A honeycomb structure aircraft control surface
By employing a regular hexagonal honeycomb structure and additive manufacturing technology on the aircraft control surface, the problems of large weight and complexity of traditional aircraft control surfaces have been solved, achieving a balance between lightweighting and strength.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI XIANGAO ELECTRONIC TECH CO LTD
- Filing Date
- 2025-08-11
- Publication Date
- 2026-07-07
AI Technical Summary
Traditional aircraft control surface structures are heavy and complex, making it difficult to achieve high-strength design and lightweighting, and the modeling and analysis of parts are also complex.
It adopts a regular hexagonal honeycomb structure with uniform external dimensions, and forms an integral structure through wall thickness variation and additive manufacturing technology. The rudder stick is solid, the rudder body has a honeycomb structure to adapt to stress characteristics, and the rudder corner has a hollow structure with reinforcing ribs to achieve a balance between strength and weight.
It achieves lightweight and strength balance in the control surface structure, simplifies the part design and modeling process, and reduces production costs and cycle time.
Smart Images
Figure CN224466110U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the technical field of aircraft structural design, and in particular to an aircraft control surface with a honeycomb structure. Background Technology
[0002] Aircraft control surfaces are the main components of the flight control system. They provide the torque needed to control flight attitude. Control surfaces are generally sheet-like structures with a large surface area and weight. Since the weight of the control surfaces has an adverse effect on the dynamic performance of the control system, the design requirements for aircraft control surfaces should be high load-bearing capacity, low aerodynamic drag, and low structural weight. Traditional skin-frame control surface structures have complex assembly processes and many process constraints, making it impossible to achieve equal strength design. Therefore, optimizing the control surface structure and reducing its weight is of great significance.
[0003] Currently, sandwich-structured control surfaces using additive manufacturing processes typically consist of upper and lower skins and a core. They have no rivet stress concentration points, are lightweight, have high strength, and good fatigue resistance. For example, Chinese patent CN216762141U, entitled "A Honeycomb Integral Control Surface Structure," discloses a honeycomb integral control surface structure. During the design process, the stress varies at different locations on the control surface, and ordinary honeycomb structures can hardly meet the requirements for strength variation. It is necessary to change the honeycomb size and set up complex anisotropic coordinated honeycombs. The internal structure of the control surface is complex, and the work of part modeling, spatial layout, analysis, and optimization design is difficult, which also increases the structural weight.
[0004] Therefore, those skilled in the art need to design a control surface structure that can better adapt to the geometry of the control surface, with a simple and efficient part design and modeling process, and effectively reduces the weight of the control surface. Utility Model Content
[0005] To solve the above-mentioned technical problems, this utility model provides a honeycomb structure aircraft control surface. The control surface includes a control handle, a control body, and a control angle. The control handle and the control angle are located on the same side of the control body. The control surface has a honeycomb structure, which includes honeycombs. The upper and lower edges of several honeycombs overlap to form a row, and each row is spaced apart.
[0006] Furthermore, the honeycomb is in the shape of a regular hexagon.
[0007] Furthermore, all the cells are the same size.
[0008] Furthermore, the rudder handle is provided with a pivot hole, which is configured as a pivot for mounting the rudder surface.
[0009] Furthermore, honeycombs arranged in a single column have the same wall thickness; honeycombs arranged in different columns have a wall thickness inversely proportional to the horizontal distance between the center of the honeycomb and the center of the pivot hole, with the wall thickness extending from the outside of the honeycomb towards the center. The formula for calculating the wall thickness is:
[0010] In the formula, s is the wall thickness of each side of the honeycomb; L is the horizontal distance between the center of the outermost regular hexagon of the rudder surface and the center of the pivot hole; b is the width of the outer side of the honeycomb; d is the horizontal distance between the center of each column of regular hexagons and the center of the rudder surface pivot; k is the wall thickness coefficient determined according to the magnitude of the rudder surface load, with a value of 0 to 1.
[0011] Furthermore, the honeycomb structure also includes connecting ribs, which are configured to connect two vertices of honeycombs in two adjacent columns that are on the same horizontal line, and the connected vertices are non-overlapping vertices in a column of honeycombs.
[0012] Furthermore, the width of the connecting rib is the average of the wall thicknesses of the two connected honeycomb cells.
[0013] Furthermore, the control surface also includes a front skin and a rear skin, and the honeycomb structure is disposed between the front skin and the rear skin. The front skin, the rear skin, and the honeycomb structure are formed into an integral structure through an additive manufacturing process.
[0014] Furthermore, the rudder is a solid structure. Due to the high stress at the rudder and honeycomb structure, the gap between the honeycomb structure and the rudder is solid.
[0015] Furthermore, the rudder angle is a hollow structure with internal reinforcing ribs. Since the stress between the honeycomb structure and the rudder angle and the front skin is small, the gap between the honeycomb structure and the rudder angle and the front skin is a hollow structure.
[0016] Furthermore, the vertices of the honeycomb are connected by transition rounded corners, which reduces stress concentration and improves structural strength.
[0017] This utility model has the following beneficial effects:
[0018] (1) This utility model adopts a honeycomb structure composed of regular hexagons of equal external dimensions. The strength design of the rudder surface is achieved by changing the wall thickness of the structure. Using additive manufacturing technology, the honeycomb structure and the upper and lower skins form an integral rudder surface structure of the same material. Differentiated structures are adopted according to different stress characteristics of the rudder surface. The rudder handle uses a solid structure to meet the high stress requirements. The rudder body uses a honeycomb structure to adapt to the stress gradient characteristics. The rudder angle adopts a hollow structure with reinforcing ribs to cope with low stress scenarios. This achieves a precise balance between structural strength and weight, while effectively reducing the weight of the rudder surface.
[0019] (2) In this utility model, the upper and lower edges of several honeycombs overlap to form a row, and each row is spaced apart. The honeycombs in a row have the same wall thickness. The honeycombs in different rows have a wall thickness that is inversely proportional to the horizontal distance between the center of the honeycomb and the center of the shaft hole. This ensures the uniform distribution of load, improves the overall stability of the structure, matches the material strength distribution with the stress distribution, avoids material waste, and ensures the balance of strength of each rudder surface.
[0020] (3) The part design and modeling process of this utility model is simple and efficient. Attached Figure Description
[0021] Figure 1 This is a schematic diagram of the overall structure of this utility model.
[0022] Figure 2 This is a schematic diagram of the rear skin side structure in this utility model.
[0023] Figure 3 This is a cross-sectional view of the present invention. Detailed Implementation
[0024] The technical solution of this utility model will be further described in detail below with reference to specific embodiments. However, this embodiment is not intended to limit this utility model. Any similar structure or similar variation of this utility model should be included in the protection scope of this utility model. The commas in this utility model all indicate the relationship between and. The English letters in this utility model are case-sensitive.
[0025] Aircraft control surfaces are typically fixed at the root. During flight, aerodynamic loads exert significant bending moments on the control surfaces, resulting in stress that is high at the root and low at the ends. A honeycomb structure design for the control surfaces allows for equal strength while maintaining their aerodynamic shape. This reduces the weight of the control mechanism, decreases the number of parts, and lowers assembly and manufacturing costs, thus shortening the production cycle.
[0026] like Figure 1As shown, this utility model provides a honeycomb structure aircraft control surface 1. The control surface 1 includes a control handle 11, a control body 12, and a control angle 13. The control handle 11 and the control angle 13 are located on the same side of the control body 12, with external dimensions of 50cm x 180cm x 10cm. The control handle 11 has a pivot hole 111, which is configured as the pivot for mounting the control surface 1. The control handle 11 has higher stress and adopts a solid structure. The stress of the control body 12 gradually increases from the end to the root, and a honeycomb structure is adopted. The stress of the control angle 13 is very low, and a hollow structure with internal reinforcing ribs 131 is adopted to reduce weight. Because the stress at the honeycomb structure and the control handle 11 is high, the gap between the honeycomb structure and the control handle 11 is solid. Because the stress between the honeycomb structure and the control angle 13 and the front skin is low, the gap between the honeycomb structure and the control angle 13 and the front skin is hollow.
[0027] like Figures 2-3 As shown, the rudder body 12 includes a front skin 123, a honeycomb structure, and a rear skin 124. The honeycomb structure is disposed between the front and rear skins. The front skin, rear skin, and honeycomb structure are formed into an integral structure through additive manufacturing. The honeycomb structure includes honeycomb 121, which is a regular hexagon with a width of 15mm. All honeycomb 121 have the same dimensions, and the top and bottom edges of the regular hexagon are parallel to the top and bottom surfaces of the rudder surface. The vertices of the honeycomb 121 are connected by transition fillets to reduce stress concentration and improve structural strength. The fillet radius is 1cm. Three honeycomb 121s are arranged in a row with their top and bottom edges overlapping. Six rows of honeycomb 121 are arranged vertically at a certain distance. The honeycomb cells in a row have the same wall thickness. The wall thickness of the honeycomb cells in different rows is inversely proportional to the horizontal distance between the center of the honeycomb cell and the center of the pivot hole. The wall thickness extends from the outside of the honeycomb cell towards the center. The formula for calculating the wall thickness is: In the formula, s is the wall thickness of each side of the honeycomb; L is the horizontal distance between the center of the outermost regular hexagon of the rudder surface and the center of the pivot hole; b is the width of the outer side of the honeycomb; d is the horizontal distance between the center of each column of regular hexagons and the center of the rudder surface pivot; k is the wall thickness coefficient determined according to the magnitude of the rudder surface load, with a value of 0 to 1. Based on the wall thickness calculation formula and the rudder surface dimensions, a wall thickness coefficient of 0.2 is taken, and the wall thicknesses of the 6 columns of honeycomb structure are 1.15cm, 1.5cm, 2cm, 2.4cm, 2.9cm, and 3.8cm, respectively.
[0028] like Figure 3As shown, the honeycomb structure also includes connecting ribs 122. The connecting ribs 122 are configured to connect two vertices of honeycombs on the same horizontal line in two adjacent columns, and the connected vertices are non-overlapping vertices in a column of honeycombs, connecting two adjacent columns of regular hexagons into a single unit. The width of the connecting rib 122 is the average of the wall thicknesses of the two honeycombs on both sides, thereby achieving equal strength for the rudder surface. Specifically, the width of the connecting rib 122 is the average of the wall thicknesses of the two connected honeycombs; that is, the width of the connecting rib connecting honeycomb wall thicknesses of 1.15cm and 1.5cm is 1.325cm, the width of the connecting rib connecting honeycomb wall thicknesses of 1.5cm and 2cm is 1.75cm, the width of the connecting rib connecting honeycomb wall thicknesses of 2cm and 2.4cm is 2.2cm, the width of the connecting rib connecting honeycomb wall thicknesses of 2.4cm and 2.9cm is 2.65cm, and the width of the connecting rib connecting honeycomb wall thicknesses of 2.9cm and 3.8cm is 3.35cm.
[0029] This invention employs a honeycomb structure composed of regular hexagons of equal external dimensions. The strength design of the control surface is achieved by varying the structural wall thickness. Using additive manufacturing technology, the honeycomb structure and the upper and lower skins form an integral control surface structure of the same material. Differentiated structures are adopted according to the different stress characteristics of the control surface. The rudder handle uses a solid structure to meet high stress requirements, the rudder body uses a honeycomb structure to adapt to the stress gradient characteristics, and the rudder angle uses a hollow structure with reinforcing ribs to cope with low stress scenarios. This achieves a precise balance between structural strength and weight, while effectively reducing the weight of the control surface.
[0030] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.
Claims
1. A honeycomb structure aircraft control surface, characterized in that, The rudder surface includes a rudder handle, a rudder body, and a rudder angle, with the rudder handle and rudder angle located on the same side of the rudder body; the rudder surface has a honeycomb structure, which includes honeycombs, with the upper and lower edges of several honeycombs overlapping to form a row, and each row is spaced apart.
2. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The honeycomb is in the shape of a regular hexagon.
3. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, All cells are the same size.
4. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The rudder handle is provided with a pivot hole, which is configured as a pivot for mounting the rudder surface.
5. The aircraft control surface with a honeycomb structure according to claim 4, characterized in that, Cellular cells arranged in a single column have the same wall thickness; for cellular cells arranged in different columns, the wall thickness is inversely proportional to the horizontal distance between the center of the cell and the center of the pivot hole.
6. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The honeycomb structure also includes connecting ribs, which are configured to connect two vertices of honeycombs in two adjacent columns that are on the same horizontal line, and the connected vertices are non-overlapping vertices in a column of honeycombs.
7. The aircraft control surface with a honeycomb structure according to claim 6, characterized in that, The width of the connecting rib is the average of the wall thicknesses of the two connected honeycomb cells.
8. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The control surface also includes a front skin and a rear skin, and the honeycomb structure is disposed between the front skin and the rear skin. The front skin, the rear skin, and the honeycomb structure are formed into an integral structure through an additive manufacturing process.
9. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The rudder is a solid structure, and the gap between the honeycomb structure and the rudder is solid.
10. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The rudder angle is a hollow structure with internal reinforcing ribs, and the gap between the honeycomb structure, the rudder angle, and the front skin is a hollow structure.
11. The aircraft control surface with a honeycomb structure according to claim 1, characterized in that, The vertices of the honeycomb are all connected by transition rounded corners.