A high performance composite aircraft aileron
By using high-performance composite materials, the traditional wing rib structure is eliminated and the combination of foam filling structure and skin is used to achieve the effects of reducing components, easy assembly, stable structure and low cost.
Patent Information
- Application Number
- CN202420943697.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-30
- Publication Date
- 2025-04-08
- Estimated Expiration
- 2034-04-30
AI Technical Summary
There are many components of existing aircraft ailerons, and the connection stability requires multiple verification and testing. In order to reduce structural weight, weight reduction holes need to be opened on the wing ribs, which increases production processes and costs.
Aircraft ailerons designed with high-performance composite materials include skin, foam-filled structure and wing spar. The foam-filled structure is wing-shaped and the skin covers the outside. The traditional wing rib structure is eliminated and can be quickly assembled and fixed through the installation port and locking hole.
The component layout is reduced, the contact area with the skin and spar is increased, the overall performance and structural stability is improved, the production process is simplified, and the cost is reduced.
Smart Images
Figure CN222728237U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aerospace equipment, in particular to a high-performance composite material aircraft aileron. Background Art
[0002] Ailerons are used to generate rolling moment in an aircraft to ensure lateral maneuverability. They are usually located outside or inside the trailing edge of the wing. Existing ailerons are usually composed of wing beams, wing ribs, skins, and trailing edge profiles. There are many components, and the connection stability between the components needs to be verified and tested many times. In order to reduce the weight of the structure, it is also necessary to open weight-reducing holes on the wing ribs, etc., which increases the production process. Utility Model Content
[0003] The technical problem to be solved by the utility model is to provide a high-performance composite aircraft aileron with fewer components, convenient assembly, short production cycle, low cost and good structural stability.
[0004] In order to solve the above technical problems, the technical solution adopted by the utility model is: a high-performance composite aircraft aileron, including a skin, a foam filling structure and a wing spar, the foam filling structure is an airfoil, and the skin covers the outside of the foam filling structure; the foam filling structure includes a leading edge, and the foam filling structure is provided with an installation opening that penetrates along the length direction of the foam filling structure near the leading edge, and the wing spar is arranged in the installation opening; the leading edge is provided with an installation groove that is connected to the installation opening, and the skin is provided with a hollow portion corresponding to the installation groove; the wing spar is provided with a locking hole corresponding to the installation groove.
[0005] Furthermore, the cross-section of the mounting opening is trapezoidal, and the cross-section of the wing beam perpendicular to its length direction is trapezoidal to match the mounting opening.
[0006] Furthermore, the foam filling structure is a PMI foam filling structure.
[0007] Furthermore, the skin comprises a carbon fiber layer, a foam layer and a glass fiber layer, the carbon fiber layer, the foam layer and the glass fiber layer are stacked in sequence, and the glass fiber layer is bonded to the foam filling structure.
[0008] Furthermore, the carbon fiber layer has a thickness of 0.3 mm, the foam layer has a thickness of 2.5 mm, and the glass fiber layer has a thickness of 0.15 mm.
[0009] Furthermore, the wing beam comprises a carbon fiber layer, a foam layer and a glass fiber layer, the carbon fiber layer, the foam layer and the glass fiber layer are stacked in sequence, and the carbon fiber layer is opposite to the mounting groove.
[0010] Furthermore, the thickness of the carbon fiber layer is 0.75 mm, the thickness of the foam layer is 13.5 mm, and the thickness of the glass fiber layer is 0.75 mm.
[0011] The beneficial effects of the utility model are: adopting a foam filling structure, eliminating the traditional wing rib structure, reducing the component layout, and increasing the contact area with the skin and wing spar; adopting a composite material layout of foam materials, skins, etc. to improve the overall performance; when the wing is under load, it can effectively provide support for the skin and the wing spar to maintain the shape of the wing; through the installation port set in the foam filling structure, the wing spar is used to quickly assemble and abut against it in multiple directions to ensure load transfer; the installation groove set at the leading edge and the locking hole of the wing spar are used for connecting and fixing the aileron to the trailing edge of the wing. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 A schematic diagram of the structure of a high-performance composite aircraft aileron according to a specific embodiment of the utility model;
[0013] Figure 2 The exploded view of a high-performance composite aircraft aileron according to a specific implementation mode of the utility model.
[0014] Description of labels:
[0015] 1. Skin; 2. Foam filling structure; 21. Leading edge; 22. Trailing edge; 23. Mounting port; 24. Mounting slot; 3. Wing beam. DETAILED DESCRIPTION
[0016] In order to explain the technical content, achieved objectives and effects of the present invention in detail, the following is an explanation in conjunction with the implementation modes and the accompanying drawings.
[0017] Please refer to Figure 1 and Figure 2 A high-performance composite aircraft aileron comprises a skin 1, a foam filling structure 2 and a spar 3, wherein the foam filling structure 2 is airfoil-shaped, and the skin 1 covers the outside of the foam filling structure 2; the foam filling structure 2 comprises a leading edge 21, and a mounting opening 23 penetrating along the length direction of the foam filling structure 2 is provided on the foam filling structure 2 near the leading edge 21, and the spar 3 is arranged in the mounting opening 23; a mounting groove 24 communicating with the mounting opening 23 is provided on the leading edge 21, and a hollow portion is provided on the skin 1 corresponding to the mounting groove 24; and a locking hole is provided on the spar 3 corresponding to the mounting groove 24.
[0018] From the above description, it can be seen that the beneficial effects of the utility model are: adopting a foam filling structure 2, eliminating the traditional wing rib structure, reducing the component layout, and increasing the contact area with the skin 1 and the wing beam 3; adopting a composite material arrangement of foam materials, skins, etc. to improve the overall performance; when the wing is under load, it can effectively provide support for the skin 1 and the wing beam 3 to maintain the shape of the wing; through the installation port 23 set in the foam filling structure 2, the wing beam 3 is used to quickly assemble and abut with it in multiple directions to ensure load transfer; through the installation groove 24 set at the leading edge 21 and the locking hole of the wing beam 3, the aileron is used to connect and fix the wing to the trailing edge 22 of the wing.
[0019] Furthermore, the cross section of the installation opening 23 is trapezoidal, and the cross section of the spar 3 perpendicular to its length direction is trapezoidal to match the installation opening 23 .
[0020] From the above description, it can be seen that through the trapezoidal design of the mounting opening 23 and the spar 3, the lateral load can be evenly transferred to the spar 3 to match the changes in the inclined two side surfaces of the wing-shaped structure; at the same time, it also avoids the situation where it is difficult to distinguish the front and back of the traditional tubular spar 3 or the plate spar 3 during assembly, and the operator can only insert and fix the spar 3 along the preset shape of the mounting opening 23.
[0021] Furthermore, the foam filling structure 2 is a PMI foam filling structure 2 .
[0022] From the above description, it can be seen that PMI foam, as a lightweight and high-strength foam plastic, is currently the hardest structural core material under the same density conditions. It can provide sufficient strength for the aileron and greatly reduce the mass.
[0023] Furthermore, the skin 1 comprises a carbon fiber layer, a foam layer and a glass fiber layer, the carbon fiber layer, the foam layer and the glass fiber layer are stacked in sequence, and the glass fiber layer is bonded to the foam filling structure 2 .
[0024] From the above description, it can be seen that the sandwich structure of carbon fiber layer, foam layer and glass fiber layer is adopted to optimize and improve the traditional metal skin 1, and the material properties of carbon fiber layer, foam layer and glass fiber layer are utilized to provide the skin 1 with better comprehensive performance while reducing the weight; the foam layer adopts PMI foam; the carbon fiber layer and the glass fiber layer are carbon fiber cloth and glass fiber cloth respectively; the outermost layer of fiber cloth of the composite fiber product is the position directly subjected to force, and peeling defects are prone to occur during use. In order to avoid this situation, carbon fiber cloth with better mechanical properties is used in the main load direction of the product.
[0025] Furthermore, the carbon fiber layer has a thickness of 0.3 mm, the foam layer has a thickness of 2.5 mm, and the glass fiber layer has a thickness of 0.15 mm.
[0026] From the above description, it can be seen that the skin 1 uses the foam layer as the main core structure, and the combination of 0.3mm carbon fiber layer, 2.5mm foam layer and 0.15 glass fiber layer is the best thickness selection.
[0027] Furthermore, the spar 3 includes a carbon fiber layer, a foam layer and a glass fiber layer, which are stacked in sequence, and the carbon fiber layer is opposite to the mounting groove 24 .
[0028] From the above description, it can be seen that the sandwich structure of the carbon fiber layer, the foam layer and the glass fiber layer is adopted to optimize and improve the traditional metal wing beam 3, and the material properties of the carbon fiber layer, the foam layer and the glass fiber layer are utilized to provide the wing beam 3 with better comprehensive performance while reducing the weight; the foam layer adopts PMI foam; the carbon fiber layer and the glass fiber layer are carbon fiber cloth and glass fiber cloth respectively; the outermost layer of fiber cloth of the composite fiber product is the position directly subjected to force, specifically corresponding to the side of the wing beam 3 close to the mounting groove 24, which is prone to peeling defects during use. In order to avoid this situation, carbon fiber cloth with better mechanical properties is used in the main load direction of the product.
[0029] Furthermore, the thickness of the carbon fiber layer is 0.75 mm, the thickness of the foam layer is 13.5 mm, and the thickness of the glass fiber layer is 0.75 mm.
[0030] From the above description, it can be seen that the spar 3 uses the foam layer as the main core structure, and the combination of 0.75mm carbon fiber layer, 13.5mm foam layer and 0.75mm glass fiber layer is the best thickness selection.
[0031] Reference Figure 1 and Figure 2 , Embodiment 1 of the present utility model is:
[0032] Application scenarios of the utility model: In the production process of existing ailerons, since they mostly use structures such as wing beams 3, wing ribs, skins 1, and trailing edge 22 profiles, there are many components. The connection stability between the components needs to be verified and tested multiple times, and in order to reduce the weight of the structure, weight-reducing holes need to be opened on the wing ribs, etc., which increases the production process.
[0033] like Figure 1 and Figure 2As shown, a high-performance composite aircraft aileron of the present embodiment includes a skin 1, a foam filling structure 2 and a spar 3, wherein the foam filling structure 2 is an airfoil shape, and the skin 1 covers the outside of the foam filling structure 2; the foam filling structure 2 is a PMI foam filling structure 2, and the foam filling structure 2 includes a leading edge 21 and a trailing edge 22, wherein the leading edge 21 is an end connected to the wing, and the trailing edge 22 is an end away from the wing; the foam filling structure 2 is provided with a mounting opening 23 passing through the foam filling structure 2 along the length direction near the leading edge 21, and the spar 3 is arranged in the mounting opening 23; the leading edge 21 is provided with a mounting groove 24 connected to the mounting opening 23, and the skin 1 is provided with a hollow portion corresponding to the mounting groove 24; the spar 3 is provided with a locking hole corresponding to the mounting groove 24.
[0034] The cross section of the installation opening 23 is trapezoidal, and the cross section of the spar 3 perpendicular to its length direction is trapezoidal to match the installation opening 23 .
[0035] The skin 1 and the spar 3 both adopt a sandwich structure. The skin 1 includes a carbon fiber layer, a PMI foam layer and a glass fiber layer, which are stacked in sequence, and the glass fiber layer is bonded to the foam filling structure 2; the carbon fiber layer is 0.3 mm thick, the PMI foam layer is 2.5 mm thick, and the glass fiber layer is 0.15 mm thick.
[0036] The spar 3 includes a carbon fiber layer, a PMI foam layer and a glass fiber layer, which are stacked in sequence, and the carbon fiber layer is opposite to the mounting groove 24. The carbon fiber layer has a thickness of 0.75 mm, the PMI foam layer has a thickness of 13.5 mm, and the glass fiber layer has a thickness of 0.75 mm.
[0037] The working principle of the utility model is as follows: the rib structure of the traditional aileron is replaced by a foam filling structure 2, and the foam filling structure 2 is in full contact with the skin 1 and the wing spar 3 to effectively transfer the load; at the same time, the sandwich structure of the skin 1 and the wing spar 3 is combined to reduce the weight while improving the overall performance.
[0038] In summary, the utility model provides a high-performance composite aircraft aileron, which adopts a foam filling structure, eliminates the traditional wing rib structure, reduces the component layout, and increases the contact area with the skin and the wing spar; adopts a composite material arrangement of foam materials, skins, etc. to improve the overall performance; when the wing is under load, it can effectively provide support for the skin and the wing spar to maintain the shape of the wing; through the installation port set in the foam filling structure, it is used to quickly assemble the wing spar and abut it in multiple directions to ensure load transfer; through the installation groove set at the leading edge and the locking hole of the wing spar, the aileron is used to connect and fix the aileron to the trailing edge of the wing.
[0039] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent transformations made using the contents of the specification and drawings of the present invention, or directly or indirectly applied in the relevant technical field, are also included in the patent protection scope of the present invention.
Claims
1. A high performance composite aircraft aileron, characterized in that: It includes a skin, a foam filling structure and a wing beam, the foam filling structure is in an airfoil shape, and the skin covers the outer side of the foam filling structure; the foam filling structure includes a leading edge, and a mounting opening that penetrates along the length direction of the foam filling structure is provided on the foam filling structure near the leading edge, and the wing beam is arranged in the mounting opening; a mounting groove that is connected to the mounting opening is provided on the leading edge, and the skin is provided with a hollow portion corresponding to the mounting groove; and the wing beam is provided with a locking hole corresponding to the mounting groove.
2. The high performance composite aircraft aileron according to claim 1, characterized in that: The cross section of the installation opening is trapezoidal, and the cross section of the wing beam perpendicular to its length direction is trapezoidal matching the installation opening.
3. The high performance composite aircraft aileron according to claim 1, characterized in that: The foam filling structure is a PMI foam filling structure.
4. The high performance composite aircraft aileron according to claim 1, characterized in that: The skin comprises a carbon fiber layer, a foam layer and a glass fiber layer, which are stacked in sequence, and the glass fiber layer is fitted with a foam filling structure.
5. The high performance composite aircraft aileron according to claim 4, characterized in that: The thickness of the carbon fiber layer is 0.3 mm, the thickness of the foam layer is 2.5 mm, and the thickness of the glass fiber layer is 0.15 mm.
6. The high performance composite aircraft aileron according to claim 1, characterized in that: The wing beam comprises a carbon fiber layer, a foam layer and a glass fiber layer, which are stacked in sequence, and the carbon fiber layer is opposite to the installation groove.
7. The high performance composite aircraft aileron according to claim 6, characterized in that: The thickness of the carbon fiber layer is 0.75 mm, the thickness of the foam layer is 13.5 mm, and the thickness of the glass fiber layer is 0.75 mm.