CN112660364A

CN112660364A - Wing capable of automatically adjusting attack angle

Info

Publication number: CN112660364A
Application number: CN202011560086.5A
Authority: CN
Inventors: 王云; 李茂源; 张莉; 闫朝; 李勋
Original assignee: Taizhou University
Current assignee: Taizhou University
Priority date: 2020-12-25
Filing date: 2020-12-25
Publication date: 2021-04-16
Anticipated expiration: 2040-12-25
Also published as: CN112660364B

Abstract

The invention discloses a wing that can automatically adjust the angle of attack, comprising a wing rotating shaft, a fixed section wing, a wing deflection limit block, a damping spring and two large wings; the two large wings pass through the aircraft. The wing shaft is connected, the fixed section wing is rotatably arranged on the wing shaft, the wing deflection limit block is arranged on the side of the large wing close to the fixed section wing, and the fixed section wing is set on the side of the large wing. There is an accommodating cavity, the wing deflection limit block extends into the accommodating cavity, one end of the damping spring is connected with the wing deflection limit block, and the other end is connected with the bottom of the accommodating cavity. The invention automatically controls the angle of attack of the large wing to adapt to the change of the flight speed through the additional moment generated by the small wing installed on the trailing edge of the large wing, thereby offsetting the influence of the speed change on the lift force and keeping the wing lift force unchanged. change, keep the flight altitude unchanged. It reduces the burden of the pilot's flight control, improves the stability and maneuverability of the aircraft's flight, and reduces the pitching and turbulence of the aircraft.

Description

Wing capable of automatically adjusting attack angle

Technical Field

The invention relates to the technical field of wings, in particular to a wing capable of automatically adjusting the size of an attack angle.

Background

In the normal flight process of civil airliners and general airplanes, the flight is hoped to be stable as much as possible, and particularly the up-and-down jolting is hoped to be avoided as much as possible. However, the influence of the relative airflow speed on the wing lift force during flight is large, and if the wing lift force is influenced by the airflow, the airspeed of the airplane is changed, so that the size of the wing lift force is changed and the weight of the airplane is unbalanced, and the airplane jolts up and down.

Many general-purpose aircraft pilots for navigation operations need to pilot the aircraft on one hand, and also need to perform flight operations on the other hand, and want the flight height and attitude of the aircraft to be as stable as possible, so that the wings are also expected to adapt to the change influence of the flight airflow to automatically adjust the attack angle of the wings, and the flight height and attitude of the aircraft are kept unchanged.

Therefore, a mechanism is needed which can automatically adjust the angle of attack of the wing to keep the lift of the wing unchanged and not affect the pitching change of the fuselage when the airspeed of the aircraft changes, so that the aircraft flies more stably and more stably, and the operation burden of a pilot can be reduced.

Disclosure of Invention

The invention aims to solve the problems that: the wing capable of automatically adjusting the size of the attack angle is provided, the attack angle of the large wing is automatically controlled to adapt to the change of the flying speed through the additional moment generated by the small wing additionally arranged on the trailing edge of the large wing, so that the influence of the speed change on the lift force is counteracted, the lift force of the wing is kept unchanged, and the flying height is kept unchanged. The burden of flight control of a pilot is reduced, the flight stability and maneuverability of the airplane are improved, and pitching jolt of the airplane is reduced.

The technical scheme provided by the invention for solving the problems is as follows: a wing capable of automatically adjusting the size of an attack angle comprises a wing rotating shaft, a fixed section wing, a wing deflection limiting block, a damping spring and two large wings; the two big wings are connected through a wing rotating shaft, the fixed section wings are arranged on the wing rotating shaft in a rotating mode, the wing deflection limiting blocks are arranged on one sides, close to the fixed section wings, of the big wings, accommodating cavities are formed in the fixed section wings, the wing deflection limiting blocks stretch into the accommodating cavities, one ends of the damping springs are connected with the wing deflection limiting blocks, and the other ends of the damping springs are connected with the bottoms of the accommodating cavities.

Preferably, the large airfoil is deflectable through a small angle ranging from 3 to 5 degrees.

Preferably, the aircraft further comprises a small wing and a large wing connecting rod, wherein the small wing is arranged at the upper end of the large wing through the large wing connecting rod and the small wing connecting rod. The lift force of the small wing is changed by means of the change of the speed of the airplane, and the adjusting moment value of the large wing is generated, so that the attack angle of the large wing is changed.

Compared with the prior art, the invention has the advantages that: according to the invention, the attack angle of the large wing is automatically controlled to adapt to the change of the flying speed by the additional moment generated by the small wing additionally arranged at the trailing edge of the large wing, so that the influence of the speed change on the lift force is counteracted, the lift force of the wing is kept unchanged, and the flying height is kept unchanged. The burden of flight control of a pilot is reduced, the flight stability and maneuverability of the airplane are improved, and pitching jolt of the airplane is reduced. The small wings can also generate additional lift force to a certain extent, and the lifting performance is improved; the invention is used on civil aviation and navigation airplanes, and has positive significance for reducing the flying jolts of the airplanes and simplifying the control of pilots.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.

FIG. 1 is a two-dimensional front view of an airfoil for automatically adjusting the angle of attack according to the present invention;

FIG. 2 is an isometric view of a wing of the present invention undergoing a deflection event that automatically adjusts the amount of angle of attack;

FIG. 3 is a schematic structural view of a wing limiting block and a damping spring for automatically adjusting the size of an attack angle;

fig. 4 is an overall view of the wing capable of automatically adjusting the size of the attack angle according to the present invention.

The attached drawings are marked as follows: 1. the airplane wing comprises a large wing, 2 a small wing, 3 a large wing connecting rod, 4 a wing rotating shaft, 5 a fixed section wing, 6 a wing deflection limiting block, 7 and a damping spring.

Detailed Description

The embodiments of the present invention will be described in detail with reference to the accompanying drawings and examples, so that how to implement the technical means for solving the technical problems and achieving the technical effects of the present invention can be fully understood and implemented.

The specific embodiment of the invention is shown in fig. 1-4, and the wing capable of automatically adjusting the size of the attack angle comprises a wing rotating shaft 4, a fixed section wing 5, a wing deflection limiting block 6, a damping spring 7 and two large wings 1; two big wing 1 passes through wing pivot 4 and connects, the canned paragraph wing 5 rotates and sets up on wing pivot 4, wing deflection stopper 6 sets up in big wing 1 is close to one side of canned paragraph wing 5, be provided with on the canned paragraph wing 5 and hold the chamber, wing deflection stopper 6 stretches into hold the intracavity, damping spring 7 one end and wing deflection stopper 6 are connected, and the other end and hold the chamber bottom and connect.

The wing deflection limiting block can prevent the wing deflection from being out of control; the damping spring can improve the stability of wing deflection.

In this embodiment, the large airfoil 1 is deflectable through a small angle in the range of 3-5 degrees.

In this embodiment, the aircraft further comprises a small wing 2 and a large wing connecting rod 3, wherein the small wing 2 is arranged at the upper end of the large wing 1 through the large wing connecting rod 3 and the small wing connecting rod 3.

In the specific embodiment of the invention, the wing rotating shaft is positioned a little bit behind the aerodynamic center of the big wing, the upper part of the rear edge of the wing rotating shaft is provided with a small adjusting wing, when the airspeed of the airplane is increased, the small wing can generate upward additional lift force, the lift force can enable the big wing to generate low head moment, the attack angle of the big wing is reduced, the increase value of the lift force of the small wing caused by the increase of the airspeed is balanced and offset, the weight balance of the airplane is maintained, and the airplane can fly stably; on the contrary, when the airspeed of the airplane is reduced, the lift force generated by the small wing is reduced, so that the large wing generates additional raising moment, the attack angle of the large wing is increased, the reduction value of the lift force of the small wing caused by the reduction of the airspeed is balanced and offset, and the stable flight of the airplane is also maintained. And the attitude of the aircraft body is basically not influenced in the process of automatically adjusting the attack angle of the large aircraft wing, and the flight stability is improved.

In order to prevent the large wing from deflecting and stalling out of control due to the influence of factors such as sudden gusts of wind and the like, a wing deflection limiting block is arranged at a proper position behind a rotating shaft of the large wing and inserted into a corresponding groove of the fixed-section wing, and the width of the groove is proper, so that the wing deflection limiting block can effectively control the wing deflection angle, and is generally controlled to be about 3-5 degrees. In order to reduce the impact vibration of the deflection of the large wing and improve the stability, damping springs are arranged above and below the wing deflection limiting block.

When the airplane is controlled to ascend and descend manually, the horizontal tail wing can be controlled by a pilot like the traditional airplane, and the large wing attack angle can be changed together with the large wing capable of automatically adjusting the attack angle, so that the airplane ascending and descending control is realized.

The small wings in the structure can also generate auxiliary lift force, and additional lift force is generated in the low-speed flight process of taking off and landing of the airplane, so that the taking off and landing performance of the airplane is improved.

When the airplane flies at a normal design speed, the lift force moment generated on the small wing is balanced with the aerodynamic moment on the large wing 1, and the large wing 1 is positioned at a design position; when the flying speed of the airplane is reduced due to the reasons, the lifting force and the lifting moment of the small wing 2 are reduced, so that the trailing edge of the large wing 1 is lowered, and the attack angle of the large wing 1 is increased, as shown in fig. 2. At this time, the lift force of the large wing 1 is increased due to the increase of the attack angle, the influence of the reduction of the lift force caused by the reduction of the speed can be compensated, the total unchanged lift force is maintained, and the aircraft can fly stably.

The foregoing is merely illustrative of the preferred embodiments of the present invention and is not to be construed as limiting the claims. The present invention is not limited to the above embodiments, and the specific structure thereof is allowed to vary. All changes which come within the scope of the invention as defined by the independent claims are intended to be embraced therein.

Claims

1. a wing for automatically adjusting the size of the angle of attack, is characterized in that: comprising a wing shaft (4), a fixed section wing (5), a wing deflection limit block (6), a damping spring (7) and two two large wings (1); the two large wings (1) are connected by a wing rotating shaft (4), the fixed section wings (5) are rotatably arranged on the wing rotating shaft (4), and the The wing deflection limit block (6) is arranged on the side of the large wing (1) close to the fixed section wing (5), the fixed section wing (5) is provided with an accommodating cavity, and the wing is deflected A limit block (6) extends into the accommodating cavity, one end of the damping spring (7) is connected with the wing deflection limit block (6), and the other end is connected with the bottom of the accommodating cavity.

2 . The wing for automatically adjusting the angle of attack according to claim 1 , wherein the large wing ( 1 ) can be deflected within a small angle range of 3-5 degrees. 3 .

3. the wing of a kind of automatic adjustment angle of attack size according to claim 1, is characterized in that: also comprise small wing (2) and big and small wing connecting rod (3), described small wing (2) The connecting rods (3) of the large and small wings are arranged on the upper end of the large wings (1).