WO2018129768A1

WO2018129768A1 - Fused wing and body aircraft

Info

Publication number: WO2018129768A1
Application number: PCT/CN2017/072079
Authority: WO
Inventors: 李晓亮
Original assignee: 顺丰科技有限公司
Priority date: 2017-01-16
Filing date: 2017-01-22
Publication date: 2018-07-19
Also published as: CN106628113A

Abstract

A fused wing and body aircraft, comprising a body (1) and wings, which are fused together. The wings comprise wings (2) that are located on a left side and right side of the body (1); the body (1) has a central symmetry surface; the body also has a central cross profile located above the central symmetry surface and a gravity center cross profile perpendicular to the vertex of the central cross profile. An upper wing surface of the gravity center cross profile is in an upward convex streamline shape, wherein the middle is high and the two sides are low; a lower wing surface of the gravity center cross profile is in a downward concave streamline shape, wherein the middle is low and the two sides are high; the height of the gravity center cross profile on the central symmetry surface is H, the width of the gravity center cross profile is D, and 0.7≤H/D≤0.8. The fused wing and body aircraft employs a novel fused wing and body layout, namely a smooth transition from the body to the outlines of the wings, so that disturbance resistance is greatly reduced, while the internal space of the body is increased, and load capacity is improved. The maximum thickness and the width ratio of the body are controlled, so that the body has a high lift-drag ratio, and the pneumatic performance of the aircraft is improved.

Description

Wing body fusion aircraft

Technical field

The present disclosure generally relates to the field of aviation aircraft technology, and in particular to a drone, and more particularly to a wing body fusion aircraft.

Background technique

In the 1960s, aircraft designers began to propose the concept of wing body fusion. The feature of the aircraft design is that there are no obvious fuselage and wing connections. The fuselage, like the wing, is designed with an airfoil that also produces lift. The wing body fusion design increases the body space, the aircraft can get better aerodynamic performance and reduce flight resistance. Most third-generation supersonic fighters such as F-15, F-16, Mirage 2000, MiG-29, Sue The -27 and so on all adopt the wing body fusion layout. The US future wing body fusion concept aircraft X-48B is an attempted application of the wing body fusion layout in the passenger aircraft.

The existing wing body fuses the layout of the aircraft, resulting in a load that is not large enough; and the flight resistance is large and the lift is small, which makes the flight radius small and the battery life short.

Summary of the invention

In view of the above-mentioned drawbacks or deficiencies in the prior art, it is desirable to provide a wing body fusion aircraft with good aerodynamic performance and high load carrying capacity.

The present application provides a wing body fusion aircraft, including a fuselage body and a wing body, the wing includes wings on the left and right sides of the fuselage; the body has a central symmetry plane; The body has a central cross section on the central symmetry plane, a center of gravity perpendicular to the apex of the central section; the upper airfoil of the center of gravity section has an upper convex line shape with a middle height and a low side, the center of gravity The lower airfoil of the cross section has a lower concave streamline shape with a lower middle and a higher side, the height of the center of gravity cross section on the central symmetry plane is H, and the width of the cross section of the center of gravity is D, wherein 0.7≤H/D ≤0.8.

Preferably, 0.76 ≤ H / D ≤ 0.78.

Preferably, the curvature of the upper airfoil of the center of gravity section is greater than the curvature of the lower airfoil.

Preferably, the structure of the center of gravity cross section is determined according to the following formula:

y=0.0003x ³ -0.0024x ² +0.0742x+H,

Where x represents the vertical distance from the central section, 0 ≤ x ≤ D/2; y represents the height of the center of gravity section at the corresponding x.

Preferably, the curvature of the upper airfoil of the central section is greater than the curvature of the lower airfoil.

Preferably, the wing comprises a plurality of cross-sectional airfoils arranged side by side from the wing root to the wing, the wing having a wing-wing type, a wing-wing type and a plurality of sectional airfoils as control surfaces The outer surface shape of the surface of the Sel;

From the wing root airfoil to the wing slightly airfoil, the torsion angle of each airfoil is gradually reduced, and the chord length of each airfoil is gradually reduced.

Preferably, five cross-sectional airfoils are provided between the wing root and the wing slightly, respectively, from 0%, 22%, 50%, 70%, 80% of the span distance of the wing root airfoil.

Preferably, the twist angle of the wing root airfoil, the five of the cross-sectional airfoils, and the wing slightly airfoil is in the direction from the wing root to the wing slightly: 0.5° to 1.5°, 0.2 °~0.7°, -0.2° to 0.2°, -0.8° to -0.5°, -1.5° to -1.0°, -2.2° to -1.2°, -3.5° to -2.6°.

Preferably, the twist angles of the wing root airfoil, the five of the cross-sectional airfoils, and the wing slightly airfoil are sequentially: 1°, 0.5°, 0 from the wing root to the wing slightly. °, -0.65°, -1.35°, -2°, -3°.

Preferably, the chord lengths of the wing root airfoil, the five of the cross-sectional airfoils, and the wing slightly airfoil are sequentially from the wing root to the wing slightly: P, 0.80P to 0.85P 0.72 to 0.76 P, 0.58 P to 0.62 P, 0.5 P to 0.55 P, 0.46 P to 0.49 P, and 0.3 P to 0.35 P.

Preferably, the chord lengths of the wing root airfoil, the five of the cross-sectional airfoils, and the wing slightly airfoil are sequentially: P, 0.83P, 0.75P, from a direction of the wing root to the wing. , 0.6P, 0.53P, 0.48P, 0.33P.

The wing body fusion aircraft provided by the present application adopts a novel wing body fusion layout, that is, a smooth transition from the fuselage to the wing shape, which greatly reduces the interference resistance, increases the internal space of the body, and improves the bearing capacity; The maximum thickness of the fuselage and the width of the fuselage, so that the fuselage has a high lift-to-drag ratio, improve the aerodynamic performance of the aircraft. In the embodiment, it is preferable to define the torsion angle and the chord length of each airfoil of the airfoil, greatly improve the lift-to-drag ratio of the whole machine, and improve the continuation of the aircraft. Flight time.

DRAWINGS

Other features, objects, and advantages of the present application will become more apparent from the detailed description of the accompanying drawings.

1 is a front view of a fuselage and a wing of a wing body according to an embodiment of the present invention;

2 is a schematic structural diagram of a fuselage according to an embodiment of the present invention;

Figure 3 is a cross-sectional view taken along line M-M of Figure 2;

Figure 4 is a diagram showing the relationship between the width and the thickness of the center of gravity of the cross section shown in Figure 3;

FIG. 5 is a schematic structural diagram of a wing provided by an embodiment of the present invention; FIG.

Figure 6 is an A-A end view of Figure 5;

Figure 7 is a cross-sectional view taken along line B-B of Figure 5;

Figure 8 is a cross-sectional view taken along line C-C of Figure 5;

Figure 9 is a cross-sectional view taken along line D-D of Figure 5;

Figure 10 is a cross-sectional view taken along line E-E of Figure 5;

Figure 11 is a cross-sectional view taken along line F-F of Figure 5;

Fig. 12 is a G-G end view of Fig. 5;

detailed description

The present application will be further described in detail below with reference to the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are merely illustrative of the invention, rather than the invention. It should also be noted that, for the convenience of description, only parts related to the invention are shown in the drawings.

It should be noted that the embodiments in the present application and the features in the embodiments may be combined with each other without conflict. The present application will be described in detail below with reference to the accompanying drawings.

Referring to FIG. 1 to FIG. 3 , the embodiment provides a wing body fusion aircraft, including a fuselage 1 and a wing body. The wing includes wings 2 located on the left and right sides of the fuselage 1 , and the body 1 has The central symmetry plane, the fuselage 1 of the wing body has a length D; the fuselage 1 has a central section 1-1 on the central symmetry plane, and a center of gravity section 2-1 perpendicular to the apex of the central section. In Fig. 2, the MM surface corresponds to the plane of the central section 1-1; the upper wing surface of the center of gravity section 2-1 has an upper convex line shape with a middle height and a low side, and the lower airfoil of the center of gravity section 2-1 is in the middle. The lower and upper sides have a lower concave streamline shape, and the maximum height of the central section as shown in FIG. 3 is H, that is, H is the maximum thickness of the fuselage body. It can be seen that the height of the center-of-gravity section 2-1 on the central symmetry plane is H, and the width of the center-of-gravity section is D, where 0.7 ≤ H / D ≤ 0.8.

According to the technical solution provided by the embodiment of the present application, a novel wing body fusion layout is adopted. When 0.7≤H/D≤0.8, the lift of the fuselage is ideal, and when the H/D is between 0.7 and 0.8, the lift is first. Increase and decrease; H/D may preferably be 0.7, 0.71, 0.72, 0.73, 0.74, 0.75, 0.76, 0.77, 0.78, 0.79, 0.8, H/D is between 0.76 and 0.78, and the lift of the fuselage has the largest value. For example, when the Reynolds number is 500000, when H<0.7D, the airfoil airfoil thickness is reduced, the pressure difference on the lower surface is reduced, the lift is reduced, and the lift-to-drag ratio coefficient is reduced. After numerical simulation, it is found that the Reynolds number is 500,000. In the case, the fuselage at H=0.65D is 13.5% lower than the H=0.75D, and the lift-to-drag ratio factor is reduced by 2.1. Therefore, the value of L should not be too small. If it is too small, it will affect the fuselage. The aerodynamic performance; when H>0.8D, the maximum thickness H of the fuselage is too large, the transition between the wing and the wing is steep, and it is easy to generate turbulence. In the case of Reynolds number 500000, the smooth flow line is at the trailing edge of the fuselage. It becomes a disordered line, which is a relatively obvious turbulent area. The generation of the turbulent area will significantly reduce the lift of the fuselage and increase the differential pressure resistance. In order to avoid turbulent transition as much as possible, the height of H should not be More than 0.8D. The maximum thickness H of the fuselage and the extension D of the fuselage are designed to be 0.7 ≤ H / D ≤ 0.8, preferably 0.76 ≤ H / D ≤ 0.78, so that the fuselage has a high lift-to-drag ratio, improving the aerodynamic performance of the aircraft.

Further, the curvature of the upper airfoil of the center of gravity section is greater than the curvature of the lower airfoil, and the fuselage 1 is lifted while ensuring a large load capacity.

Further, the structure of the center of gravity section is determined according to the following formula:

y=0.0003x ³ -0.0024x ² +0.0742x+H,

Where x represents the vertical distance from the central section, 0 ≤ x ≤ D/2; y represents the height of the center of gravity section at the corresponding x. Referring to Figure 4, when x = 0, y is the largest, that is, the maximum thickness H of the fuselage; when x = D / 2, y is the smallest, that is, the wing root of the wing (the joint between the fuselage and the wing) thickness.

Further, the solution provided by this embodiment is applicable to a cargo drone or a passenger aircraft. The application of the aspect, for example H, is preferably 32.15 dm, and the height can satisfy a certain load space.

Further, the curvature of the airfoil under the curvature of the upper airfoil of the central section allows the fuselage 1 to obtain lift while ensuring a large load capacity.

Further, as shown in FIG. 5 to FIG. 12, the wing of the wing body of the present invention comprises a plurality of cross-sectional airfoils arranged side by side from the wing root 3 to the wing 4. The wing has a wing-wing type and a wing. The slightly airfoil and the multi-section airfoil are the outer surface shapes of the Bezier surface established by the control surface; from the wing root airfoil to the wing slightly airfoil, the torsion angle of each airfoil is gradually reduced, and the chord of each airfoil The length gradually decreases. In Fig. 1, the A-A surface is the end surface at the wing root, corresponding to the wing root airfoil type 3-1; the G-G surface is the end surface slightly at the wing, corresponding to the wing slightly airfoil type 3-7.

The wing of the wing body fusion aircraft provided by the present invention forms a surface of the wing by a Bezier surface, and the torsion angle of the blade root wing type, the five section airfoil type, and the wing slightly airfoil shape gradually increases from the wing root to the wing wing shape. Decreasing, and the chord length of each airfoil is gradually reduced, that is, by defining the torsion angle of each airfoil and the chord length, the wing has good aerodynamic performance, the lift is significantly improved, and the resistance is reduced, so The use of this wing can increase the aircraft payload and improve endurance.

Further, there are five cross-sectional airfoils from the wing root 3 to the wing slightly 4, respectively, which are 0%, 22%, 50%, 70%, 80% of the span distance of the wing root airfoil. In Fig. 5, each of the cutting positions is a cross-sectional airfoil, and the five cross-sectional airfoil from the wing root 3 to the wing slightly 4 is the first cross-sectional airfoil 3-2, the second cross-sectional airfoil 3-3, The third section airfoil 3-4, the fourth section airfoil 3-5, and the fifth section airfoil 3-6. In actual use, the airfoil can adopt an airfoil with a large lift coefficient. For example, the five cross-section airfoil from the wing root to the wing can be GOE227, NACA5402, NACA7403, NACA7408, NACA6401. Of course, the choice of airfoil is not only It is limited to the five types. Other types of airfoils can be selected according to actual needs. The five listed here are only for illustration. Of course, other numbers of cross-section airfoils can be set according to actual needs.

Further, from the wing root 3 to the wing slightly 4, the twist angle α of the wing root airfoil, the five cross-section airfoil, and the wing slightly airfoil are: 0.5° to 1.5°, 0.2° to 0.7°, -0.2 °~0.2°, -0.8° to -0.5°, -1.5° to -1.0°, -2.2° to -1.2°, -3.5° to -2.6°. The torsion angle α referred to herein is the angle between the line connecting the leading edge point and the trailing edge point of the airfoil to the horizontal plane. By setting the twist angle, Can improve lift and reduce drag.

Further, from the wing root 3 to the wing 4, the twist angle α of the wing root airfoil, the five cross-section airfoil, and the wing slightly airfoil are: 1°, 0.5°, 0°, -0.65°, - 1.35°, -2°, -3°. The torsion angle at each airfoil is designed according to this, which can greatly improve the lift of the wing and reduce the resistance.

Further, from the wing root 3 to the wing slightly 4, the chord lengths of the wing root airfoil, the five cross-section airfoil, and the wing slightly airfoil are: P, 0.80P to 0.85P, 0.72 to 0.76P, 0.58P. ～0.62P, 0.5P to 0.55P, 0.46P to 0.49P, and 0.3P to 0.35P. That is, the chord length of the wing root airfoil is P, and the chord lengths of the airfoil at the span distances of 0%, 22%, 50%, 70%, 80%, and 100% of the wing root airfoil are respectively 0.80. P to 0.85P, 0.72 to 0.76P, 0.58P to 0.62P, 0.5P to 0.55P, 0.46P to 0.49P, and 0.3P to 0.35P. By setting the chord length, you can better increase lift and reduce drag.

Further, from the wing root 3 to the wing slightly 4, the chord lengths of the wing root airfoil, the five cross-section airfoil, and the wing slightly airfoil are: P, 0.83P, 0.75P, 0.6P, 0.53P, 0.48 P, 0.33P. The chord length at each airfoil is designed according to this, which can greatly improve the lift of the wing and reduce the resistance.

The impact of the embodiment on the lift and drag of the whole machine is less than 5%, and the characteristics of the high lift-to-drag ratio of the wing body fusion fuselage are fully exerted, and the lift-to-resistance ratio of the whole machine is above 14.0.

The above description is only a preferred embodiment of the present application and a description of the principles of the applied technology. It should be understood by those skilled in the art that the scope of the invention referred to in the present application is not limited to the specific combination of the above technical features, and should also be covered by the above technical features without departing from the inventive concept. Other technical solutions formed by any combination of their equivalent features. For example, the above features are combined with the technical features disclosed in the present application, but are not limited to the technical features having similar functions.

Claims

A wing body fusion aircraft characterized by comprising a fuselage and a wing of a wing body, the wing comprising wings on left and right sides of the fuselage; the fuselage having a central symmetry plane; The fuselage has a central cross section on the central symmetry plane, a center of gravity cross section perpendicular to the apex of the central section; the upper airfoil section of the center of gravity section has an upper convex line shape with a middle height and a low side on both sides, The lower airfoil of the center of gravity cross section has a lower concave streamline shape with a lower middle and a higher side, the height of the center of gravity cross section on the central symmetry plane is H, and the width of the cross section of the center of gravity is D, wherein 0.7≤H/ D ≤ 0.8.
The wing body fusion aircraft according to claim 1, wherein 0.76 ≤ H/D ≤ 0.78.
The wing body fusion aircraft of claim 1 wherein the upper airfoil section of the center of gravity section has a curvature that is greater than the curvature of the lower airfoil.
The wing body fusion aircraft according to claim 3, wherein the structure of the center of gravity section is determined according to the following formula:

y=0.0003x 3 -0.0024x 2 +0.0742x+H,

Where x represents the vertical distance from the central section, 0 ≤ x ≤ D/2; y represents the height of the center of gravity section at the corresponding x.
The wing body fusion aircraft of claim 1 wherein said central section has an upper airfoil curvature that is greater than a lower airfoil curvature.
A wing body fusion aircraft according to any one of claims 1 to 5, wherein the wing comprises a plurality of cross-sectional airfoils arranged side by side from the wing root to the wing, the wing having a wing root The outer shape of the Bezier surface established by the control surface is the airfoil, the wing slightly airfoil and the plurality of cross-section airfoils;

From the wing root airfoil to the wing slightly airfoil, the torsion angle of each airfoil is gradually reduced, And the chord length of each airfoil gradually decreases.
The wing body fusion aircraft according to claim 6, wherein five cross-sectional airfoils are provided between the wing root and the wing slightly, respectively, 0%, 22% from the wing root airfoil, 50%, 70%, 80% of the exhibition distance.
The wing body fusion aircraft according to claim 7, wherein said wing root airfoil, five said sectional airfoil, said wing slightly airfoil from said wing root to said wing slightly The twist angles are: 0.5° to 1.5°, 0.2° to 0.7°, -0.2° to 0.2°, -0.8° to -0.5°, -1.5° to -1.0°, -2.2° to -1.2°, - 3.5 ° ~ -2.6 °.
The wing body fusion aircraft according to claim 8, wherein said wing root airfoil, five said sectional airfoil, said wing slightly airfoil from said wing root to said wing slightly The twist angles are: 1°, 0.5°, 0°, -0.65°, -1.35°, -2°, -3°.
The wing body fusion aircraft according to claim 7, wherein said wing root airfoil, five said sectional airfoil, said wing slightly airfoil from said wing root to said wing slightly The chord lengths are: P, 0.80P to 0.85P, 0.72 to 0.76P, 0.58P to 0.62P, 0.5P to 0.55P, 0.46P to 0.49P, and 0.3P to 0.35P.
The wing body fusion aircraft according to claim 10, wherein said wing root airfoil, five said sectional airfoil, said wing slightly airfoil from said wing root to said wing slightly The chord lengths are: P, 0.83P, 0.75P, 0.6P, 0.53P, 0.48P, 0.33P.