A fixed-wing aircraft main wing skeleton structure

Abstract

The utility model discloses a fixed wing aircraft main wing skeleton structure, including the carbon fiber square tube one and carbon pole of horizontal setting, the carbon fiber square tube one with the carbon pole constitute the spar, the both ends of carbon fiber square tube one are equipped with main wing midwing spar, the both ends of main wing midwing spar are equipped with the carbon fiber square tube two and carbon fiber square tube three respectively of inclined setting, the both ends of carbon pole are equipped with the duct fixed part of the sleeve in main wing midwing spar, carbon fiber square tube one, carbon fiber square tube two and carbon fiber square tube three. Have very high tensile strength, effectively restrain the bending deformation and torsional deformation of the wing under the aerodynamic load, keep accurate aerodynamic shape, reduce aerodynamic efficiency loss. Provide better control response and accuracy. Carbon fiber material is under the action of alternating load, and its fatigue strength is very high, can significantly prolong the service life of structure.

Description

Technical Field

[0001] This utility model relates to the field of fixed-wing aircraft technology, specifically to a main wing skeleton structure for a fixed-wing aircraft. Background Technology

[0002] An aircraft is any flying object manufactured by humans, capable of taking off from the ground, flying in space, and controlled by humans for personal use.

[0003] However, existing aircraft main wing structures suffer from the following problems: they are typically based on experience, standard layouts (such as parallel carbon rods, simple carbon plate beams), or easily manufactured solutions. They lack in-depth optimization for specific loads, aerodynamic requirements, and weight targets. The connections between spars and ribs, and between the wing and fuselage, rely on adhesive bonding, lacking a progressive force transmission transition design. The pursuit of lightweighting often results in the adoption of minimum safety margins, without pre-setting redundant force transmission paths. Furthermore, deformation can lead to a decrease in the overall flight stability of the aircraft.

[0004] No effective solutions have yet been proposed to address the problems in the relevant technologies. Utility Model Content

[0005] In view of the problems in the related technologies, this utility model proposes a main wing frame structure for fixed-wing aircraft to overcome the above-mentioned technical problems existing in the existing related technologies.

[0006] Therefore, the specific technical solution adopted by this utility model is as follows:

[0007] A main wing frame structure for a fixed-wing aircraft includes a transversely arranged carbon fiber square tube and a carbon rod, wherein the carbon fiber square tube and the carbon rod form a wing spars.

[0008] The carbon fiber square tube one has a main wing mid-section wing spars at both ends, and the main wing mid-section wing spars have inclined carbon fiber square tubes two and three at both ends respectively. The carbon rod has duct fixing members at both ends that are sleeved on the main wing mid-section wing spars, the carbon fiber square tube one, the carbon fiber square tube two, and the carbon fiber square tube three.

[0009] The two sets of carbon fiber square tubes are provided with a main wing fuselage connecting fastener sleeved on the carbon fiber square tube at one end that is close to each other.

[0010] The bottom ends of the second and third carbon fiber square tubes are connected to the main wing latches.

[0011] Preferably, the carbon fiber square tube is symmetrically provided with retractable landing gear fixing components that are connected to the carbon rod.

[0012] Preferably, the two sets of main wing fuselage connecting fasteners are provided with a fuselage main wing connecting fastener sleeved on the side close to each other, and the two sets of main wing fuselage connecting fasteners are provided with a main wing fuselage connecting fastener sleeved on the side far from each other.

[0013] Preferably, the main wing latch is provided with carbon rod sleeves that are respectively connected to the second and third carbon fiber square tubes.

[0014] Preferably, the connection points between the carbon rod and the main wing fuselage connecting fastener, the fuselage main wing connecting fastener, the duct fastener, and the retractable landing gear fastener are provided with a low-density foam material skin adhesive for bonding and fixing.

[0015] Preferably, the main wing has two layers of low-density foam material on its outer surface as a skin.

[0016] The beneficial effects of this invention are as follows: A wing spars are formed by one transverse carbon fiber square tube and one transverse carbon rod, while stringers are formed by two carbon fiber square tubes and two carbon fiber square tubes. This unique arrangement, with two layers of low-density foam material serving as the skin, is glued to the frame, enveloping the entire skeleton. This achieves the required structural strength with minimal weight and ensures even stress distribution throughout the main wing. It possesses extremely high tensile strength, effectively suppressing bending and torsional deformation of the wing under aerodynamic loads, maintaining a precise aerodynamic shape, and reducing aerodynamic efficiency loss. This provides better handling responsiveness and precision. Furthermore, the carbon fiber material exhibits extremely high fatigue strength under alternating loads, significantly extending the structural lifespan.

[0017] By using low-density foam material to cover and glue the structure, the problem of shaking and breakage is effectively reduced, the torsional and bending strength is enhanced, the structure is more stable, and the front strong and rear weak stringers are matched with the aerodynamic pressure distribution to further reduce weight. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is an exploded view of the main wing frame structure of a fixed-wing aircraft according to an embodiment of the present utility model;

[0020] Figure 2 This is a cross-sectional view of the main wing frame structure of a fixed-wing aircraft according to an embodiment of the present utility model;

[0021] Figure 3 This is a schematic diagram of the main wing skeleton structure of a fixed-wing aircraft according to an embodiment of the present utility model.

[0022] In the picture:

[0023] 1. Carbon fiber square tube one; 2. Carbon rod; 3. Main wing mid-section spars; 4. Carbon fiber square tube two; 5. Carbon fiber square tube three; 6. Duct fastener; 7. Main wing fuselage connection fastener one; 8. Fuselage main wing connection fastener; 9. Main wing fuselage connection fastener two; 10. Carbon rod sleeve; 11. Main wing latch; 12. Landing gear retraction and extension fastener; 13. Main wing; 14. Skin. Detailed Implementation

[0024] To further illustrate the various embodiments, the present invention provides accompanying drawings, which are part of the disclosure of the present invention. These drawings are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.

[0025] According to an embodiment of the present invention, a main wing skeleton structure for a fixed-wing aircraft is provided.

[0026] Example 1:

[0027] like Figure 1-3 As shown, the main wing frame structure of the fixed-wing aircraft according to an embodiment of the present invention includes a carbon fiber square tube 1 and a carbon rod 2 arranged laterally, wherein the carbon fiber square tube 1 and the carbon rod 2 form a wing spars.

[0028] The carbon fiber square tube 1 has a main wing mid-section wing spars 3 at both ends. The main wing mid-section wing spars 3 have two inclined carbon fiber square tubes 4 and 5 at both ends. The carbon rod 2 has duct fixing members 6 at both ends that are sleeved on the main wing mid-section wing spars 3, the carbon fiber square tube 1, the carbon fiber square tube 4, and the carbon fiber square tube 5.

[0029] The two sets of carbon fiber square tubes 4 are provided with a main wing fuselage connecting fastener 7 sleeved on the carbon fiber square tube 1 at one end that is close to each other.

[0030] The bottom ends of the second carbon fiber square tube 4 and the third carbon fiber square tube 5 are connected to the main wing latch 11.

[0031] Example 2:

[0032] like Figure 1-3As shown, the carbon fiber square tube 1 is symmetrically provided with retractable landing gear fixing parts 12 connected to the carbon rod 2. On the side of the two sets of main wing fuselage connecting fixing parts 7 that are close to each other, there is a fuselage main wing connecting fixing part 8 that is sleeved on the carbon fiber square tube 1 and the carbon rod 2. On the side of the two sets of fuselage main wing connecting fixing parts 8 that are far apart from each other, there is a main wing fuselage connecting fixing part 9 that is sleeved on the carbon fiber square tube 1. The main wing latch 11 is provided with carbon rod sleeves 10 that are respectively connected to the carbon fiber square tube 2 4 and the carbon fiber square tube 3 5.

[0033] Example 3:

[0034] like Figure 1-3 As shown, the connection between the carbon rod 2 and the main wing fuselage connecting fastener 7, the fuselage main wing connecting fastener 8, the duct fastener 6 and the retractable landing gear fastener 12 is provided with a low-density foam material skin adhesive to fix it, including the main wing 13, the outer surface of the main wing 13 is provided with two layers of low-density foam material as skin 14.

[0035] In summary, by utilizing the above-mentioned technical solution of this utility model, a wing spars are formed by a transverse carbon fiber square tube 1 and a transverse carbon rod 2, and stringers are formed by two carbon fiber square tubes 4 and two carbon fiber square tubes 5. This unique arrangement, with two layers of low-density foam material as the skin, is glued to the frame, encasing the entire frame. This achieves the required structural strength with minimal weight and ensures even force distribution throughout the main wing. The low-density foam material skin, glued and fixed, effectively reduces swaying and breakage, enhances torsional and bending strength, and makes the structure more stable. The front-stronger, rear-weaker stringers match the aerodynamic pressure distribution, further reducing weight.

[0036] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A main wing frame structure for a fixed-wing aircraft, characterized in that, It includes a transversely arranged carbon fiber square tube (1) and a carbon rod (2), wherein the carbon fiber square tube (1) and the carbon rod (2) form a wing beam; The carbon fiber square tube one (1) is provided with a main wing mid-section wing spars (3) at both ends. The main wing mid-section wing spars (3) are respectively provided with inclined carbon fiber square tube two (4) and carbon fiber square tube three (5) at both ends. The carbon rod (2) is provided with duct fixing parts (6) sleeved on the main wing mid-section wing spars (3), the carbon fiber square tube one (1), the carbon fiber square tube two (4) and the carbon fiber square tube three (5) at both ends. Two sets of carbon fiber square tubes (4) are provided with a main wing fuselage connecting fastener (7) sleeved on the carbon fiber square tube (1) at one end close to each other; The bottom ends of the carbon fiber square tube 2 (4) and the carbon fiber square tube 3 (5) are connected to the main wing latch (11).

2. The main wing frame structure of a fixed-wing aircraft according to claim 1, characterized in that, The carbon fiber square tube (1) is symmetrically provided with retractable landing gear fixing parts (12) that are connected to the carbon rod (2).

3. The main wing frame structure of a fixed-wing aircraft according to claim 2, characterized in that, On the side of the two sets of main wing fuselage connecting fasteners (7) that are close to each other, there is a fuselage main wing connecting fastener (8) that is sleeved on the carbon fiber square tube (1) and the carbon rod (2). On the side of the two sets of main wing fuselage connecting fasteners (8) that are far apart from each other, there is a main wing fuselage connecting fastener (9) that is sleeved on the carbon fiber square tube (1).

4. The main wing frame structure of a fixed-wing aircraft according to claim 3, characterized in that, The main wing latch (11) is provided with carbon rod sleeves (10) that are respectively connected to the second carbon fiber square tube (4) and the third carbon fiber square tube (5).

5. The main wing frame structure of a fixed-wing aircraft according to claim 4, characterized in that, The carbon rod (2) is fixed with a low-density foam material skin adhesive at the connection points with the main wing fuselage connecting fastener (7), the fuselage main wing connecting fastener (8), the duct fastener (6), and the landing gear retraction fastener (12).

6. The main wing frame structure of a fixed-wing aircraft according to claim 1, characterized in that, Includes a main wing (13), the outer surface of which is provided with two layers of low-density foam material as skin (14).

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