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Method and device for controlling multi-rotor wing variable pitch aircraft

A variable-pitch aircraft and control method technology, applied in the field of aerial photography, can solve the problems of short motor life and insensitive response, and achieve the effect of soft load changes and fast speed

Active Publication Date: 2014-07-23
徐州博创建设发展集团有限公司
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The object of the present invention is to provide a control method and control device for a multi-rotor pitch-variable aircraft to solve the technical problems of short motor life and insensitive response of unmanned aircraft motors in the prior art

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  • Method and device for controlling multi-rotor wing variable pitch aircraft
  • Method and device for controlling multi-rotor wing variable pitch aircraft
  • Method and device for controlling multi-rotor wing variable pitch aircraft

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Embodiment Construction

[0031] The technical solutions in the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0032] This case involves a variable-pitch multi-axis aircraft. On the one hand, a motor can simultaneously drive multiple rotors to rotate synchronously. On the other hand, the pitch of each rotor is variable. The structure is described in detail below by way of examples.

[0033] ginseng figure 1 As shown, the variable-pitch aircraft includes a frame 10 , a drive system 20 and a variable-pitch rotor 30 mounted on the frame.

[0034] The support 10 is a supp...

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Abstract

The invention discloses a device for controlling a multi-rotor wing variable pitch aircraft. The aircraft comprises a main body part and a rotor wing component used for driving the main body part, wherein the rotor wing component comprises a first rotor wing and a second rotor wing which are arranged alternately; the device for controlling the multi-rotor wing variable pitch aircraft comprises a first control rod; the control rod is used for controlling the screw pitch of the first rotor wing to be increased along the first moving direction and the screw pitch of the second rotor wing to be reduced; the first control rod is also used for controlling the screw pitch of the first rotor wing to be reduced along the second moving direction and the screw pitch of the second rotor wing to be increased. The invention also discloses a method for controlling the multi-rotor wing variable pitch aircraft. Compared with an existing multi-rotor wing aircraft driven by multiple motors, the multi-rotor wing variable pitch aircraft brings softer load change to motors when doing spinning action, and is relatively rapid and relatively accurate in spinning action execution speed. Furthermore, compared with a traditional scheme that the spinning action is driven by the multiple motors, the device and the method do not need to frequently change the rotating speeds of all the motors, so that more electricity can be saved.

Description

technical field [0001] The application belongs to the field of aerial photography, and in particular relates to a control method and a control device for a multi-rotor pitch-variable aircraft. Background technique [0002] Each axis of the multi-axis aircraft in the existing technical solution is composed of a corresponding propeller and a motor driving the corresponding propeller. The attitude maintenance and maneuvering action of the aircraft flight is to control the speed of each motor separately through the flight control system (the rotation directions of the various motors of the existing multi-axis aircraft are in pairs to counteract the spin torque) to achieve the attitude and action control of the aircraft of. The attitude of the vertical take-off and landing aircraft includes level and tilt. Maneuvering actions include level flight, ascent, descent, and spin (around its own Z axis, that is, the vertical axis of the horizontal plane of the body structure). The as...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/80
CPCB64C27/605B64U10/14B64U50/27B64U30/296B64U2101/30
Inventor 杨华东吴奇才赵江
Owner 徐州博创建设发展集团有限公司
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