A low altitude aircraft spar SMC substrate structure

Abstract

The utility model relates to a kind of low altitude aircraft paddle root SMC matrix structure.It solves the problem that aircraft paddle root is heavy in prior art, difficult to meet the demand of low altitude aircraft to lightweight and high efficiency.It includes vinyl resin base layer, vinyl resin base layer both sides are provided with rigid support structure, rigid support structure and vinyl resin base layer are circumferentially provided with compression wear-resistant structure, and a plurality of series stable structures are provided in compression wear-resistant structure and are threaded in rigid support structure and vinyl resin base layer.The utility model has the advantages that on the basis of greatly reducing weight, it has high rigidity, strong compression wear resistance and structural stability suitable for low altitude aircraft, and realizes the demand of aircraft paddle root lightweight and high efficiency.

Description

Technical Field

[0001] This utility model relates to the field of sheet metal technology, specifically to an SMC substrate structure for the propeller root of a low-altitude aircraft. Background Technology

[0002] The rotor root of low-altitude aircraft (such as drones and electric vertical takeoff and landing aircraft) is a key component connecting the rotor to the fuselage. It bears complex dynamic loads and vibration impacts, placing extremely high demands on the lightweight, high strength, high rigidity, and fatigue resistance of its materials. When existing aircraft are subjected to gusts during flight, rigid or semi-rigid rotors are unable to effectively eliminate the effects of gusts, causing the aircraft to sway and even crash. When hitting treetops, their high rigidity and low cushioning also make them prone to damage. When stationary, the rotor blades occupy a large area, which is not conducive to shipboard deployment and storage, and they are also prone to mechanical fatigue damage due to vibration under wind. In addition, although using traditional metal materials as the base material for the rotor root of aircraft has high strength and rigidity, its weight is large and cannot meet the requirements of lightweight and high efficiency for low-altitude aircraft.

[0003] To address the shortcomings of existing technologies, people have conducted long-term explorations and proposed various solutions. For example, Chinese patent literature discloses a flexible rotor blade for a rotary-wing aircraft [CN114954936B], which includes a blade body, a structural component, and a blade substrate wrapped around the structural component. The root of the structural component is fixed to a blade root connector. The structural component is assembled from several hinged joints, with rotation angles set between the joints to allow the blade body to bend to a certain extent above and below the blade's plane of rotation.

[0004] The above solution has solved to some extent the problems of poor stability, easy damage and large space occupation of the propeller blades of existing aircraft. However, the solution still has many shortcomings. For example, the base material of the propeller root of traditional aircraft is heavy, which makes it difficult to meet the requirements of low-altitude aircraft for lightweight and high efficiency. Summary of the Invention

[0005] The purpose of this invention is to address the above-mentioned problems by providing a low-altitude aircraft rotor root SMC substrate structure.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a low-altitude aircraft rotor root SMC substrate structure, comprising a vinyl ester resin base layer, rigid support structures provided on both sides of the vinyl ester resin base layer, a pressure-resistant and wear-resistant structure provided circumferentially on the rigid support structure and the vinyl ester resin base layer, and a plurality of series stabilizing structures passing through the rigid support structure and the vinyl ester resin base layer within the pressure-resistant and wear-resistant structure.

[0007] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, the vinyl ester resin base layer includes a vinyl ester main layer, and resin fiber layers mixed with toughening agents and low-shrinkage agents are disposed on both sides of the vinyl ester main layer, with a pressure-relieving gap between the resin fiber layers and the vinyl ester main layer.

[0008] In the aforementioned SMC substrate structure for the rotor root of a low-altitude aircraft, several equally spaced support members are fixedly fitted into the pressure relief gap.

[0009] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, the rigid support structure includes a support layer, and a plurality of support connectors are provided on the side of the support layer near the resin fiber layer, with a filling cavity formed between two adjacent support connectors.

[0010] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, the cavity is filled with a flexible curing agent, and a glass fiber layer is disposed on the surface of the support layer. In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, the pressure-resistant and wear-resistant structure includes a shaped inner frame layer, and a flexible polymer layer is provided on the outer periphery of the shaped inner frame layer.

[0011] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, a glass microsphere layer is disposed between the flexible polymer layer and the shaped inner frame layer.

[0012] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, the series stabilization structure includes a series seat. The two ends of the series seat are positioned by slots set in the inner wall of the shaping inner frame layer, and the series seats are equidistantly distributed within the substrate structure.

[0013] In the aforementioned SMC substrate structure for a low-altitude aircraft rotor root, a first strip-shaped clearance groove is provided on the support layer for the tandem seat to pass through, and a second strip-shaped clearance groove is correspondingly provided on the vinyl main layer and the resin fiber layer for the tandem seat to pass through.

[0014] In the aforementioned SMC substrate structure for the rotor root of a low-altitude aircraft, the tandem base is provided with several positioning chucks that correspond to the first strip-shaped clearance groove and the second strip-shaped clearance groove, respectively.

[0015] Compared with existing technologies, the advantages of this invention are as follows: By combining a vinyl ester main layer with a resin fiber layer, along with pressure-relieving gaps and support components, the weight of the substrate is significantly reduced while maintaining structural strength and cushioning performance. Secondly, the rigid support structure, through the design of a support layer, support connector, and cavity filled with flexible curing agent, combined with a surface glass fiber layer, not only strengthens the rigidity of the substrate to ensure performance but also avoids weight redundancy caused by increased rigidity. Furthermore, the pressure-resistant and wear-resistant structure achieves excellent pressure resistance and wear resistance while further controlling the overall weight. Finally, the series seat with positioning chuck, along with slots and strip-shaped clearance grooves, stably connects each layer, ensuring the synergy and stability of the overall structure of the substrate. Ultimately, while significantly reducing weight, it possesses high rigidity, strong pressure resistance and wear resistance, and structural stability suitable for low-altitude aircraft, fulfilling the requirements of lightweight and high-efficiency propeller roots for aircraft. Attached Figure Description

[0016] Figure 1 This is a cross-sectional view of the present invention; Figure 2 This is a schematic diagram of the vinyl ester resin base layer structure of this utility model; Figure 3 This is a detailed structural cross-sectional view of the vinyl resin base layer in this utility model; Figure 4 This is a schematic diagram of the rigid support structure in this utility model; Figure 5 This is a detailed sectional view of the pressure-resistant and wear-resistant structure in this utility model; Figure 6 This is a schematic diagram of the series seat structure in this utility model; In the diagram: 1. Vinyl resin base layer; 11. Vinyl main layer; 12. Resin fiber layer; 13. Pressure-relieving gap; 14. Support component; 2. Rigid support structure; 21. Support layer; 22. Support connector; 23. Filling cavity; 24. Glass fiber layer; 3. Pressure-resistant and wear-resistant structure; 31. Shaping inner frame layer; 32. Flexible polymer layer; 33. Glass microsphere layer; 4. Series stabilizing structure; 41. Series seat; 42. Slot; 43. First strip relief groove; 44. Second strip relief groove; 45. Positioning chuck. Detailed Implementation

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] like Figure 1-6 As shown, a low-altitude aircraft rotor root SMC substrate structure includes a vinyl ester resin base layer 1, rigid support structures 2 are provided on both sides of the vinyl ester resin base layer 1, and a pressure-resistant and wear-resistant structure 3 is provided circumferentially on the rigid support structure 2 and the vinyl ester resin base layer 1. Several series stabilizing structures 4 are provided in the pressure-resistant and wear-resistant structure 3, which are inserted into the rigid support structure 2 and the vinyl ester resin base layer 1.

[0019] The vinyl resin base layer 1 includes a vinyl main layer 11, and resin fiber layers 12 mixed with toughening agents and low shrinkage agents are disposed on both sides of the vinyl main layer 11, and there is a pressure-relieving gap 13 between the resin fiber layers 12 and the vinyl main layer 11.

[0020] The resin fiber layer 12 is used to improve the toughness of the substrate and reduce molding shrinkage while avoiding weight redundancy. The pressure relief gap 13 between the resin fiber layer 12 and the vinyl main layer 11 is used to buffer the stress impact when the paddle root is working. The support members 14 that are equidistantly embedded in the pressure relief gap 13 can prevent structural deformation caused by the gap while retaining the buffering function, and ensure the support stability of the base layer 1.

[0021] As can be seen, several equally spaced support members 14 are fixedly fitted inside the pressure relief gap 13.

[0022] In detail, the rigid support structure 2 includes a support layer 21, and a plurality of support connecting seats 22 are provided on the side of the support layer 21 near the resin fiber layer 12, and a filling cavity 23 is formed between two adjacent support connecting seats 22.

[0023] Preferably, the cavity 23 is filled with a flexible curing agent, and the surface of the support layer 21 is provided with a glass fiber layer 24. The structure 2 is equipped with flexible materials to help buffer stress and the weight of the fully rigid structure is added; the glass fiber layer 24 on the surface of the support layer 21 further improves rigidity and fatigue resistance, ensuring that the structure 2 meets the rigidity requirements under the premise of lightweight.

[0024] Furthermore, the pressure-resistant and wear-resistant structure 3 includes a shaped inner frame layer 31, and a flexible polymer layer 32 is disposed on the outer periphery of the shaped inner frame layer 31.

[0025] Furthermore, a glass microsphere layer 33 is disposed between the flexible polymer layer 32 and the shaped inner frame layer 31.

[0026] The shaping inner frame layer 31 provides a shaping base for the circumferential structure and prevents the overall deformation of the substrate. The flexible polymer layer 32 is used to directly improve the wear resistance of the propeller root and cope with external friction during low-altitude flight. The glass microsphere layer 33 utilizes the lightweight and high compressive strength of glass microspheres to further reduce the overall weight while enhancing circumferential compressive strength.

[0027] Specifically, the series stabilizing structure 4 includes a series seat 41, the two ends of which are positioned by slots 42 provided on the inner wall of the shaping inner frame layer 31, and the series seats 41 are equidistantly distributed within the base material structure.

[0028] More specifically, the support layer 21 is provided with a first strip-shaped relief groove 43 through which the series seat 41 can pass, and the vinyl main layer 11 and the resin fiber layer 12 are respectively provided with a second strip-shaped relief groove 44 through which the series seat 41 can pass.

[0029] In addition, the series seat 41 is provided with several positioning chucks 45 that correspond to the first strip-shaped relief groove 43 and the second strip-shaped relief groove 44 respectively.

[0030] The positioning chuck 45 engages with the first strip-shaped clearance groove 43 and the second strip-shaped clearance groove 44 to prevent relative displacement of each layer. Combined with the equidistant distribution design of the series seat 41, it ensures that the overall structure is subjected to uniform force and realizes the coordinated and stable operation of each core layer.

[0031] In summary, the principle of this embodiment is as follows: resin fiber layers 12 are provided on both sides of the vinyl ester resin base layer 1, and several equidistant support members are embedded in its pressure-relieving gaps 13, which reduces the material weight and ensures the stability of the support; the rigid support structure 2 enhances rigidity while avoiding weight redundancy; the pressure-resistant and wear-resistant structure 3 takes into account shaping, wear resistance and lightweighting; the series stabilizing structure 4 realizes the stable connection of each layer, and finally makes the overall structure adaptable to the lightweighting and energy-saving requirements of low-altitude aircraft.

[0032] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to substitute them, without departing from the spirit of this utility model or exceeding the scope defined by the appended claims.

[0033] Although this document frequently uses terms such as vinyl ester resin base layer 1, vinyl ester main layer 11, resin fiber layer 12, pressure-relieving gap 13, support member 14, rigid support structure 2, support layer 21, support connector 22, filling cavity 23, glass fiber layer 24, pressure-resistant and wear-resistant structure 3, shaping inner frame layer 31, flexible polymer layer 32, glass microsphere layer 33, series stabilizing structure 4, series seat 41, slot 42, first strip clearance groove 43, second strip clearance groove 44, positioning chuck 45, etc., the possibility of using other terms is not excluded. The use of these terms is merely for the convenience of describing and explaining the essence of this utility model; interpreting them as any additional limitation would contradict the spirit of this utility model.

Claims

1. A low-altitude aircraft rotor root SMC substrate structure, comprising a vinyl ester resin base layer (1), characterized in that, Rigid support structures (2) are provided on both sides of the vinyl resin base layer (1). The rigid support structure (2) and the vinyl resin base layer (1) are provided with a pressure-resistant and wear-resistant structure (3) in the circumferential direction. The pressure-resistant and wear-resistant structure (3) is provided with a number of series stabilizing structures (4) that pass through the rigid support structure (2) and the vinyl resin base layer (1).

2. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 1, characterized in that, The vinyl resin base layer (1) includes a vinyl main layer (11), and resin fiber layers (12) mixed with toughening agent and low shrinkage agent are provided on both sides of the vinyl main layer (11), and there is a pressure-relieving gap (13) between the resin fiber layer (12) and the vinyl main layer (11).

3. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 2, characterized in that, The pressure relief gap (13) is fixedly fitted with several equally spaced support members (14).

4. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 3, characterized in that, The rigid support structure (2) includes a support layer (21), and a plurality of support connecting seats (22) are provided on the side of the support layer (21) near the resin fiber layer (12), and a filling cavity (23) is formed between two adjacent support connecting seats (22).

5. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 4, characterized in that, The cavity (23) is filled with a flexible curing agent, and the surface of the support layer (21) is provided with a glass fiber layer (24).

6. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 1, characterized in that, The pressure-resistant and wear-resistant structure (3) includes a shaped inner frame layer (31), and a flexible polymer layer (32) is provided on the outer periphery of the shaped inner frame layer (31).

7. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 6, characterized in that, A glass microsphere layer (33) is provided between the flexible polymer layer (32) and the shaped inner frame layer (31).

8. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 6, characterized in that, The series stabilizing structure (4) includes a series seat (41), the two ends of which are positioned by a slot (42) set on the inner wall of the shaping inner frame layer (31), and the series seats (41) are equidistantly distributed within the substrate structure.

9. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 8, characterized in that, The support layer (21) is provided with a first strip groove (43) through which the serial seat (41) can pass, and the vinyl main layer (11) and the resin fiber layer (12) are respectively provided with a second strip groove (44) through which the serial seat (41) can pass.

10. The SMC substrate structure for the rotor root of a low-altitude aircraft according to claim 9, characterized in that, The series seat (41) is provided with a plurality of positioning chucks (45) respectively corresponding to the first strip-shaped relief groove (43) and the second strip-shaped relief groove (44).

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