Control method and control device for pitch-variable aircraft

A technology of a variable-pitch aircraft and a control device, applied in the field of aerial photography, can solve the problems of insensitive response during the spin process of the unmanned aerial vehicle, and achieve the effect of soft change of motor load and high efficiency

Active Publication Date: 2016-04-20
江苏謇公湖农业科技发展有限责任公司
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  • Abstract
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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 problem of insensitive response during the spin process of unmanned aircraft in the prior art

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  • Control method and control device for pitch-variable aircraft
  • Control method and control device for pitch-variable aircraft

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Embodiment Construction

[0022] 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.

[0023] 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 through preferred embodiments.

[0024] ginseng figure 1 As shown, the variable-pitch aircraft includes a frame 10 , a drive system 20 and a variable-pitch rotor 30 installed on the frame.

[0025] The support...

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Abstract

A control apparatus and control method for a variable-pitch aerial vehicle. The control apparatus comprises a first control rod. The first control rod, in a first state, controls simultaneous increase in the pitch of rotors and the rotational speed of a motor of the aerial vehicle. The first control rod, in a second state, controls simultaneous reduction in the pitch of the rotors and the rotational speed of the motor of the aerial vehicle. When the aerial vehicle needs to increase pitch for climbing, a flight controller controls the motor to increase correspondingly the rotational speed for increased torque at a certain proportion. This mode provides relatively high efficiency, moderate sensitivity, and easy control.

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 Patents(China)
IPC IPC(8): B64C27/80
CPCB64C27/08B64C27/78
Inventor 杨华东吴奇才赵江
Owner 江苏謇公湖农业科技发展有限责任公司
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