CN111017191A

CN111017191A - Winglet

Info

Publication number: CN111017191A
Application number: CN201911318520.6A
Authority: CN
Inventors: 谭玉婷; 王斌; 耿建中
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-12-19
Filing date: 2019-12-19
Publication date: 2020-04-17

Abstract

The invention belongs to the field of aircraft design, and particularly relates to a wingtip winglet. The wingtip winglet comprises a fixed wing surface (2) and a foldable wing surface (4), wherein the fixed wing surface (2) is connected with the foldable wing surface (4) through a first rotating device (3). After the wingtip winglet is additionally arranged, the induced resistance of the airplane is reduced, and the additional lift force is generated, so that the lift-drag ratio of the airplane is increased, and the quick-sailing capability and the long-time stagnation patrol capability of the airplane can be improved.

Description

Winglet

Technical Field

The invention belongs to the field of aircraft design, and particularly relates to a wingtip winglet.

Background

The wingtip winglet can reduce the induced resistance of the wing, and has very important significance for ship-borne fixed wing early warning patrol aircrafts with emphasized fast sailing capability and long-time stagnation patrol capability. The conventional wingtip winglet adopted by the carrier-based fixed-wing aircraft mainly has the following problems: 1. wingtip winglets are limited in size by the suitability and geometric compatibility of the aircraft and cannot be designed only to optimize the performance of the aircraft; 2. wingtips winglets reduce the induced drag of the wing and are advantageous for aircraft during take-off, climb and cruise phases, but increase drag is required during landing to reduce landing glide distance and bring the aircraft to a stop as quickly as possible, and therefore, the addition of conventional winglets has a detrimental effect on aircraft performance during landing.

Disclosure of Invention

The purpose of the invention is as follows: the wingtip winglet can meet the requirements of suitability and geometric compatibility of a warship aircraft, improve the rapid sailing capability and the long-time air stagnation patrol capability and can not generate adverse effects on the landing performance.

The technical scheme of the invention is as follows:

in a first aspect, there is provided a winglet comprising: the fixed wing surface 2, the foldable wing surface 4, the fixed wing surface 2 and the foldable wing surface 4 are connected through a first rotating device 3.

Alternatively, the foldable airfoil 4 is arranged to be folded inwards by the first turning device 3 to be perpendicular to the plane of symmetry of the fuselage.

Optionally, the first rotation means 3 is a hinge or a lead screw.

Optionally, a speed reduction plate 5 is further included, and the speed reduction plate 5 is arranged on one side of the foldable airfoil 4 close to the body through a second rotating device 6 and can rotate around a vertical shaft.

Optionally, the second rotating means 6 is a hinge or a lead screw.

Optionally, the winglet trailing edge and the wing trailing edge lie in the same plane.

Optionally, the height of the winglet is equal to the wing tip chord length.

Optionally, the winglet area comprises from 1.5% to 3% of the wing area.

Optionally, the winglet has an camber angle of no more than 25 degrees.

The invention has the advantages that:

the invention relates to a wingtip winglet which can be folded inwards and is provided with a speed reducing plate on the outer surface.

After the wingtip winglet is additionally arranged, the induced resistance of the airplane is reduced, and the additional lift force is generated, so that the lift-drag ratio of the airplane is increased, and the quick-sailing capability and the long-time stagnant patrol capability of the airplane can be improved; when the ship surface operates, the winglets can be folded inwards, so that the folding and unfolding envelope lines of the folded wings cannot be influenced, and the space requirement for additionally installing the winglets is increased; no matter the wings are folded downwards and backwards or upwards towards the symmetrical plane of the fuselage, the winglets do not generate geometric interference on the folding appearance, so the appearance size of the winglets is not limited by the adaptability and geometric compatibility of the ship; in addition, the speed reducer on the inner surface of the winglet can be opened during landing, so that the functions of increasing resistance and reducing the landing distance are achieved.

Drawings

Figure 1 is a schematic illustration of the winglet of the invention deployed with the speed reduction plate thereon not open;

figure 2 is a schematic view of the winglet of the invention in a folded condition;

FIG. 3 is a schematic view of the winglet according to the invention in an open position;

FIG. 4 is a schematic view of the installation position of the invention on a ship-based propeller-driven aircraft;

the labels in the figure are: 1. the airplane wing comprises a wing body, 2, a fixed wing surface, 3, a first rotating device, 4, a foldable wing surface, 5, a speed reducing plate, 6 and a second rotating device.

Detailed Description

The present invention is described in further detail below with reference to the attached drawings.

A winglet, comprising: the fixed wing surface 2, the foldable wing surface 4, the fixed wing surface 2 and the foldable wing surface 4 are connected through a first rotating device 3.

Optionally, the first rotation means 3 is a hinge or a lead screw.

Optionally, the second rotating means 6 is a hinge or a lead screw.

Optionally, the height of the winglet is equal to the wing tip chord length.

Optionally, the winglet area comprises from 1.5% to 3% of the wing area.

Optionally, the winglet has an camber angle of no more than 25 degrees.

Example (b):

a winglet, comprising: the airplane wing comprises a fixed wing surface 2, a foldable wing surface 4 and a speed reducing plate 5, wherein the fixed wing surface 2 is arranged at the wing tip of a wing 1, the fixed wing surface 2 is connected with the foldable wing surface 4 through a first rotating device 3, and the foldable wing surface 4 can be inwards folded to be perpendicular to the symmetrical plane of a fuselage. The speed reducing plate 5 is arranged on one side, close to the machine body, of the foldable airfoil 4, the speed reducing plate 5 is connected with the foldable airfoil 4 through a second rotating device, and the speed reducing plate 5 can rotate around a vertical shaft.

The trailing edge of the wingtip winglet and the trailing edge of the wing are located in the same plane, and the structural strength of the wingtip winglet can be improved.

The height of the wingtip winglet is equal to the chord length of the wingtip of the wing, so that the aerodynamic characteristics of the wingtip winglet are optimal, and the structural weight cost is minimum.

The winglet area accounts for 1.5-3% of the wing area, and the total efficiency of the winglet can be improved.

The camber angle of the wingtip winglet is not more than 25 degrees, and the wing root bending moment and the rolling moment brought by the wingtip winglet can be reduced.

Claims

1. A winglet, comprising: the fixed wing surface (2) and the foldable wing surface (4) are connected through the first rotating device (3).

2. A winglet according to claim 1, wherein the foldable wings (4) are arranged to be folded inwards by the first turning means (3) to be perpendicular to the plane of symmetry of the fuselage.

3. The winglet according to claim 1, wherein the first rotation device (3) is a hinge or a lead screw.

4. A winglet according to claim 1, further comprising a speed-reducing plate (5), the speed-reducing plate (5) being arranged on the side of the foldable airfoil (4) close to the fuselage by means of second turning means (6) and being rotatable about a vertical axis.

5. The winglet according to claim 1, wherein the second turning device (6) is a hinge or a lead screw.

6. The winglet of claim 1, wherein the winglet trailing edge and the wing trailing edge lie in the same plane.

7. The winglet of claim 1, wherein the winglet has a height equal to the chord length of the wing tip.

8. The winglet of claim 1, wherein the winglet area comprises from 1.5% to 3% of the wing area.

9. The winglet of claim 1, wherein the outboard cant angle of the winglet is no more than 25 degrees.