Vertical take-off and landing aircraft with double ducted fans

A ducted fan and vertical take-off and landing technology, which is applied in the field of drones, can solve the problems of complex structure, poor aerodynamic efficiency, and large energy consumption, and achieve the effects of reducing moment of inertia, high aerodynamic efficiency, and good noise shielding

Active Publication Date: 2020-12-01
CIVIL AVIATION UNIV OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the present invention aims to propose a dual-duct fan vertical take-off and landing aircraft to solve the problems of complex body structure, poor aerodynamic efficiency, high noise, and large energy consumption.

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  • Vertical take-off and landing aircraft with double ducted fans
  • Vertical take-off and landing aircraft with double ducted fans
  • Vertical take-off and landing aircraft with double ducted fans

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Embodiment Construction

[0037] It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0038] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention Creation and simplification of description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the invention. In addition, the terms "first", "second", etc. are used for descriptive purposes only, and should no...

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Abstract

The invention provides a vertical take-off and landing aircraft with double ducted fans. The vertical take-off and landing aircraft comprises a front fuselage, two tilting mechanisms symmetrically installed on the front fuselage, and ducted fans rotationally connected with the front fuselage through the tilting mechanisms. The front fuselag comprises two sets of front fuselag frames, tilting mechanism installation positions are arranged on the two sets of front fuselag frames respectively, the two sets of tilting mechanisms are installed on the tilting mechanism installation positions respectively, each tilting mechanism comprises a tilting shaft, one end of each tilting shaft is rotationally connected with the corresponding tilting mechanism, and the other end of each tilting shaft is fixedly connected with the corresponding ducted fan. According to the vertical take-off and landing aircraft with the double ducted fans, compared with fixed wings, the ducted fan unmanned aerial vehiclehas the advantages of being high in aerodynamic efficiency, compact in vehicle body structure, high in safety coefficient, simple in control mode, good in noise shielding performance and the like.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a dual-duct fan vertical take-off and landing aircraft. Background technique [0002] Traditional unmanned aerial vehicles, generally including unmanned helicopters, fixed-wing aircraft, multi-rotor aircraft and other aircraft, have the disadvantages of complex body structure, poor aerodynamic efficiency, high noise, and high energy consumption, while ducted unmanned aerial vehicles have traditional unmanned aerial vehicles. Man-machine incomparable advantages, such as good maneuverability, compact body structure, high aerodynamic efficiency, good noise shielding and so on. At present, it is precisely because of the above advantages that ducted UAVs have increasingly become a new research direction in the field of UAVs. Under the premise that the diameter of the propeller is the same and the pitch is the same, the ducted power device will generate so...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/00B64C27/20B64C27/32B64C27/52
CPCB64C29/00B64C27/20B64C27/32B64C27/52
Inventor 肖海建卢翔单泽众单金洋田明辉姜番王卓曹馨月陈茜
Owner CIVIL AVIATION UNIV OF CHINA
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