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Distributed power tilting rotor unmanned aerial vehicle and control method thereof

A technology of tilt-rotor and control method, applied in the field of unmanned aerial vehicle, can solve the problems of difficult optimal power matching, aerodynamic instability, difficult control, etc. Effect

Active Publication Date: 2019-10-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

[0003] Tilting rotorcraft has always been a research hotspot at home and abroad. It faces technical problems such as complex aerodynamic characteristics and difficult control: there is a large gap between engine power requirements in vertical take-off and fixed-wing flight modes, and it is difficult to achieve optimal power matching; at the same time, synchronous tilting The resulting aerodynamic instability also makes the gyroplane difficult to control

Method used

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  • Distributed power tilting rotor unmanned aerial vehicle and control method thereof
  • Distributed power tilting rotor unmanned aerial vehicle and control method thereof
  • Distributed power tilting rotor unmanned aerial vehicle and control method thereof

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Embodiment Construction

[0050] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0051] Such as figure 1 As shown, a distributed power tilt-rotor UAV includes a fuselage 1, a wing 2 and a V-shaped tail 3. It also includes a first rotor system 4 on the wing and a second rotor system 5 on the tail.

[0052] Such as figure 2 As shown, the first rotor system includes four tilting rotors arranged on the wing and a tilting mechanism for tilting, including a motor 5, a blade 6 and a tilting motor 7.

[0053] This embodiment adopts a preferred technical solution, each tilting mechanism has a limit device, within the range of 0-90°, figure 2 The left and right are the schematic diagrams with the tilt angles of 0 and 90° respectively.

[0054] This embodiment adopts a preferred technical solution to overlap the rotation axis of the rotor in the first rotor system with the center of gravity axis of the drone, and the center of gravity o...

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Abstract

The invention discloses a distributed power tilting rotor unmanned aerial vehicle and a control method thereof. The distributed power tilting rotor unmanned aerial vehicle includes a first rotor system disposed on wings and a second rotor system disposed at a V-shaped empennage; the first rotor system includes four tilting rotors, and the four tilting rotors are disposed in pairs on a left wing and a right wing; and the second rotor system includes two rotors, and the two rotors are respectively disposed on both sides of the V-shaped wing. The control method of the unmanned aerial vehicle includes a rotor modal control law, a fixed-wing modal control law, and a transition mode control strategy. The distributed power tilting rotor unmanned aerial vehicle and the control method thereof can achieve optimal power matching of a power system, and also provide robust and reliable control for each of states of a rotorcraft.

Description

Technical field [0001] The invention belongs to the technical field of drones, and particularly relates to a tilt-rotor drone. Background technique [0002] Tilt-rotor aircraft can not only take off and land vertically and hover in the air like a helicopter, but also can fly with a fixed wing like a fixed wing. It has the characteristics of high efficiency, fast speed and long range. Therefore, the tilt rotor aircraft has a wide range of application prospects. [0003] Tilt-rotor aircraft has always been a research hotspot at home and abroad, facing technical problems such as complex aerodynamic characteristics and difficult control: the engine power requirements in vertical take-off and fixed-wing flight modes are very different, and it is difficult to achieve optimal power matching; at the same time, synchronous tilting The resulting aerodynamic instability also makes the rotorcraft difficult to control. [0004] Therefore, the field still needs to study a new tilt-rotor aircraft...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/52B64C27/22B64C19/00G05B13/04
CPCB64C19/00B64C27/22B64C27/52G05B13/042
Inventor 李康一曾旭王新华岳凤玉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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