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Novel aircraft and control method thereof

An aircraft, a new type of technology, is applied in the field of drones to achieve the effect of reducing complexity, compact structure, and simplified structure

Pending Publication Date: 2019-11-08
李泽波
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a highly simplified novel aircraft, solve the yaw problem of the existing odd-wing aircraft with the lowest possible cost, and realize its stability and controllability, so as to achieve low cost, low energy consumption, stable Breakthroughs in sex and security

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  • Novel aircraft and control method thereof
  • Novel aircraft and control method thereof
  • Novel aircraft and control method thereof

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Embodiment Construction

[0060] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0061] It should be noted that the specific dimensions and specifications appearing below, including length, height, distance, angle, etc., specific quantities and specific materials are all feasible methods provided for the convenience of specific implementation, and they can be adjusted according to actual needs .

[0062] It should be understood that the structural design described in the present invention is to serve functions. In the case of satisfying the basic functions, different structural designs can be used according to different usage scenarios. A str...

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Abstract

The invention provides a novel aircraft and a control method thereof, and belongs to the technical field of unmanned aerial vehicles. The novel aircraft comprises a fuselage, wings and rotor wings. The wings are evenly distributed on the periphery of the fuselage. The rotor wings are fixed to the tail ends of all the wings through motor bases. The novel aircraft rotates steadily around the centralaxis during flight, and additional lift is provided through the wings. Through the control method provided by the invention, control over the other five degrees of freedom is achieved when the aircraft yaws and is unstable.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and more specifically relates to a structure and a control method of a novel spinner. Background technique [0002] Among the multi-rotor aircraft currently on the market, the development of the quad-rotor and the hexa-rotor is the most mature. The aircraft with an even number of rotors can control the attitude and position of the aircraft through the change of the thrust of the motor, and balance the moments. In contrast, trirotor aircraft has the advantages of compact structure, less consumables, good controllability, etc., and generally consumes less energy and is low in cost, and is especially suitable for the production of micro aircraft. However, the torque problem of the trirotor has not been well resolved. [0003] At present, there are few studies on trirotor aircraft at home and abroad, and they mainly focus on intelligent control research, nonlinear robust control re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22B64C27/32
CPCB64C27/22B64C27/32
Inventor 李泽波方潮铭王轶轩黄戈莹高铭张雨浓
Owner 李泽波
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