CN111086622A

CN111086622A - Aircraft with variable wing pitch angle and implementation method

Info

Publication number: CN111086622A
Application number: CN201911318625.1A
Authority: CN
Inventors: 韩宝钰; 吉飞; 刘中凯
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: 2020-05-01

Abstract

The invention belongs to the technical field of airplane overall design and airplane structure design, and relates to an aircraft with variable wing pitch angle and an implementation method; comprises a wing (1), a fuselage (2), a crossover sub (3) and a rotary joint (4); compared with the traditional airplane, the invention can change the pitch angle of the wings according to different takeoff weights and ranges so as to achieve the best flight performance. The novel wing body connection scheme realizes rapid change of the wing pitch angle configuration at minimum weight cost by only replacing one adapter, and when the wing pitch angle is changed for construction, the wing always rotates around a rotating shaft, so that the wing is simple to position, can be operated in an external field, is simple and convenient to construct, has a simple principle, and is direct in force transmission. The wing joint and the adapter are novel in structural form and reasonable in force transmission path, double-shear connection is achieved, the inclined ribs are ingeniously connected through the two bolts, and the whole joint can bear loads in all directions.

Description

Aircraft with variable wing pitch angle and implementation method

Technical Field

The invention belongs to the technical field of overall design and structural design of airplanes, and relates to an aircraft with variable wing pitch angle and an implementation method.

Background

The pitch angle of wings of the traditional airplane cannot be changed, and the pitch angle configuration of the airplane cannot be changed according to different tasks and voyage requirements. The general wing body connecting structure is a fixed structure, if the relative angle between the wing and the fuselage needs to be changed, the whole wing body connecting structure needs to be destructively disassembled, and the construction is extremely complex and basically cannot be realized.

Disclosure of Invention

The purpose of the invention is as follows: the invention firstly provides an aircraft with a variable pitch angle structure, which meets the requirements of the optimal pitch angle for different tasks, and provides an optimal solution for changing the pitch angle of the wing.

The technical scheme of the invention is as follows: an aircraft with a variable wing pitch angle is characterized by comprising a wing 1, a fuselage 2, a conversion joint 3 and a rotary joint 4; the adapter 3 is connected with the front parts of the wing 1 and the fuselage 2; the rotary joints 4 are connected with the rear parts of the wings 1 and the fuselage 2, the number and the positions of each joint are set according to the load, the axes of the wing body connecting bolts of all the rotary joints 4 are coincided with the rotation axis, and the rotation axis is along the span direction of the wings.

The adapter 3 comprises a wing adapter 301, an adapter 302 and a fuselage adapter 303; one end of the adapter 302 is connected with the wing joint 301 through a self-locking bolt, and the other end of the adapter 302 is connected with the fuselage joint 303 through a self-locking bolt.

The adaptor 302 changes the length of the adaptor 302 according to the change of the pitch angle. Primarily to replace different adapters 302 for different pitch angles.

The rotary joint 4 comprises a wing joint 401 and a fuselage joint 402; the double shear connection is realized through the wing body connecting bolt.

The angle of the pitch angle increases and the length of the adaptor 302 increases.

The adapter 302 and the wing joint 401 are provided with a plurality of tilted ribs, so that the tilted ribs can bear loads in all directions.

The tabs of the adapter 4 may be arranged in different directions to transfer loads in different directions.

A method for realizing variable wing pitch angle is characterized in that when the wing pitch angle needs to be changed, wing body connecting bolts on all conversion joints are firstly removed, a wing rotates around a rotating shaft, an original adapter is removed, a new adapter is replaced, the wing rotates in place around the rotating shaft, and the wing body connecting bolts on the conversion joints are installed.

The invention has the beneficial effects that: compared with the traditional aircraft, the aircraft with the variable pitch angle structure can change the pitch angle of the wings according to different takeoff weights and ranges so as to achieve the optimal flight performance. The novel wing body connection scheme realizes rapid change of the wing pitch angle configuration at minimum weight cost by only replacing one adapter, and when the wing pitch angle is changed for construction, the wing always rotates around a rotating shaft, so that the wing is simple to position, can be operated in an external field, is simple and convenient to construct, has a simple principle, and is direct in force transmission. The structural form of the adapter is shown in fig. 3, the structural form of the wing joint and the adapter is novel, the force transmission path is reasonable, double-shear connection is achieved, the oblique ribs are ingeniously connected through the two bolts, and the whole joint can bear loads in all directions.

Drawings

FIG. 1 is a front view of a wing body connection structure according to the present invention

FIG. 2 is an enlarged view of the connection structure of the adapter (3) according to the present invention

FIG. 3 is a rear view of the wing body connection structure of the present invention

FIG. 4 is an enlarged view of the wing body connection structure of the present invention

FIG. 5 is a schematic view of a crossover and rotary joint

FIG. 6 is a schematic view of a wing joint (301) and a fuselage joint (303)

Detailed Description

The invention is further described below with reference to the accompanying drawings:

the invention relates to a novel wing body connecting scheme, as shown in figures 1-4, a wing (1) and a fuselage (2) are connected through a wing body connecting joint, the wing body connecting joint is divided into two types, one type is a conversion joint (3), the other type is a rotary joint (4), the number and the position of each type of joint are set according to the load, but the axes of wing body connecting bolts of all the rotary joints are ensured to be coincident with a rotating axis, and the rotating axis is along the span direction of the wing. In the example, 2 rotary joints and transfer joints are provided.

As shown in fig. 5-6, the adapter (3) comprises three parts, namely a wing joint (301), an adapter (302) and a fuselage joint (303); the wing joint is connected with the adapter through the self-locking bolt, the connection form is shown in figure 3, double-shear connection is realized, and the inclined ribs are connected for transmitting the lateral load of the corner pieces; the adaptor is connected with the machine body joint through 1 wing body connecting bolt, and is also in double-shear connection. The change of the pitch angle of the wing is realized by replacing different adapters.

The rotary joint (4) comprises a wing joint (401) and a fuselage joint (402), and double-shear connection is realized through 1 wing body connecting bolt.

The quick assembly and disassembly of the wings and the fuselage are realized by assembling and disassembling all the wing body connecting bolts.

When the pitch angle of the wing needs to be changed, the construction is carried out according to the following steps: and removing the wing body connecting bolts on the conversion joints, rotating the wings around the rotating shaft, removing the original adapter, replacing a new adapter, rotating the wings in place around the rotating shaft, and installing the wing body connecting bolts on the conversion joints.

Example (b):

an unmanned aerial vehicle has two mission modes, one is large takeoff weight and short range, the other is small takeoff weight and long range, and the optimal wing pitch angle of the first mode is 2 degrees larger than that of the second mode. By using the unmanned aerial vehicle, one unmanned aerial vehicle can execute two task modes by replacing different adapters.

The specific implementation mode is as follows: the required number of the wing body connecting bolts is calculated according to the size of the wing body connecting load, the rotary joint generally transmits course and vertical load, and lug pieces of the conversion joint can be arranged along different directions to transmit the load in different directions. The connecting bolt axes of all rotary joints are located at the rotary shaft according to the structural space and the position where the various joints are arranged according to the load. When the pitch angle of the wing needs to be changed, the construction is carried out according to the following steps: and removing the wing body connecting bolts on the conversion joints, rotating the wings around the rotating shaft, removing the original adapter, replacing a new adapter, rotating the wings in place around the rotating shaft, and installing the wing body connecting bolts on the conversion joints.

Claims

1. An aircraft with a variable wing pitch angle is characterized by comprising wings (1), a fuselage (2), a conversion joint (3) and a rotary joint (4); the adapter (3) is connected with the front parts of the wing (1) and the fuselage (2); the rotary joints (4) are connected with the rear parts of the wings (1) and the fuselage (2), the number and the positions of each joint are set according to the load, the axes of the wing body connecting bolts of all the rotary joints (4) are coincided with the rotation axis, and the rotation axis is along the span direction of the wings.

2. The variable wing pitch aircraft of claim 1, wherein the crossover joint (3) comprises a wing joint (301), an adapter (302), a fuselage joint (303); one end of the adapter piece (302) is connected with the wing joint (301) through a self-locking bolt, and the other end of the adapter piece (302) is connected with the fuselage joint (303) through a self-locking bolt.

3. The variable wing pitch aircraft of claim 2, wherein the adaptor (302) changes the length of the adaptor (302) in response to changes in pitch.

4. The variable wing pitch aircraft of claim 1, wherein the rotary joint (4) comprises a wing joint (401) and a fuselage joint (402).

5. The variable wing pitch aircraft of claim 3, wherein the angle of pitch increases and the length of the adaptor (302) increases.

6. The variable wing pitch aircraft of claim 2, wherein a plurality of tilted ribs are provided on the adapter (302) and the wing joint (401).

7. The variable wing pitch aircraft of claim 1, wherein the tabs of the crossover joint (4) may be arranged in different directions.

8. The variable wing pitch aircraft of claim 4, wherein a plurality of tilted ribs are provided on the wing joints (401).

9. A method for realizing variable wing pitch angle is characterized in that when the wing pitch angle needs to be changed, wing body connecting bolts on all conversion joints are firstly removed, a wing rotates around a rotating shaft, an original adapter is removed, a new adapter is replaced, the wing rotates in place around the rotating shaft, and the wing body connecting bolts on the conversion joints are installed.