rotor device 2;

[0053] The seat 5 and the operating device are c...

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Abstract

The invention discloses a multi-axis manned aircraft. The multi-axis manned aircraft comprises a rack, a power device, a transmission device, rotor wing devices, a pitch varying device, a seat and a control device, wherein the power device, the transmission device, the rotor wing devices, the pitch varying device, the seat and the control device are arranged on the rack. The transmission device is connected with the power device and the rotor wing devices. Each rotor wing device comprises a rotor wing head and a propeller. The rotor wing heads are symmetrically installed on the rack. The propellers are installed on the rotor wing heads. The number of the rotor wing heads and the propellers is at least three sets. The pitch varying device is connected with the rotor wing devices. The seat and an operating device are correspondingly arranged in the middle of a rack structure. The power device is connected with the rotor wing devices. The control device is connected with the power device, the rotor wing devices and the operating device. Operation is easier and more convenient in the flying process. An operator can easily handle various flight states. The multi-axis manned aircraft is simple in structure and achieves complete functions.

Description

technical field [0001] The present application relates to a multi-axis manned aircraft. Background technique [0002] At present, traditional helicopters have a single rotor with a tail rotor layout, relying on the rotation of the main rotor to provide lift, and the high-speed rotation of the tail rotor generates a lateral push-pull force, which is used to overcome the counter torque generated by the main rotor. This layout is simple in structure and mature in technology, and can be flexibly used to manufacture helicopters of various specifications, and its operation is relatively simple. However, the tail boom leads to a large parking area, the carrying tail boom and the long-distance tail rotor drive shaft are easily damaged, the risk of collision is high, the hovering performance is unstable, and the tail rotor is easily damaged by foreign objects, causing major accidents, and the tail rotor needs to be consumed. 15% or so of engine power. [0003] In addition to single...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C31/00B64C27/02B64C11/44
CPCB64C11/44B64C27/08B64C31/00B64U50/11B64U10/14B64U10/11B64U50/20B64U2201/10
Inventor 陶亮申守健秦立新
Owner SUN HAWK HENAN AVIATION IND CO LTD
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