A flexible variable camber wing based on cell structure

Abstract

This invention relates to a flexible variable-camber wing based on a cellular structure, belonging to the field of aircraft structural technology. It comprises three basic cellular structures: a base cell, transfer cells, and flexible connecting units; a drive mechanism; and two auxiliary structures adapted to the basic cellular structures: the wing's leading edge and trailing edge. The basic cellular structures achieve flexible and continuous deformation of the wing surface through a regular and continuous arrangement. The auxiliary structures mainly maintain the integrity of the overall wing structure and support the actuators and transmission devices. The trailing edge of the variable-camber wing, based on the cellular structure, deforms through a torsion bar driven by a motor that traverses the wing, thereby moving the individual transfer cells. This invention achieves smooth and continuous deformation of the wing's trailing edge through modular assembly of cellular structures, offering advantages such as lightweight design, load-bearing capacity, high assembly speed, and reusability.

Description

Technical Field

[0001] This invention relates to a flexible variable camber wing based on a cell structure, with the cell structure as the main component, and belongs to the field of aircraft structure technology. Background Technology

[0002] Aircraft variable-camber wings are driven by camber mechanisms and / or flexible structural deformation at the leading and trailing edges. They continuously and smoothly adjust the wing camber in real time according to flight conditions, thereby achieving optimal aerodynamic efficiency and ultimately reducing drag, aircraft weight, and fuel efficiency. The emergence and rapid development of smart materials and structures have provided a solid material and structural foundation for the realization of variable-camber wings. Currently, aircraft trailing-edge flaps mainly employ non-compliant deformation methods such as mechanism-driven mechanisms, resulting in gaps at deformation joints and significant noise. Furthermore, non-compliant deformation methods result in an uneven wing deformation profile, severely impacting aerodynamic efficiency improvement and optimization. This invention addresses the problem of non-flexible continuous deformation at the trailing edge of traditional variable-camber wings by designing a flexible variable-camber wing based on a cellular structure. The advantages of this design are that it achieves smooth and continuous deformation of the wing trailing edge through modular assembly of cellular structures, exhibiting lightweight, high stiffness, high assembly speed, and reusability. It is an important approach to achieving adaptive flexible deformation of wings. Summary of the Invention

[0003] The purpose of this invention is to address the problem of non-flexible continuous deformation of the trailing edge in existing variable-camber wing mechanisms, which leads to gaps at the deformation joints causing significant noise, and the unsmooth deformation profile affecting aerodynamic efficiency. This invention proposes a variable-camber wing based on a cellular structure, which achieves smooth and continuous deformation of the wing's trailing edge through modular assembly of cellular structures. It features lightweight, high stiffness, high assembly speed, and reusability, and has significant application value in the field of compliant deformation structure design for variable-camber wings.

[0004] The core idea of ​​this invention is to design a variable-camber wing based on a cellular structure. This primarily comprises three basic cellular structures: a base cell, flexible connecting units, and transfer cells, as well as two auxiliary structures adapted to the basic cellular structures: the wing's leading edge and trailing edge. The basic cellular structures achieve flexible and continuous deformation of the wing surface through a regular and continuous arrangement. The auxiliary structures mainly maintain the integrity of the overall wing structure and house the actuators and transmission devices. The trailing edge deformation of the variable-camber wing, based on the cellular structure, is achieved by a motor driving a torsion bar that traverses the wing, thereby moving each transfer cell.

[0005] The objective of this invention is achieved through the following technical solution:

[0006] A variable camber wing based on a cell structure mainly comprises three basic cells: two sets of base cell components, a transmission cell component structure, and a flexible connecting unit; a drive mechanism; and two auxiliary structures adapted to the basic cell structure: the wing leading edge and the wing trailing edge. The two sets of base cell components are respectively installed on both sides of the wing leading edge and the wing trailing edge. The base cell components are divided into upper and lower layers, each layer consisting of multiple base cell structures connected together. The two layers are connected by a flexible connecting unit. The two sets of base cell components are connected to the transmission cell through the flexible connecting unit. The drive mechanism is installed at the wing leading edge.

[0007] The matrix cell structure adopts a hexagonal structure as a whole, and the main body is divided into a joint plane and a supporting structure. The joint plane is a rounded hexagon with slots on the six sides; the supporting structure adopts a six-cylinder structure with side plates.

[0008] The diagonal length of the hexagonal matrix cell is 5-10% of the wing chord length.

[0009] The transfer cell adopts an improved matrix cell structure, with hexagonal matrix cell structures on both sides and the middle width is stretched. The connection between the support structure and the joint plane is "H" shaped, and the middle stretching length is 1 to 1.5 times the diagonal length of the hexagon.

[0010] The thickness of the matrix cell and the transfer cell is adjusted according to the airfoil. The shape of the upper edge of the support structure is adjusted to fit various different airfoil shapes, and its exterior can be deformed by supporting flexible wing membrane material.

[0011] The flexible connection unit is shaped like an "N" and is connected to the hexagonal grooves on the bonding plane of the base cell and the transfer cell by the slots arranged on the upper and lower sides respectively. The flexible connection units are used in pairs and are installed in an anti-symmetrical manner when connected. A pair of flexible connection units connects four bonding planes.

[0012] The drive mechanism includes a motor and a torsion bar. The motor is mounted on the leading edge of the wing, and the torsion bar is mounted on the motor. The motor drives the torsion bar that crosses the wing, and the torsion bar drives each transmission cell to form displacement to achieve trailing edge bending.

[0013] The torsion bar is made of metal or composite material; the curve shape of the torsion bar is determined by the deflection profile of the variable camber wing target, and the deflection position of the torsion bar is the center chord of the variable camber wing target deflection profile. The length of the torsion bar should reach but not exceed the base cell connecting the trailing edge of the wing.

[0014] The matrix cell, transfer cell, leading edge, and trailing edge are made of metallic or composite materials.

[0015] The flexible connection unit is made of a composite material containing an elastic matrix.

[0016] Beneficial effects of the invention

[0017] This invention has the following characteristics:

[0018] 1. A cell-based structure is used to achieve continuous flexing of the wing trailing edge, making the wing deformation smoother and improving the wing's aerodynamic performance.

[0019] 2. The flexible connection units are designed in an "N" shape, thus allowing for a certain degree of compression or tension in the planar direction. When connected in pairs and installed anti-symmetrically, they ensure uniform load and deformation transfer. All flexible connection units are installed in the same direction to guarantee the overall load and deformation transfer and the structural scalability.

[0020] 3. The variable camber wing can be quickly assembled using a modular cell structure, and the cells can be reused. When a cell is damaged, it can be quickly disassembled and replaced, enabling rapid maintenance of the variable camber wing.

[0021] 4. The variable camber wing based on cell structure changes the original mechanical drive deformation mechanism, making the wing structure lighter, and the splicing of cells gives the wing a certain rigidity and can withstand loads.

[0022] 5. The motor drives the torsion bar to rotate, and the torsion bar drives the transmission cell to form displacement to achieve wing camber. This method has strong load-bearing capacity of the motor and torsion bar, and the transition of trailing edge deflection angle is smoother and more continuous. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the variable camber wing structure of the present invention;

[0024] Figure 2 These are a three-dimensional diagram and a front view of the matrix cell structure of this invention;

[0025] Figure 3 This invention provides a perspective view and a front view of the cell structure.

[0026] Figure 4 This is a schematic diagram of the flexible connection unit structure of the present invention;

[0027] Figure 5 This is a three-view drawing showing the connection between the flexible connecting unit of the present invention and the matrix cell and the transfer cell;

[0028] Figure 6 These are the side and top views of the variable camber wing of this invention;

[0029] Figure 7 This is a schematic diagram of the torsion bar drive scheme of the present invention;

[0030] Figure 8This is a schematic diagram showing the shape and length of the torsion bar of the present invention. Detailed Implementation

[0031] The present invention will now be described in detail with reference to the accompanying drawings and examples.

[0032] like Figure 1 As shown, the present invention is a variable camber wing based on cell structure. The implementation method includes: arranging three basic cell structures at intervals, and then installing the appropriate leading edge and trailing edge of the wing to form a variable camber wing segment that can achieve continuous deformation.

[0033] It mainly includes two sets of base cell components, three basic cells: a transfer cell component structure and a flexible connection unit, as well as two auxiliary structures adapted to the basic cell structure: the wing leading edge and the wing trailing edge; and a drive mechanism. The two sets of base cell components are respectively installed on both sides of the wing leading edge and the wing trailing edge. The base cell components are divided into upper and lower layers, each layer consisting of multiple base cells connected together. The two layers are connected by a flexible connection unit. The two sets of base cell components are connected to the transfer cell through the flexible connection unit. The drive mechanism is installed at the wing leading edge.

[0034] The matrix cell, transfer cell, leading edge, and trailing edge are made of metallic or composite materials. The flexible connecting unit is made of composite material containing an elastic matrix.

[0035] like Figure 2 The matrix cell structure is described above. The matrix cell as a whole adopts a hexagonal structure, mainly divided into a bonding plane and a supporting structure. The bonding plane is a rounded hexagon and is connected to other cell structures via flexible connecting units through corresponding slots in six directions. The supporting structure adopts a six-cylinder structure with side plates, built based on the bonding plane and determining the inner circle shape of the bonding plane. The diagonal length of the hexagonal matrix cell accounts for 5-10% of the wing chord length. By adjusting the shape of the upper edge of the supporting structure, it can conform to various wing shapes, and its exterior can be deformed through a supporting flexible skin material.

[0036] like Figure 3 The diagram shows the transfer cell, which is an improved hexagonal matrix cell. It retains the original hexagonal matrix cell structure on both sides and stretches the middle width. The junction between the supporting structure and the connecting plane is an "H"-shaped beam with better load-bearing and transfer effects. The middle stretch length is 1 to 1.5 times the diagonal length of the hexagon.

[0037] like Figure 4 The image shows the flexible connecting unit. The flexible connecting unit is generally N-shaped, allowing for a certain degree of compression or stretching in the planar direction. It then engages with the hexagonal base cell via slots arranged on the top and bottom of both sides. (See image for details.) Figure 5The diagram shows the connection between the flexible connecting unit and the base cell and transfer cell. The flexible connecting units are used in pairs, with each pair connecting four joint planes and installed in an anti-symmetrical manner to achieve uniform load and deformation transfer. To ensure the overall load and deformation transfer and the scalability of the structure, all flexible connecting units maintain the same directional installation pattern.

[0038] Figure 6 The figures shown are a side view and a top view of the variable camber wing of the present invention. As can be seen from the side view, the three basic cell structures are arranged in a spaced distribution pattern. To adapt to the shape of the wing surface in its normal state, the airfoil section needs to be designed. Therefore, the upper edge of the supporting structure of each basic cell and the transferring cell needs to be trimmed to adapt to the selected airfoil structure, and the cells in each part are reasonably numbered. Then, the appropriate leading edge and trailing edge structures of the wing are installed, thereby forming a variable camber wing section capable of chordally flexible and continuous deformation.

[0039] Figure 7 This is a schematic diagram of the torsion bar drive scheme of the present invention. For ease of viewing, one of the transmission cells in the middle has been omitted. A variable camber wing based on a cell structure requires a actuator to move the transmission cells to achieve changes in the wing's shape to generate camber changes. This scheme uses a torsion bar that runs through the transmission cells, with a drive mechanism located at the front of the wing section. The drive mechanism includes a motor and a torsion bar. The motor is mounted on the leading edge of the wing, and the torsion bar is mounted on the motor. The motor is connected to a coupling, which in turn drives the torsion bar that traverses the wing, causing each transmission cell to move and thus deform the wing surface shape. Its advantages are that the motor and torsion bar have strong load-bearing capacity, the transition between changes is more reasonable, the deformation is more flexible, and it better conforms to the wing surface deformation morphology of a real aircraft. Figure 8 This is a schematic diagram showing the shape and length of the torsion bar of the present invention. The torsion bar is made of metal or a 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 the center chord of the variable camber wing target deflection shape. The length of the torsion bar should reach but not exceed the base cell of the auxiliary trailing edge connecting the trailing edge.

[0040] The size and number of the matrix cell, transfer cell, and flexible connection unit need to be adjusted according to the chord length, span, thickness, and airfoil of the variable camber airfoil section. Simultaneously, the size of the drive motor also needs to be adjusted according to the airfoil section dimensions. When the airfoil section has a large span, multiple drive motors can be used for driving.

[0041] The above description is merely a preferred embodiment of the present invention, and the present invention should not be limited to the content disclosed in this embodiment and the accompanying drawings. Any equivalent or modified embodiments made without departing from the spirit of the present invention fall within the scope of protection of the present invention.

Claims

1. A variable camber airfoil based on a cell structure, characterized in that, It includes three basic cells: two sets of base cell components, a transfer cell component structure, and a flexible connection unit; a drive mechanism; and two auxiliary structures adapted to the basic cell structure: the wing leading edge and the wing trailing edge. The two sets of base cell components are respectively installed on both sides of the wing leading edge and the wing trailing edge. The base cell components are divided into two layers, each composed of multiple base cell structures connected together. The two layers are connected by a flexible connection unit. The two sets of base cell components are connected to the transfer cell through the flexible connection unit. The drive mechanism is installed at the wing leading edge. The matrix cell assembly adopts a hexagonal structure as a whole, and the main body is divided into a joint plane and a support structure; the joint plane is a rounded hexagon with slots on the six sides; the support structure adopts a six-cylinder structure with side plates. The diagonal length of the hexagonal structure accounts for 5-10% of the wing chord length. The transfer cell adopts an improved matrix cell structure, with hexagonal matrix cell structures on both sides and the middle width stretched. The connection between the support structure and the joint plane is "H" shaped, and the middle stretching length is 1 to 1.5 times the diagonal length of the hexagon. The thickness of the matrix cell and the transfer cell is adjusted according to the airfoil. The shape of the upper edge of the support structure is adjusted to fit various different airfoil shapes. Its exterior can be deformed by supporting flexible wing membrane material. The flexible connection unit is shaped like an "N" and is connected to the hexagonal slots on the bonding plane of the base cell and the transfer cell by the slots arranged on the upper and lower sides respectively. The flexible connection units are used in pairs and are installed in an anti-symmetrical manner when connected. A pair of flexible connection units connects four bonding planes.

2. The variable camber wing based on cell structure according to claim 1, characterized in that, The trailing edge drive mechanism of the variable camber wing is driven by a motor and a torsion bar installed at the leading edge of the wing. The motor is installed at the leading edge of the wing, and the torsion bar is installed on the motor. The motor drives the torsion bar that crosses the wing, and the torsion bar drives the various transmission cells to form displacement to achieve trailing edge camber.

3. The variable camber wing based on cell structure according to claim 2, characterized in that, 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 the middle chord 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.

4. The variable camber wing based on cell structure according to claim 1, characterized in that, The matrix cell, transfer cell, leading edge, and trailing edge are made of metallic or composite materials.

5. The variable camber wing based on cell structure according to claim 1, characterized in that, The flexible connection unit is made of a composite material containing an elastic matrix.

Images