Non-co-axial multi-rotor aircraft and attitude control method thereof

A technology for a multi-rotor aircraft and a flight control system, applied in the field of aircraft and multi-rotor aircraft attitude control, can solve the problems of single driving mode, small aircraft load, short flight time, etc.

Inactive Publication Date: 2013-03-06
XIAN WIDE WORLD ZENITH AVIATION TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the technical problems of the current multi-rotor aircraft to control the attitude of the aircraft by changing the rotor speed, such as single driving mode, small aircraft load, and short flight time, the present invention provides a multi-rotor aircraft and its attitude control method

Method used

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  • Non-co-axial multi-rotor aircraft and attitude control method thereof
  • Non-co-axial multi-rotor aircraft and attitude control method thereof
  • Non-co-axial multi-rotor aircraft and attitude control method thereof

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Embodiment Construction

[0059] A multi-rotor aircraft, including a body, a flight control system, a power drive system installed on the body, and 2N rotor assemblies, wherein N≥2, the rotor assemblies are installed above the body and evenly distributed on the circumference centered on the frame .

[0060] The power transmission mechanism includes a power distribution mechanism and a reversing mechanism arranged between the reduction mechanism and the rotor assembly, the number of the power distribution mechanism is consistent with the number of the rotor assembly, and the number of the reversing mechanism is half of the number of the rotor assembly; the power distribution mechanism is in accordance with The attitude control signal of the flight control system distributes the power output by the deceleration mechanism directly to the corresponding rotor assembly or redistributes it to the adjacent rotor assembly through the reversing mechanism.

[0061] The reduction mechanism is used to reduce the outp...

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Abstract

The present invention relates to a non-co-axial multi-rotor aircraft, which comprises an aircraft body, a power system, a transmission system, a flying control system, and 2N rotor components, wherein N is more than or equal to 2, the power system drives the rotor component to rotate through the transmission system, the flying control system controls the power system to work, every rotor component comprises a rotor and a blade pitch driving mechanism for changing a rotor blade pitch, the flying control system is provided for controlling works of every blade pitch driving mechanism, the transmission system comprises N forward direction transmission mechanisms and N reverse direction transmission mechanisms, the forward direction transmission mechanisms and the reverse direction transmission mechanisms are sequentially and staggedly distributed, and the power system drives the rotors of the N rotor components to rotate along the same direction through the N forward direction transmission mechanisms. With the present invention, technical problems of single driving manner, low aircraft load, short flying time and the like due to application of rotor rotation speed changing to control an aircraft attitude by the existing multi-rotor aircraft are solved.

Description

technical field [0001] The invention belongs to the technical field of aviation products, and relates to a multi-rotor aircraft attitude control method and an aircraft using the method. Background technique [0002] The control method of the multi-rotor aircraft on the market is to control the attitude of the aircraft by changing the rotor speed. Such a control method has the following defects: [0003] 1. Most of its rotor drive methods are suitable for motor drive, and it is not easy to design and manufacture heavy-duty, long-endurance multi-rotor aircraft. [0004] 2. It is not easy to use the control of the drive mode other than motor drive, such as fuel drive. Contents of the invention [0005] In order to solve the technical problems of the current multi-rotor aircraft to control the attitude of the aircraft by changing the rotor speed, such as single driving mode, small aircraft load, and short flight time, the present invention provides a multi-rotor aircraft and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/02B64C11/30B64D35/04
Inventor 王辉
Owner XIAN WIDE WORLD ZENITH AVIATION TECH
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