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A kind of distributed power tilt rotor unmanned aerial vehicle and its control method

A technology of tilt rotor and control method, which is applied in the field of unmanned aerial vehicles, can solve problems such as difficult optimal power matching, aerodynamic instability, and difficult control, and achieve the goal of improving flight safety and flight quality, flexible tasks, and high speed Effect

Active Publication Date: 2020-12-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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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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  • A kind of distributed power tilt rotor unmanned aerial vehicle and its control method
  • A kind of distributed power tilt rotor unmanned aerial vehicle and its control method
  • A kind of distributed power tilt rotor unmanned aerial vehicle and its control method

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Embodiment Construction

[0050] The technical solutions 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, wings 2 and a V-shaped tail 3. It also includes a first rotor system 4 arranged on the wing and a second rotor system 5 at the empennage.

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

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

[0054] This embodiment adopts an optimal technical solution, and the rotation axis of the rotor in the first rotor system coincides with the axis of the center of g...

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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 unmanned aerial vehicles, and in particular relates to a tilting-rotor unmanned aerial vehicle. Background technique [0002] Tilt rotor aircraft can not only take off and land vertically like a helicopter, hover in the air, but also fly fast like a fixed wing. It has the characteristics of high efficiency, fast speed and long range. Therefore, the tilt rotor aircraft has a wide application prospect. [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. [0004] Therefore, there is still a need in this f...

Claims

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Application Information

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Patent Type & Authority Patents(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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