CN117885926A

CN117885926A - Novel vertical take-off and landing composite wing aircraft

Info

Publication number: CN117885926A
Application number: CN202311033506.8A
Authority: CN
Inventors: 王海峰
Original assignee: Cool Century Guangzhou Intelligent Equipment Center
Current assignee: Cool Century Guangzhou Intelligent Equipment Center
Priority date: 2023-08-16
Filing date: 2023-08-16
Publication date: 2024-04-16

Abstract

The invention provides a design method of a novel vertical take-off and landing composite wing aircraft, which has the advantages of a multiaxial aircraft and a fixed wing aircraft, adopts extremely simple and compact design, has the capability of vertical take-off and landing, and can hover, accelerate forwards and cruise with high efficiency by matching a specially designed power mechanism with a flight controller. The design of the invention can also adopt a control surface-free control method, thereby avoiding the problems of delay, instability and the like in the traditional control surface control method, reducing the resistance of the aircraft and improving the flight performance of the aircraft. The invention has simple design, high reliability and low cost, and has wide application prospect in the field of aircrafts.

Description

Novel vertical take-off and landing composite wing aircraft

Technical Field

The invention relates to the field of aircrafts, in particular to a design of a novel vertical take-off and landing composite wing aircraft.

Background

The common multiaxial aircraft can only adjust the gesture through power, obtains the acceleration in XYZ each direction, because the large tracts of land airfoil that does not have the fixed wing provides the lift, most power is wasted on keeping the lift of rotor. The traditional fixed wing aircraft has larger occupied space, the gesture and the flight direction of the fixed wing aircraft need to be controlled by a plurality of control surfaces, the fixed wing aircraft is greatly influenced by airflow, and the problems of control delay, unstable gesture and the like exist in the flight, take-off and landing processes. The invention provides a design method of a novel vertical take-off and landing composite wing aircraft, which has the advantages of a multiaxial aircraft and a fixed wing aircraft, adopts extremely simple and compact design, has the capability of vertical take-off and landing, and can hover, accelerate forwards and cruise with high efficiency by matching a specially designed power mechanism with a flight controller. The design of the invention can also adopt a control surface-free control method, thereby avoiding the problems of delay, instability and the like in the traditional control surface control method, reducing the resistance of the aircraft and improving the flight performance of the aircraft. The invention has simple design, high reliability and low cost, and has wide application prospect in the field of aircrafts.

Disclosure of Invention

The invention provides a design of a novel vertical take-off and landing composite wing aircraft, which comprises the following technical scheme:

the novel vertical take-off and landing composite wing aircraft comprises a 10-body main body, a 20-main wing surface, a 30-vertical tail wing, a 40-horizontal tail wing, a 50-front power cabin, a 60-front upper power mechanism, a 70-front lower power mechanism, a 80-right rear power mechanism and a 90-left rear power mechanism according to the parts shown in figure 1. The helicopter has the advantages of a helicopter (or multiple rotors) and a fixed-wing unmanned aerial vehicle, has vertical take-off and landing capability, can cruise with high efficiency, and simultaneously maintains sensitive attitude control capability under various air conditions.

The invention refers to fig. 1, wherein 10 main body of the machine body is main loading equipment, and adopts the design of rear gravity center; 20. the main airfoil provides a main lift force during flat flight; 30. the vertical tail wing and the horizontal tail wing 40 have no control surface, and mainly keep stable flight attitude during flat flight. 50. The front power cabin is internally provided with a 60 front upper power mechanism and a 70 front lower power mechanism for providing power and yaw control for the horizontal and vertical directions of the front part of the aircraft; 80. the right rear power mechanism and the 90 left rear power mechanism provide power and rolling control in horizontal and vertical directions at the rear part of the aircraft.

According to the invention, referring to fig. 2, in the design, according to the application requirement of an aircraft, the installation angle a of the propeller surfaces of 4 groups of power mechanisms has an inclination angle of 10-30 degrees with the vertical line, and the aircraft vertically takes off at the angle of the inclination angle a during taking off, so that the multi-rotor taking-off and landing capability is realized. After reaching the flying height, the inclination angle is reduced through the controller or the control rod, the aircraft can obtain forward acceleration, the main wing surface of the aircraft provides main lifting force when reaching horizontal cruising, and the power required by the aircraft can be greatly reduced.

In the design, the 60 front upper power mechanism and the 70 front lower power mechanism are coaxially or closely arranged in the 50 front power cabin, so that the front power of the whole machine is more compact; 80. the right rear power mechanism and the 90 left rear power mechanism are positioned on the 20 main wing surfaces and accelerate the surface air flow on the 20 main wing surfaces, so that the effects of improving the lift force and reducing the induced resistance are achieved.

In the design, the blade of the 80 right rear power mechanism is a positive blade, and the blade of the 90 left rear power mechanism is a negative blade, so that yaw force generated during rolling at a specific speed is counteracted with the reverse torque force of the blade, and the control complexity is reduced.

Drawings

FIG. 1 is a schematic isometric view.

FIG. 2 is a schematic view of an aircraft side view power pack installation angle and take-off and landing angle.

Fig. 3 is a schematic top view.

Claims

1. A novel vertical take-off and landing composite wing aircraft has vertical take-off and landing capability, can cruise with high efficiency, and simultaneously maintains sensitive attitude control capability under various air conditions. The method is characterized in that: the main part of the multi-rotor and fixed-wing composite design without tilting fixed angles comprises a main body of a fuselage, a main wing surface, a front power cabin, a front upper power mechanism, a front lower power mechanism, a right rear power mechanism and a left rear power mechanism, the gravity center of the whole aircraft is arranged at the rear, and the main wing surface is shaped as a flying wing or a delta wing.

2. A high efficiency cruising pitch powered aircraft design as in claim 1 wherein: the front power is coaxially or closely arranged in the front power cabin, the right rear power mechanism blade is a positive blade, the left rear power mechanism blade is a negative blade, and the installation position is above the main wing surface.

3. A high efficiency cruising pitch powered aircraft design as in claim 1 wherein: the installation angle a of the propeller surfaces of the 4 groups of power mechanisms has an inclination angle of 10-30 degrees with the vertical line to the front, and the aircraft vertically takes off at the angle of backward inclination a during taking off, so that the multi-rotor taking-off and landing capability is realized.

4. A high efficiency cruising pitch powered aircraft design as in claim 1 wherein: the control without control surface can be adopted, and the thrust lifting of each power unit is adjusted under the flying state of the fixed wing, so that the roll, pitch and yaw control of the aircraft can be realized.