CN114771823A

CN114771823A - Fixed wing VTOL aircraft

Info

Publication number: CN114771823A
Application number: CN202210412800.9A
Authority: CN
Inventors: 何云瀚; 文广为; 邱炜; 项军华; 张育林
Original assignee: Huzhou Institute of Zhejiang University
Current assignee: Huzhou Institute of Zhejiang University
Priority date: 2022-04-19
Filing date: 2022-04-19
Publication date: 2022-07-22

Abstract

A fixed-wing vertical take-off and landing aircraft comprises an aircraft body, wings and a cabin door, wherein two sides of the aircraft body are respectively provided with one wing; the mounting frame is fixed at the tail part of the aircraft body and comprises four tail wings, and each tail wing is provided with a group of rotor wing modules; the two tail wings extend towards the upper side of the machine body, and the tail wings are upwards opened to form a V shape; the other two rotor wing modules extend towards the lower side of the fuselage, and the empennage is arranged in a V shape by stretching downwards; the tail wings which are opened upwards and the tail wings which are opened downwards are symmetrically distributed on the upper side and the lower side of the machine body. The four rotor modules form a symmetrical fuselage layout along the upper side and the lower side of the fuselage, a runway is not needed, the flight attitude is converted by adjusting a control system after flight until a level flight state is achieved, and the four rotor modules are simple in structure, high in reliability and good in safety.

Description

Fixed wing VTOL aircraft

Technical Field

The invention relates to the field of aviation, in particular to a fixed wing aircraft for implementing vertical take-off and landing.

Background

At present, in the civil passenger navigation field, large-scale civil airliners to small-scale and medium-scale civil airliners have been developed quite well and become an important daily travel means for people. In recent years, miniaturized aircrafts have been increasingly developed, including small manned fixed-wing aircrafts and also multi-rotor manned aircrafts like V-22 tilt-rotor aircrafts.

Both of the above mentioned aircraft have their own disadvantages. The small manned fixed wing aircraft has the defects that the aircraft runway is required to take off and land, an airport is required to be built to ensure normal use, and the requirement on the use environment is high. Many rotors manned vehicle realizes the attitude adjustment that the vertical rotation is flat flies through verting that changes the rotor, need install the mechanism of verting on the rotor, and the structure is complicated, and the reliability is low, has certain potential safety hazard.

Disclosure of Invention

Based on the above description, the invention aims to provide a fixed-wing vertical take-off and landing aircraft, which can solve the problems that the existing small manned fixed-wing aircraft has high requirements on the use environment, and a multi-rotor manned aircraft has a complex structure and low reliability.

The adopted technical scheme is as follows:

a fixed wing vertical take-off and landing aircraft comprises an aircraft body, wings and a cabin door, wherein two sides of the aircraft body are respectively provided with one wing, the fixed wing vertical take-off and landing aircraft is characterized by comprising four groups of rotor wing modules and a mounting rack,

each group of rotor wing modules comprises a power column, a propeller and a driving device;

the afterbody at the fuselage is fixed to the mounting bracket, including four fin, sets up a set of rotor module on every fin.

The two tail wings extend towards the upper side of the machine body and are arranged in a V shape, and the upward opening angle of the tail wings is 90-150 degrees, preferably 122 degrees.

The other two tail wings extend towards the lower side of the machine body and are arranged in a V shape, and the downward opening angle of the tail wings is 90-150 degrees, preferably 122 degrees.

The two upwards-opened tail wings and the two downwards-opened tail wings are symmetrically distributed up and down, so that differential control is realized, the flight attitude can be freely adjusted, and the vertical tail wing and the horizontal tail wing have the characteristics of a vertical tail wing and a horizontal tail wing, namely, the vertical tail wing and the horizontal tail wing have two capabilities of generating vertical lift force and adjusting the horizontal flight attitude.

A drive means is mounted within the power column to drive the propeller. The power columns are arranged on the tail wings and are parallel to the central axis of the machine body. The tail end of the power column extends to the outside of the tail and is positioned on the same vertical plane to be used as a landing support point. The tail end of the power column is also provided with a damping device.

The propeller is arranged at the front end of the power column and is positioned on the same vertical plane.

The cabin door comprises an upper cabin door and a lower cabin door which can be opened and closed, and the inner side of the lower cabin door is provided with a stair; the upper door is opened upwards, and the lower door is opened downwards.

The seat is rotated more than 60 degrees.

The fixed-wing aircraft further comprises a control system, a cockpit and a power system.

Control system connects the drive device of four rotor modules respectively, adjusts the control plane in order to realize the conversion of flight attitude on the rotational speed power of each rotor module and wing, the fin.

The cabin is positioned in the fuselage, and a rotatable seat is arranged in the cabin; the rotation axis of the seat is parallel to the horizontal central axis of the cabin.

The power system is arranged in the fuselage or the wings, the power system respectively provides power for the four groups of rotor wing modules, and the power system is respectively connected with the driving device. The driving device is any one of a matching motor or an internal combustion engine and is arranged in the power column; each driving device is respectively connected with one rotor module to provide driving force.

Further, the power system is respectively connected with power ends of the motors to provide power; the power supply end is one of a storage battery or a fuel cell or fuel oil.

According to the invention, the upper side and the lower side of the fuselage are in V-shaped symmetrical fuselage layout through the four rotor wing modules, and the four damping devices on the rotor wing modules are grounded; when taking off, the power system provides power for four rotor modules, the power generated by control takes off vertically without a runway, the requirement on the use environment is low, the control system adjusts the rotating speed power of each motor to realize the conversion of the flight attitude after flying, the aircraft body is gradually tilted until the aircraft wing is in a flat flight state, namely a fixed wing, and a tilting mechanism is not required to be installed on the rotor modules, so that the aircraft has the advantages of simple structure, high reliability and good safety. And the seat in the cabin can rotate in a self-adaptive manner according to the adjustment of the posture of the aircraft in the flying process, so that the passengers can always keep the horizontal sitting posture, the physiological discomfort caused by the change of the sitting posture is avoided, and the riding comfort level is improved.

Drawings

FIG. 1 is a perspective view of a fixed-wing VTOL aerial vehicle in an embodiment of the present invention;

FIG. 2 is an elevation view of an aircraft in a vertical flight configuration in accordance with an embodiment of the present invention;

FIG. 3 is a side perspective view of the aircraft in a vertical flight configuration in accordance with an embodiment of the present invention;

FIG. 4 is a top view of the aircraft in a horizontal flight configuration in accordance with an embodiment of the present invention;

FIG. 5 is a side perspective view of an aircraft in a level flight configuration in accordance with an embodiment of the present invention.

Detailed Description

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

As shown in fig. 1 to 4, 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. Wherein, two sides of the fuselage 100 are respectively provided with a wing 110, and the fuselage 100 is provided with a cabin door; the four rotor wing modules are symmetrically arranged above and below the fuselage 100 to form a V-shaped fuselage layout respectively, the rotor wing modules are driven by motors, and each motor is connected with one rotor wing module respectively to provide driving force; the control system is respectively connected with the four motors to adjust the rotating speed and power of each motor to realize the conversion of the flight attitude.

Referring to fig. 3 and 5, the cabin is located in the fuselage 100, in which a rotatable seat 200 is provided, the rotation axis of the seat 200 coinciding with the horizontal mid-axis of the cabin; the seat 200 is rotated by 90 degrees to keep the occupant in a seated position at all times.

The power system is installed in the machine body 100, the power system is respectively connected with power ends of the four motors to provide power, and the power system comprises a battery, a battery management module and electrical equipment.

Referring to fig. 1, 2 and 4, a rotor module power column 320 and a propeller 330. Mounting bracket 310 is fixed at the afterbody of fuselage, including four empennages, sets up a set of rotor module on every empennage. The two tail wings extend towards the upper side of the machine body and are arranged in a V shape, and the upward opening angle of the tail wings is 90-150 degrees, preferably 122 degrees. The other two rotor wing modules extend towards the lower side of the fuselage and are arranged in a V shape, and the downward opening angle of the tail wing is 90-150 degrees, preferably 122 degrees.

The power column 320 is installed at the end of each empennage of the installation frame 310 and is parallel to the central axis of the body 100, the propeller 330 is installed at the front end of the power column 320, and the motor is installed in the power column 320.

Referring to fig. 2 and 3, the ends of four power columns 320 extend out of the tail and are located on the same vertical plane for serving as landing support points. The end of the power column 320 is provided with a shock absorbing device 340 so that the aircraft can land smoothly. The propeller 330 is disposed at the front end of the power column 310 and is located on the same vertical plane.

Referring to fig. 3 and 5, the hatch is located at the belly of the fuselage 100 and includes an upper hatch 120 and a lower hatch 130 that can be opened and closed, and stairs are installed at the inner side of the lower hatch 130, so that passengers can get on and off without interference of propellers, and can conveniently get in and out of the cabin through the stairs on the lower hatch 130.

Claims

1. A fixed-wing vertical take-off and landing aircraft comprises an aircraft body, wings and a cabin door, wherein two sides of the aircraft body are respectively provided with one wing; the mounting frame is fixed at the tail part of the fuselage and comprises four tail wings, and each tail wing is provided with a group of rotor wing modules;

the two tail wings extend towards the upper side of the machine body and are arranged in a V shape, and the tail wings are opened upwards; the other two rotor wing modules extend towards the lower side of the fuselage and are arranged in a V shape, and the tail wings are opened downwards; the two tail wings which are opened upwards and the two tail wings which are opened downwards are symmetrically distributed on the upper side and the lower side of the machine body.

2. The fixed-wing vtol aerial vehicle of claim 1, wherein the four propellers are all located at the front end of the power column and on the same vertical plane.

3. A fixed-wing vtol aircraft as claimed in claim 1 wherein the power strut is mounted on each empennage parallel to the central axis of the fuselage.

4. The fixed-wing vtol aerial vehicle of claim 1, wherein the ends of the power strut extend beyond the tail and are located on the same vertical plane.

5. The fixed-wing VTOL aircraft of claim 1, wherein the two tail wings are opened upwards at an angle of 90 ° to 150 °.

6. The fixed-wing VTOL aerial vehicle of claim 1, wherein the angle of downward flare of the two tail wings is 90 ° to 150 °.

7. The fixed-wing vtol aerial vehicle of claim 1, wherein the fixed-wing aerial vehicle further comprises a control system, a cockpit, and a power system.

8. The fixed-wing VTOL aerial vehicle of claim 7, wherein the control system is connected to the driving devices of four rotor modules respectively, and adjusts the rotation speed and power of each rotor module and the control surface on the wing and the empennage to realize the conversion of flight attitude.

9. The fixed-wing vtol aircraft of claim 7, wherein said cabin is located within the fuselage, and wherein seats are provided; the rotation axis of the seat is parallel to the horizontal central axis of the cabin.

10. The fixed-wing vtol aerial vehicle of claim 7, wherein said power system is mounted in said fuselage or said wing, is connected to each of said drive devices, and provides power to four rotor modules.