CN115973407A

CN115973407A - Flexible variable camber wing based on cell structure

Info

Publication number: CN115973407A
Application number: CN202211581786.1A
Authority: CN
Inventors: 张梦杰; 周进; 宋坤苓; 薛景锋; 王文娟
Original assignee: Chinese Aeronautical Est
Current assignee: Chinese Aeronautical Est
Priority date: 2022-12-09
Filing date: 2022-12-09
Publication date: 2023-04-18

Abstract

The invention relates to a flexible camber wing based on a cell structure, which mainly comprises the cell structure and belongs to the technical field of aircraft structures; the method comprises the following steps: the aircraft comprises 3 basic cell structures of a base cell, a transmission cell and a flexible connecting unit, a driving mechanism and 2 auxiliary structures which are adapted to the leading edge and the trailing edge of the basic cell structure. The basic cell structure realizes flexible continuous deformation of the airfoil through regular and continuous arrangement, and the auxiliary structure is mainly used for maintaining the integrity of the overall structure of the airfoil and carrying a driver and a transmission device. The variable camber wing trailing edge based on the cell structure realizes the trailing edge deformation by driving a torsion bar transversely passing through the wing to drive each transmission cell to move through a motor. The invention can realize the smooth and continuous deformation of the trailing edge of the wing by building block splicing of the cellular structure, and has the advantages of light weight, bearing capacity, high construction speed and reutilization.

Description

Flexible variable camber wing based on cell structure

Technical Field

The invention relates to a flexible deflection wing based on a cellular structure, which mainly comprises the cellular structure and belongs to the technical field of aircraft structures.

Background

The variable camber wing of the airplane is driven by the variable camber mechanism and/or the flexible structure of the front edge and the rear edge of the wing to deform, and the camber of the wing is continuously and smoothly adjusted in real time according to the flight state, so that the optimal pneumatic benefit is obtained, and the purposes of reducing the flight drag, reducing the weight of the airplane, reducing the fuel efficiency and the like are further achieved. The advent and rapid development of smart materials and structures provides a good material and structural foundation for the implementation of a variable camber wing. The trailing edge flap of the current aircraft is mainly realized by non-compliant deformation modes such as mechanism driving and the like, so that gaps exist at deformation connection positions, and therefore significant noise is generated. In addition, the non-compliant deformation mode causes the deformation profile of the wing to be not smooth, and the improvement and optimization of the aerodynamic efficiency are seriously influenced. The invention designs a flexible camber-changing wing based on a cell structure aiming at the problem of non-flexible continuous deformation of the trailing edge of the traditional camber-changing wing.

Disclosure of Invention

The invention aims to solve the problems that gaps exist at the deformation connection part to generate obvious noise and the deformation contour is not smooth to influence the pneumatic efficiency improvement due to the inflexible continuous deformation of the driving type trailing edge of the existing variable camber wing mechanism. The variable camber wing based on the cellular structure can realize flexible, smooth and continuous deformation of the wing trailing edge through building block type splicing of the cellular structure, has the characteristics of light weight, high rigidity, high building speed and reusability, and has important application value in the field of design of flexible deformation structures of variable camber wings.

The invention relates to a variable camber airfoil based on a cell structure, which mainly comprises 3 basic cell structures of a base cell, a flexible connecting unit and a transmission cell, and 2 auxiliary structures of an airfoil leading edge and an airfoil trailing edge, wherein the 2 auxiliary structures are adapted to the basic cell structures. The basic cell structure realizes flexible continuous deformation of the airfoil through regular and continuous arrangement, and the auxiliary structure is mainly used for maintaining the integrity of the overall structure of the airfoil and is provided with a driver and a transmission device. The variable camber wing trailing edge based on the cell structure realizes the trailing edge deformation by driving a torsion bar transversely passing through the wing to drive each transmission cell to move through a motor.

The purpose of the invention is realized by the following technical scheme:

a variable camber wing based on a cell structure mainly comprises two groups of basic cell components, a transmission cell component structure, 3 basic cells of a flexible connection unit, a driving mechanism and 2 auxiliary structures, wherein the 2 auxiliary structures are adapted to the wing leading edge and the wing trailing edge of the basic cell structure; two groups of base body cell element assemblies are respectively and correspondingly arranged on two sides of the front edge and the rear edge of the wing, the base body cell element assemblies are arranged in an upper layer and a lower layer, each layer is formed by connecting a plurality of base body cell element structures, the two layers are connected through a flexible connecting unit, the two groups of base body cell element assemblies are connected with the transmission cell elements through the flexible connecting unit, and a driving mechanism is arranged at the front end of the wing.

The whole base cell structure adopts a hexagonal structure, and the main body mainly comprises a joint plane and a supporting structure. The joint plane is in a rounded hexagon, and the six edges are provided with clamping grooves; the supporting structure adopts a structure with six cylindrical belts and side plates.

The length of the opposite angle of the hexagon of the base cell accounts for 5-10% of the length of the wing chord.

The transmission cell adopts an improved base cell structure, the two sides of the transmission cell adopt a hexagonal base cell structure, the middle width is stretched, the connecting part of the supporting structure and the joint plane is H-shaped, and the stretching length of the middle part is 1-1.5 times of the diagonal length of the hexagon.

The thicknesses of the base body cell element and the transmission cell element are adjusted according to the wing profiles, the profiles of the upper edges of the supporting structures are adjusted to fit different wing profiles, and the outer portions of the supporting structures can be deformed by supporting flexible wing membrane materials.

The flexible connecting unit is integrally N-shaped and is combined with the hexagonal clamping grooves on the joint plane of the base body cell element and the transmission cell element through the clamping grooves which are respectively arranged at the upper part and the lower part of two sides; the flexible connecting units are used in pairs when connected and are arranged in an anti-symmetric manner; a pair of flexible connection units connects the four joining planes.

The driving mechanism comprises a motor and a torsion bar, the motor is arranged at the front end of the wing, the torsion bar is arranged on the motor, the motor drives the torsion bar which transversely penetrates through the wing, and the torsion bar drives each transmission cell unit to form displacement so as to realize trailing edge bending.

The torsion bar is made of metal materials or composite materials; the curve shape of the torsion bar is determined by the deflection shape of the variable camber wing target, and the deflection position of the torsion bar is a middle chord line of the deflection shape of the variable camber wing target. The length of the torsion bar should reach but not exceed the base cell connecting the trailing edge of the wing.

The base body cells, the transmission cells, the front edge and the rear edge are made of metal materials or composite materials.

The flexible connecting unit is made of composite material containing an elastic matrix.

The invention has the beneficial effects

The invention has the following characteristics:

1. the wing trailing edge is continuously bent by adopting a cell structure-based form, so that the wing deformation is more flexible, and the aerodynamic performance of the wing is improved.

2. The flexible connection unit is designed to be "N" type, so that a certain degree of compression or tension can be achieved in the plane direction. When the connecting device is used in pairs and is arranged in an anti-symmetric manner, the uniform transmission of load and deformation can be realized. All flexible connection units all keep same orientation installation to guarantee overall structure's load deformation transmission and the expansibility of structure.

3. The variable camber wing can be spliced by building block type of the cell structure to realize quick construction, and the cell can be reused, when one cell is damaged, the variable camber wing can be quickly disassembled and replaced to realize quick maintenance of the variable camber wing;

4. the variable camber wing based on the cell structure changes the original mechanical driving deformation mechanism, so that the wing structure has lighter weight, and the wing has certain rigidity and can bear load through the splicing of the cells.

5. The motor is adopted to drive the torsion bar to rotate, the torsion bar drives the transmission cell element to form displacement to realize wing deflection, and the motor and the torsion bar have strong bearing capacity and more flexible and continuous transition of the change of the deflection angle of the rear edge.

Drawings

FIG. 1 is a schematic view of a variable camber airfoil configuration according to the present invention;

FIG. 2 is a perspective view and a front view of a base cell structure according to the present invention;

fig. 3 is a perspective view and a front view of a transfer cell structure according to the present invention;

FIG. 4 is a schematic view of the structure of the flexible connection unit of the present invention;

FIG. 5 is a three-dimensional view of the flexible connecting unit of the present invention connected to a base cell and a transfer cell;

FIG. 6 is a side and top view of a variable camber airfoil of the present invention;

FIG. 7 is a schematic view of a torsion bar drive scheme of the present invention;

fig. 8 is a schematic view of the profile and length of a torsion bar in accordance with the present invention.

Detailed Description

The invention is described in detail below with reference to the figures and examples.

As shown in fig. 1, the present invention is a variable camber airfoil based on a cellular structure, and the embodiment includes: three basic cell structures are arranged at intervals, and then the front edge and the rear edge of the adaptive wing are installed, so that the variable camber wing panel capable of realizing continuous deformation is formed.

The aircraft mainly comprises two groups of base cell element assemblies, a transmission cell element assembly structure, 3 base cells of flexible connection units and 2 auxiliary structures of a wing leading edge and a wing trailing edge which are adapted to the base cell element structure; the two groups of base body cell element assemblies are respectively and correspondingly arranged on two sides of the front edge and the rear edge of the wing, the base body cell element assemblies are arranged in an upper layer and a lower layer, each layer is formed by connecting a plurality of base body cell elements, the two layers are connected through a flexible connecting unit, the two groups of base body cell element assemblies are connected with the transmission cell elements through flexible connecting units, and the driving mechanism is arranged at the front end of the wing.

The base body cells, the transmission cells, the front edge and the rear edge are made of metal materials or composite materials. The flexible connecting unit is made of composite material containing an elastic matrix.

Fig. 2 shows the structure of the substrate cell. The whole base body cell adopts a hexagonal structure, and the main body of the base body cell is mainly divided into a bonding plane and a supporting structure. The whole joint plane is in a rounded hexagon and is connected with other cell structures through the corresponding clamping grooves in six directions through the flexible connecting units. The supporting structure adopts six cylindrical belt side plate structures, and the inner ring appearance of the joint plane is constructed and determined based on the joint plane. The length of the hexagon diagonal of the base cell accounts for 5-10% of the chord length of the airplane. By adjusting the profile of the upper edge of the support structure to fit a variety of different wing profiles, the exterior of the support structure can be deformed by supporting the flexible skin material.

As shown in fig. 3, the transmission cells are modified hexagonal base cells, retaining the original hexagonal base cell structure on both sides and stretching the middle width. The joint of the supporting structure and the connecting plane is an H-shaped beam with better bearing and transmission effects. The intermediate stretching length is 1 to 1.5 times of the diagonal length of the hexagon.

The flexible connection unit is shown in fig. 4. The flexible connection unit is in an N shape as a whole, and can realize certain compression or stretching in the plane direction. And then the hexagonal base body cell is jointed with the hexagonal base body cell through clamping grooves which are respectively arranged at the upper part and the lower part of the two sides. As shown in fig. 5, the flexible connection units are connected with the base cell and the transmission cell, the flexible connection units are used in pairs when connected, and the pair of flexible connection units are connected with four joint planes and are arranged in an anti-symmetric manner so as to realize uniform transmission of load and deformation. Simultaneously, all flexible connection units keep the same direction installation rule for guaranteeing the load deformation transmission of the whole structure and the expansibility of the structure.

FIG. 6 is a side view and a top view of a variable camber airfoil of the present invention. From the side view, it can be seen that the three basic cell structures are arranged in a spaced-apart manner, so that the wing section profile needs to be set to adapt to the profile of the wing surface in the conventional state, and therefore the upper edge parts of the supporting structures of the base cells and the transmission cells need to be cut to adapt to the selected wing section structure, and the cells at each position are reasonably numbered. And then installing adaptive wing leading edge and wing trailing edge structures, and further forming a variable-camber wing section capable of realizing chord-wise flexible continuous deformation.

Fig. 7 is a schematic view of a torsion bar drive scheme of the present invention. For ease of viewing, one of the intermediate transfer cells is hidden. The variable camber wing based on the cell structure generates camber change, and a driver is required to drive a transmission cell to move so as to realize change of the wing appearance. The scheme adopts the torsion bar to penetrate through the transmission cell elements, the driving mechanism is arranged at the front part of the wing section and comprises the motor and the torsion bar, the motor is arranged at the front end of the wing, the torsion bar is arranged on the motor, the motor is connected with the coupler and then drives the torsion bar which traverses the wing to drive each transmission cell element to move so as to realize the deformation of the airfoil shape, and the scheme has the advantages that the bearing capacity of the motor and the torsion bar is strong, the change transition is more reasonable, the deformation is more flexible, and the airfoil deformation is more consistent with the airfoil deformation form of a real airplane. FIG. 8 is a schematic diagram of the shape and length of a torsion bar according to the present invention. The torsion bar is made of metal material or composite material with high hardness. The curve shape of the torsion bar is determined by the deflection shape of the variable camber wing target, and the deflection position of the torsion bar is a middle chord line of the deflection shape of the variable camber wing target. The length of the torsion bar should reach but not exceed the base cell connecting the trailing edge secondary trailing edge.

The sizes and the number of the base body cells, the transmission cells and the flexible connecting units need to be adjusted according to the chord length, the extension length and the thickness of the variable-camber wing section and the wing profile, and meanwhile, the size of the driving motor also needs to be adjusted according to the size of the wing section. When the wing panel has a large span length, a plurality of groups of driving motors can be arranged for driving.

While the foregoing is directed to the preferred embodiment of the present invention, it is not intended that the invention be limited to the embodiment and the drawings disclosed herein. Equivalents and modifications may be made without departing from the spirit of the disclosure, which is to be considered as within the scope of the invention.

Claims

1. A variable camber wing based on a cell structure is characterized by comprising two groups of basic cell components, a transmission cell component structure, 3 basic cells of a flexible connection unit, a driving mechanism and 2 auxiliary structures, wherein the 2 auxiliary structures are adapted to the leading edge and the trailing edge of the basic cell structure; two groups of base body cell element assemblies are respectively and correspondingly arranged on two sides of the front edge and the rear edge of the wing, the base body cell element assemblies are arranged in an upper layer and a lower layer, each layer is formed by connecting a plurality of base body cell element structures, the two layers are connected through a flexible connecting unit, the two groups of base body cell element assemblies are connected with the transmission cell elements through the flexible connecting unit, and a driving mechanism is arranged at the front end of the wing.

2. The wing of claim 1, wherein the base cell structure is a hexagonal structure, and the main body of the base cell structure is mainly divided into a joint plane and a supporting structure. The joint plane is in a shape of a rounded hexagon, and clamping grooves are formed in six edges; the supporting structure adopts a structure with six cylindrical belts and side plates.

3. The wing of claim 1, wherein the diagonal length of the hexagonal base cells is 5-10% of the chord length of the wing.

4. The wing of claim 1, wherein the transmission cells are formed of modified base cell structures, the two sides of the wing are formed of hexagonal base cell structures, the intermediate width of the wing is elongated, the connecting portion between the support structure and the joint plane is formed in an "H" shape, and the intermediate elongated length is 1 to 1.5 times the diagonal length of the hexagon.

5. The wing with variable camber based on cellular structure of claim 1, wherein the thickness of the base cells and the transmission cells is adjusted according to the airfoil profile, and the outer portion of the wing is deformed by supporting the flexible wing film material by adjusting the profile of the upper edge of the supporting structure to fit various wing profiles.

6. The wing of claim 1, wherein the flexible connection unit is of an "N" shape as a whole, and is combined with the hexagonal slots on the joint plane of the base cell and the transmission cell by the slots respectively arranged on the upper and lower sides; the flexible connecting units are used in pairs when connected and are arranged in an anti-symmetric manner; a pair of flexible connection units connects the four joining planes.

7. The wing of claim 1, wherein the drive mechanism of the trailing edge of the wing includes a motor and a torsion bar, the motor is mounted on the front end of the wing, the torsion bar is mounted on the motor, the motor drives the torsion bar across the wing, and the torsion bar drives the transmission cells to displace to achieve the trailing edge bending.

8. The wing of claim 1, wherein the torsion bar is made of metal or composite material; the curve shape of the torsion bar is determined by the deflection shape of the variable camber wing target, and the deflection position of the torsion bar is a middle chord line of the deflection shape of the variable camber wing target. The length of the torsion bar should reach but not exceed the base cell connecting the trailing edge of the wing.

9. The modified camber airfoil of claim 1, wherein the base cells, the transfer cells, the leading edge and the trailing edge are made of a metallic material or a composite material.

10. The inflected wing of claim 1, wherein the flexible connecting unit is made of a composite material including an elastic matrix.