Fixed-wing vertical take-off and landing aircraft

A vertical take-off and landing, fixed-wing technology, applied in the aviation field, can solve the problems of multi-rotor manned aircraft, such as complex structure, high environmental requirements, and low reliability, so as to avoid physiological discomfort, low environmental requirements, and high reliability Effect

Pending Publication Date: 2022-07-22
浙江大学湖州研究院
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Based on the above description, the purpose of the present invention is to propose a fixed-wing vertical take-off and landing aircraft, which can solve the probl

Method used

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  • Fixed-wing vertical take-off and landing aircraft
  • Fixed-wing vertical take-off and landing aircraft
  • Fixed-wing vertical take-off and landing aircraft

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Embodiment Construction

[0027] The technical solutions of the present invention are described in detail below. The embodiments of the present invention are only for illustrating a specific structure, and the scale of the structure is not limited by the embodiments.

[0028] like Figure 1 to Figure 4 As shown, a vertical take-off and landing fixed-wing aircraft includes a fuselage 100, a rotor module, a control system, a cockpit and a power system. The two sides of the fuselage 100 are respectively provided with a wing 110, and the fuselage 100 is provided with a hatch; there are four rotor modules, which are symmetrically arranged above and below the fuselage 100 to form a V-shaped fuselage layout. , the rotor module is driven by a motor, and each motor is connected to a rotor module to provide driving force; the control system is respectively connected to four motors to adjust the speed and power of each motor to realize the conversion of flight attitude.

[0029] refer to image 3 and Figure ...

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Abstract

The fixed-wing vertical take-off and landing aircraft comprises a fuselage, wings and cabin doors, the wings are arranged on the two sides of the fuselage respectively, the fixed-wing vertical take-off and landing aircraft further comprises four sets of rotor wing modules and a mounting frame, and each rotor wing module comprises a power column and a propeller; the mounting frame is fixed at the tail part of the fuselage and comprises four empennages, and a group of rotor modules are arranged on each empennage; the two empennages extend towards the upper side of the fuselage, and the empennages are opened upwards and arranged in a V shape; the other two rotor wing modules extend towards the lower side of the fuselage, and the empennage opens downwards and is arranged in a V shape; the upwards-opened empennages and the downwards-opened empennages are symmetrically distributed on the upper side and the lower side of the fuselage. The four rotor wing modules form a fuselage layout which is symmetrical along the upper side and the lower side of the fuselage, a runway is not needed, the flight attitude conversion is realized through adjustment of a control system after the aerial state until the level flight state is achieved, and the unmanned aerial vehicle is simple in structure, high in reliability and good in safety.

Description

technical field [0001] The invention relates to the field of aviation, in particular to a fixed-wing aircraft to implement vertical take-off and landing. Background technique [0002] At present, in the field of civil manned navigation, from large civil passenger aircraft to small and medium-sized civil passenger aircraft, the development has been quite complete, and it has become an important means of people's daily travel. In recent years, miniaturized aircraft have become increasingly popular, including small manned fixed-wing aircraft and multi-rotor manned aircraft similar to the V-22 tiltrotor. [0003] But both of the above-mentioned aircraft have their own disadvantages. The disadvantage of small manned fixed-wing aircraft is that it needs an airstrip for take-off and landing, an airport must be built to ensure normal use, and it has high requirements for the use environment. The multi-rotor manned aircraft realizes the attitude adjustment of vertical and horizonta...

Claims

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Application Information

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IPC IPC(8): B64C27/28B64C27/26B64C29/00B64D27/24B64C1/14B64D11/06
CPCB64C27/28B64C27/26B64C29/00B64D27/24B64C1/1423B64D11/0639
Inventor 何云瀚文广为邱炜项军华张育林
Owner 浙江大学湖州研究院
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