Yaw control method for tilting vertical take-off and landing fixed-wing UAV in rotor wing mode

A technology for vertical take-off and landing and yaw control, applied in the field of unmanned aerial vehicles, can solve the problems of unstable horizontal attitude of the aircraft and increase the risk of uncontrolled crash, so as to avoid the instability of the aircraft, solve the large jitter of the aircraft, and realize the heading control. Effect

Inactive Publication Date: 2019-03-01
XIAN LINGKONG ELECTRONICS TECH CO LTD
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  • Abstract
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AI Technical Summary

Problems solved by technology

Since it can be regarded as a quadrotor in the rotor mode, if differential speed control is used, one group of diagonal motor speeds will increase during yaw control, and the speed of the other group will become smaller. When the yaw amount reaches a certain level It will lead to the instability of the aircraft's horizontal attitude and increase the risk of out-of-control crash

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  • Yaw control method for tilting vertical take-off and landing fixed-wing UAV in rotor wing mode
  • Yaw control method for tilting vertical take-off and landing fixed-wing UAV in rotor wing mode
  • Yaw control method for tilting vertical take-off and landing fixed-wing UAV in rotor wing mode

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Embodiment Construction

[0020] The following describes the specific implementation of the present invention in conjunction with the accompanying drawings and examples: It should be noted that the above-mentioned left and right sides are all in the top view, with the plane of symmetry of the aircraft as the reference plane, and the direction from the tail to the nose as the reference direction divided into the left side and right side.

[0021] Such as figure 1 As shown, the yaw control method in the rotor mode of the tilting vertical take-off and landing fixed-wing UAV includes a vertical take-off and landing fixed-wing with a rotor tilting function installed on the fixed-wing wing, wherein the rotor parts are respectively connected for the motor A driven power unit, wherein the rotors on both sides of the front are provided with a tilting device, which is characterized in that the yaw control is realized by controlling the tilting device and four power units, which specifically includes the followin...

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Abstract

The invention discloses a yaw control method for a tilting vertical take-off and landing fixed-wing UAV in a rotor wing mode. The UAV comprises a vertical take-off and landing fixed wing having a rotor wing tilting function and installed on a fixed wing, wherein rotor wing parts are connected to motor-driven power units; the rotor wings on the front two sides are provided with tilting rotation devices. The method is characterized by achieving yaw control by controlling the tilting rotation devices and the four power units, and specifically includes the following steps that the UAV, according to a tilting instruction, rotates the tilting rotation devices by a certain angle of inclination, wherein the tilting rotation device on the tilting direction side tilts forwardly, and the other tilting rotation device tilts backwardly to realize the tilting of the UAV; after the tilting is completed, the tilting rotation devices resume a starting position and the UAV enters a level flight state. The method solves the large jitter of the aircraft which often occurs in the heading control.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a yaw control method for a tilting vertical take-off and landing fixed-wing unmanned aerial vehicle in the rotor mode. Background technique [0002] The tilting four-rotor vertical take-off and landing fixed-wing UAV is a new type of aircraft between the four-rotor and the fixed wing. It can not only meet the requirements of vertical take-off and landing, but also achieve the advantages of fixed-wing long-endurance carrying weight, and has great application value in various remote sensing and telemetry fields such as aerial surveys. [0003] The tilting four-rotor vertical take-off and landing fixed-wing UAV is a new type of aircraft between the four-rotor and the fixed wing. There are three main flight modes of the aircraft: quadrotor mode, transition mode, and fixed-wing mode. Tilting four-rotor vertical take-off and landing fixed-wing UAVs fly in four-rotor ...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/101
Inventor 韩伟毛立尧王宬陈溯邓修涛
Owner XIAN LINGKONG ELECTRONICS TECH CO LTD
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