Layout and control method of a distributed power tilt-wing aircraft

A tilting wing, distributed technology, applied in the aviation field, can solve problems such as aerodynamic interference mode conversion control reliability

Active Publication Date: 2021-07-06
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a layout and control method of a distributed power tilting wing aircraft, to solve the problem of aerodynamic interference between the rotor and the wing and the problem of the reliability of the mode conversion control. The excellent controllability of the propulsion system and the vertical take-off and landing capability of the tilting wing aircraft are well combined to form a brand-new model scheme.

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  • Layout and control method of a distributed power tilt-wing aircraft
  • Layout and control method of a distributed power tilt-wing aircraft
  • Layout and control method of a distributed power tilt-wing aircraft

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Embodiment Construction

[0052] The present invention will be described in further detail below in conjunction with the accompanying drawings. These drawings are all simplified schematic diagrams, which only illustrate the basic structure of the present invention in a schematic manner, so they only show the configurations related to the present invention.

[0053] As shown in Figure 1, a layout of a distributed power tilting wing aircraft includes a fuselage 1, a front canard 2, a wing main wing 3, a front canard elevator 4, a wing aileron 5, and a forward tilting shaft 6. Rear tilt shaft 7, power system 8, vertical stabilizer 9.

[0054] The fuselage 1 is the main load-carrying part of the effective transport load of the aircraft, and plays the role of connecting various parts; Wing 5 provides the steering moment in level flight, the front canard elevator 4 provides the pitching moment, and the wing aileron 5 provides the rolling moment; the forward-tilt shaft 6 and the rear-tilt shaft 7 connect the...

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Abstract

The invention discloses a layout and control method of a distributed power tilting wing aircraft. The canard layout aircraft is selected, and a plurality of engines are installed inside the front canard and the main wing of the wing to realize the distributed power; before the vertical take-off state The front canard and the main wing of the wing are tilted to be vertical, and the eight engines generate pulling force to lift the body off the ground, and at the same time, the differential work corrects the attitude of the body; Throttle dynamic adjustment; when the forward flight speed is sufficient to make the lift generated by the front canard and the main wing of the wing offset the gravity, the front canard and the main wing of the wing completely turn to the level, enter the high-speed level flight state, and realize hanging and hovering to The conversion of level flight; the conversion process of level flight, hovering and landing is exactly the opposite. The power system of the present invention is simple to set up, and a locking mechanism is provided; the control of the present invention is direct and reliable, and the tilting mechanism and attitude control are separated to avoid the failure of multiple functions caused by one system failure.

Description

technical field [0001] The present invention relates to a layout and control method of a distributed power tilting wing aircraft, and relates to a layout scheme of a vertical take-off and landing aircraft based on tilting wing technology and its modes of vertical take-off and landing, hovering, and level flight. and the control method for switching between modes. It belongs to the field of aviation technology. Background technique [0002] In recent years, vertical take-off and landing aircraft is very popular in both military and civilian fields. After the U.S. wars against Iraq and Afghanistan ended, the U.S. paid more and more attention to the development of vertical take-off and landing aircraft, and gave it the top ten categories of future key equipment for the U.S. military. Its ability to adapt to complex terrain and environments is what the US military values. The rest of the countries are also catching up with the pace of the United States, putting more energy in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C29/00B64C27/26B64C27/28
CPCB64C27/26B64C27/28B64C29/0033
Inventor 周尧明苏雨赵浩然陈旭智
Owner BEIHANG UNIV
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