Turnable multi-rotor wing double-body duck type arranged unmanned aerial vehicle

A technology of unmanned aerial vehicles and dual fuselages, which is applied to aircrafts, canard planes, motor vehicles, etc., to achieve the effects of simple control, high hovering efficiency, and improved propulsion efficiency in level flight

Inactive Publication Date: 2018-03-20
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although vertical take-off and landing aircraft have been widely used for a long time, new designs of vertical take-off and landing aircraft have long been unable to guarantee the increase of flight speed without sacrificing range, efficiency and operation ability

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  • Turnable multi-rotor wing double-body duck type arranged unmanned aerial vehicle
  • Turnable multi-rotor wing double-body duck type arranged unmanned aerial vehicle
  • Turnable multi-rotor wing double-body duck type arranged unmanned aerial vehicle

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Embodiment Construction

[0016] In order to describe the technical content, structural features, achieved goals and effects of the present invention in detail, the following will be described in detail in conjunction with the embodiments and accompanying drawings.

[0017] The most critical idea of ​​this patent is to introduce the aerodynamic layout of twin fuselages and long-distance canards, and introduce the tiltable multi-rotor power system of "Y" layout.

[0018] see figure 1 , figure 2 and Figure 5 , a vertical take-off and landing unmanned aerial vehicle, comprising a pitot tube 1, a photoelectric camera probe 2, a canard 3, a canard deflection rudder 4, 5, a radar 5, a landing gear 6, a left and right fuselage 8, 9, and a flight control computer 10. Main propulsion propeller tilting device 11, coaxial double propeller 12, main wing 13, vertical tail deflection rudder 14, main wing deflection rudder 15, tail thruster inlet 16, tail propeller 17, tail thruster 18 , the left and right verti...

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Abstract

The invention relates to an unmanned aerial vehicle which takes off and lands down vertically. The unmanned aerial vehicle has pneumatic arrangement of double bodies and remote duck wings, a power system of the unmanned aerial vehicle is composed of four propellers with tilting mechanisms, which are arranged in a 'Y'-shaped manner, variable wings based on flexible structures are adopted as wings of the unmanned aerial vehicle, and a control surface of the unmanned aerial vehicle is of a flexible seamless control surface structure. The unmanned aerial vehicle has the beneficial effects that dueto adoption of a tiltable multi-rotor wing system, vertical lifting and landing down are achieved, and a 'waste weight' caused by a useless power system is avoided in level flight; due to adoption ofthe power system between the two bodies, air flow interference between the propellers and the bodies is avoided; due to adoption of the double bodies, the body rigidity can be improved, and the bodyweight can be reduced; due to adoption of the remote duck wings, the lift coefficient of the whole vehicle is increased, the position of a pneumatic center is adjusted, the rigidity of the vehicle isimproved, and the weight of the vehicle is reduced; due to adoption of the self-adaptive wings based on flexible structures, the pneumatic appearances of the wings are at optimal states constantly; and due to adoption of the flexible seamless control surface, the wings and the control surface are in seamless connection, so that interference resistance is reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an unmanned aerial vehicle for vertical take-off and landing. The aircraft adopts an aerodynamic layout with two fuselages and long-distance canard wings, a pair of coaxial double propeller systems and a power system composed of two single propellers. And a variable wing based on a compliant structure and a flexible seamless rudder surface structure are designed, which can have the characteristics of high hovering efficiency, high-speed forward flight, and vertical take-off and landing. Background technique [0002] Vertical take-off and landing aircraft is an important aircraft category. Although vertical take-off and landing aircraft have been widely used for a long time, new designs of vertical take-off and landing aircraft have long been unable to guarantee the increase of flight speed without sacrificing range, efficiency and operation ability. With the development of tech...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/00B64C39/12
CPCB64C29/00B64C39/12
Inventor 王秦阳田申吴颂平王杰陈垚廖东平
Owner BEIHANG UNIV
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