Corner-reinforced spider web hyperbolic bionic pillar sandwich panel and hovercar chassis

Abstract

The invention discloses a corner-reinforced spider web hyperbolic bionic pillar sandwich panel and a hovercar chassis. The corner-reinforced spider web hyperbolic bionic pillar sandwich panel comprises an inner core layer and panels fixedly connected to the two sides of the inner core layer. The inner core layer comprises a plurality of pillar units arranged in a two-dimensional periodic array; each supporting column unit comprises a hyperbolic supporting column with the middle contracting and the two ends expanding, and corner reinforcing structures arranged at the two axial ends of the hyperbolic supporting column correspondingly. The corner reinforcing structure comprises a plurality of radial supporting components and at least one annular supporting component, each radial supporting component extends in the radial direction of the end face of the hyperbolic supporting column, one end of each radial supporting component is connected to the center of the end face, and the other end of each radial supporting component is connected to a connecting point of the periphery of the end face. The annular supporting component is arranged around the center of the end face, and the annular supporting component and the radial supporting component are connected to form a spider web structure. Efficient energy absorption and stress dispersion can be achieved under vertical impact and multi-direction loads, and therefore the impact resistance of the hovercar chassis is remarkably improved.

Description

Technical Field

[0001] This invention relates to the field of flying car technology, and more particularly to corner-reinforced spider web hyperbolic bionic strut sandwich panels and flying car chassis. Background Technology

[0002] In related technologies, flying cars need to withstand dynamic impacts, vibrations, and lateral loads during ground driving, and also absorb enormous vertical impact energy during vertical takeoff and landing or emergency landing. However, the energy absorption design of traditional car chassis only considers ground collision scenarios, while the takeoff and landing buffer structure of aircraft fails to take into account the stiffness and layout requirements in vehicle mode. Therefore, the energy absorption performance of existing chassis structural systems is significantly insufficient under multiple operating conditions. Summary of the Invention

[0003] This invention aims to at least solve one of the technical problems existing in the prior art. Therefore, one object of this invention is to propose a corner-reinforced spiderweb hyperbolic bionic strut sandwich panel that can achieve efficient energy absorption and stress dispersion under vertical impact and multi-directional loads, thereby significantly improving the impact resistance of flying car chassis.

[0004] The present invention also proposes a flying car chassis.

[0005] A first aspect of the present invention provides a corner-reinforced spider web hyperbolic bionic pillar sandwich panel, the corner-reinforced spider web hyperbolic bionic pillar sandwich panel including an inner core layer and a panel fixedly connected to both sides of the inner core layer;

[0006] The inner core layer includes multiple pillar units arranged in a two-dimensional periodic array;

[0007] The support unit includes a hyperbolic support that tapers in the middle and expands at both ends, and corner reinforcement structures respectively located at both ends of the hyperbolic support along its axial direction.

[0008] The corner reinforcement structure includes a plurality of radial support members and at least one circumferential support member. Each of the radial support members extends radially along the end face of the hyperbolic column, with one end connected to the center of the end face and the other end connected to a connection point at the periphery of the end face.

[0009] The circumferential support member is arranged around the center of the end face, and the circumferential support member is connected to the radial support member to form a spider web structure.

[0010] In some embodiments, the hyperbolic support includes two symmetrically arranged frustums, which are joined together at their minor diameter ends and the major diameter ends of the two frustums are located at both ends of the axial direction of the hyperbolic support. The minor diameter end face and the major diameter end face of the frustum have the same number of sides and are both constructed as regular N-gons. In the two-dimensional periodic array, two adjacent support units are connected to each other through adjacent corner points on their respective major diameter end faces.

[0011] In some embodiments, the minor diameter end face is coaxially arranged with the major diameter end face, and the minor diameter end face is rotated by an angle M relative to the major diameter end face about the axis of the hyperbolic support, such that each corner point of the minor diameter end face is located on the perpendicular bisector of the corresponding edge of the major diameter end face; each corner point of the minor diameter end face is connected to the two endpoints of the corresponding edge of the major diameter end face by two diagonal struts; where M=π / N.

[0012] In some embodiments, N is an even number and greater than or equal to 4.

[0013] In some embodiments, one end of the radial support member is connected to the center of the end face, and the other end of the radial support member is connected to the corner of the large-diameter end face.

[0014] In some embodiments, the angle between the facet of the frustum and the major diameter end face of the frustum is 0° to 30°.

[0015] In some embodiments, the corner reinforcement structure further includes chordal support members, one end of each chordal support member being vertically connected to the radial support member and the other end being connected to the periphery of the end face, so that the chordal support frame, the radial support member, and the periphery of the end face together form a local triangular reinforcement structure.

[0016] In some embodiments, the number of inner core layers is at least two and they are located between the two panels.

[0017] In some embodiments, an epoxy structural adhesive layer is provided between the panel and the inner core layer.

[0018] A second aspect of the present invention provides a flying car chassis, the flying car chassis including a chassis body, a quick-release structure and a corner-reinforced spider web hyperbolic bionic strut sandwich panel according to the first aspect of the present invention;

[0019] The quick-release structure includes a first snap-fit ​​part provided on the corner-reinforced spider web hyperbolic bionic support sandwich panel and a second snap-fit ​​part provided on the chassis body;

[0020] The first latching part includes two latching hook groups spaced apart along a first direction and a connecting plate connecting the two latching hook groups, each latching hook group including two latching hooks spaced apart along a second direction;

[0021] The first direction is perpendicular to the second direction and is parallel to the connecting plate;

[0022] The hook includes a first hook arm and a second hook arm connected together. The first hook arm extends along a third direction perpendicular to the connecting plate. The second hook arm extends in a direction that is approximately parallel to the second direction and toward another hook in the hook group. The connecting plate is used to connect the corner-reinforced spider web hyperbolic bionic support sandwich panel.

[0023] The second snap-fit ​​portion includes a snap-fit ​​body, an elastic portion, and two stop portions that slide along a second direction on the snap-fit ​​body. The snap-fit ​​body snaps between two snap-fit ​​groups. The elastic portion is used to drive the two stop portions to slide in opposite directions along the second direction so that the two stop portions are supported between two first snap arms. The second snap arms are used to apply a supporting force toward the connecting plate to the stop portions.

[0024] The snap-fit ​​body and the connecting plate are provided with a positioning post on one side and a positioning groove on the other side that is inserted into the positioning groove.

[0025] As can be seen from the technical solution, the embodiments provided by the present invention have the following advantages:

[0026] (1) The hyperbolic strut adopts a geometric configuration of contraction in the middle and expansion at both ends. While significantly reducing the amount of material used, it retains a large cross section at the ends to ensure the connection strength with the panel and corner reinforcement structure, thereby achieving better specific stiffness and specific strength as a whole. It is particularly suitable for weight-sensitive transportation equipment (such as flying cars).

[0027] (2) The spider web-like support network in the corner reinforcement structure is formed by the interweaving of radial and circumferential support members, forming a multi-path force transmission system with rotational symmetry. When the sandwich panel is subjected to in-plane shear, bending or local impact loads, the load can be quickly guided to the central area through the radial members, and the circumferential support members coordinate the deformation in each direction, effectively avoiding stress concentration and improving the overall load uniformity and stability of the structure;

[0028] (3) The ends of hyperbolic columns are high-stress areas under compression or impact loads, which are prone to local buckling. Therefore, in this embodiment, a corner reinforcement structure is provided at the ends to significantly enhance the structural continuity from the periphery of the end face to the center, improve the local bending and shear stiffness, thereby delaying buckling and improving structural stability.

[0029] (4) The spider web structure imitates the biological configurations in nature that efficiently distribute loads (such as spider webs and leaf vein networks), while the hyperbolic profile originates from the natural protective structure of a tortoise shell, adopting a mechanical adaptation strategy of contraction in the middle and expansion at both ends. The two are combined, with the outer end of the radial support member of the spider web structure connected to the periphery of the end face of the hyperbolic column, directly introducing the in-plane load into the high-stiffness end region of the hyperbolic column, while the axial deformation of the hyperbolic column is constrained by the end of the spider web structure, inhibiting buckling extension; thus, a continuous and efficient three-dimensional force transmission path and a multi-layered composite energy absorption structure are formed from in-plane load, corner reinforcement structure, hyperbolic column end to thickness direction energy dissipation, which can achieve efficient energy absorption and stress dispersion under vertical impact and multi-directional load, thereby significantly improving the impact resistance of the flying car chassis. Attached Figure Description

[0030] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a schematic diagram of the corner-reinforced spider web hyperbolic bionic support sandwich panel according to an embodiment of the present invention;

[0032] Figure 2 This is a schematic diagram of the inner core layer according to an embodiment of the present invention;

[0033] Figures 3-4 This is a structural schematic diagram of a support unit according to an embodiment of the present invention;

[0034] Figures 5-6 This is a schematic diagram of multiple support units arranged in a two-dimensional periodic array according to an embodiment of the present invention;

[0035] Figure 7 This is an assembly diagram of the quick-release structure according to an embodiment of the present invention;

[0036] Figures 8-9 This is a schematic diagram of the structure of the first connecting portion according to an embodiment of the present invention;

[0037] Figure 10 This is a schematic diagram of the structure of the second connecting portion according to an embodiment of the present invention;

[0038] Figure 11 This is a cross-sectional schematic diagram of the second connecting portion according to an embodiment of the present invention.

[0039] Figure label:

[0040] Corner-reinforced spider web hyperbolic bionic support sandwich panel 1000

[0041] Inner core layer 100, panel 200, epoxy structural adhesive layer 300, quick-release structure 400;

[0042] Column unit 1, hyperbolic column 11, frustum 111, large diameter end face 1111, small diameter end face 1112, diagonal truss 1113, corner reinforcement structure 12, radial support member 121, circumferential support member 122, chordal support member 123;

[0043] First latching part 2, first latching hook group 21a, second latching hook group 21b, latching hook 211, first latching arm 2111, second latching arm 2112, connecting plate 22, positioning post 23;

[0044] Second snap-fit ​​part 3, snap-fit ​​body 31, elastic part 32, stop part 33, bolt 34, positioning groove 35;

[0045] Corner point P;

[0046] First direction D1, second direction D2, third direction D3. Detailed Implementation

[0047] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0048] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0049] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0050] In recent years, with the rise of the concept of urban air mobility, flying cars, as a new type of transportation integrating aerospace engineering and new energy technologies, have become an important development direction in the global aerospace and transportation fields. These aircraft rely on distributed electric propulsion systems to achieve vertical takeoff and landing and short-distance flight, combining the "flexibility of a car" with the "rapid maneuverability of an aircraft," and are widely regarded as important vehicles for future urban short-distance transportation, emergency rescue, medical transport, and logistics. Currently, the United States, Europe, and China have all included flying cars in their key development plans. NASA has proposed the Advanced Air Mobility (AAM) development framework, and the European Aviation Safety Agency (EASA) and the Federal Aviation Administration (FAA) have respectively issued airworthiness standards for flying cars; many domestic enterprises and research institutions are also conducting prototype verification and airworthiness research. Under this development trend, the safety and structural reliability of flying cars have become one of the key factors restricting their commercialization. According to EASA's Special Condition VTOL safety requirements, flying cars must ensure the integrity of the passenger compartment and survival space in the event of an "emergency landing" or "loss of power descent." This requirement makes crashworthiness design a core aspect of flying car structural design. In the overall configuration of a flying car, the chassis structure is not only the main load-bearing and connecting component, but also a key area for energy absorption and impact buffering. Therefore, designing a biomimetic energy-absorbing structure for the flying car chassis is of great significance for improving the overall crashworthiness and occupant safety.

[0051] Currently, structural research on flying cars mainly focuses on overall aerodynamic layout, propulsion systems, battery arrangement, and lightweight composite materials, while systematic research on the energy absorption and protection performance of the chassis structure is lacking. No publicly available technologies specifically address energy-absorbing structures or design methods for flying car chassis. During operation, flying cars must withstand dynamic impacts, vibrations, and lateral loads from ground travel, and absorb enormous vertical impact energy during takeoff and landing or emergency landing. Traditional automotive chassis energy-absorbing designs only consider ground collision scenarios, while aircraft landing and takeoff buffer structures fail to consider the stiffness and layout requirements in vehicle mode. Therefore, existing structural systems have significant shortcomings in multi-condition energy absorption performance, structural integration, and lightweighting. In other words, there is currently no structural system capable of accommodating both ground and air operation modes and achieving energy absorption and impact buffering functions at the chassis level. Energy-absorbing structures for flying car chassis remain a technological gap. Therefore, there is an urgent need to propose a dedicated energy-absorbing structure design method for flying car chassis, so as to achieve efficient energy absorption and structural safety under multi-directional impacts while ensuring lightweight and load-bearing performance, and provide reliable protection for flying cars under extreme conditions such as forced landings and collisions.

[0052] To address the shortcomings of existing flying car chassis structures, such as the lack of efficient energy-absorbing design, difficulty in balancing lightweight design with multi-condition protection, and inconvenient maintenance and replacement, this invention aims to propose a sandwich panel structure that combines energy absorption and cushioning, lightweight construction, and modular quick-release features. This structure achieves efficient energy absorption and stress dispersion under vertical impacts and multi-directional loads, and its quick-release structure enables rapid assembly, disassembly, and modular replacement, thereby significantly improving the impact resistance and maintenance convenience of the flying car chassis.

[0053] The following is for reference. Figures 1-11 The invention describes a corner-reinforced spider web hyperbolic bionic strut sandwich panel 1000 and a flying car chassis according to embodiments of the present invention.

[0054] Example 1

[0055] like Figure 1 As shown, a first aspect embodiment of the present invention provides a corner-reinforced spider web hyperbolic bionic pillar sandwich panel 1000, which includes an inner core layer 100 and a panel 200. There are two panels 200, one panel 200 fixedly connected to one side of the inner core layer 100, and the other panel 200 fixedly connected to the other side of the inner core layer 100.

[0056] like Figure 2 As shown, the inner core layer 100 includes a plurality of pillar units 1 arranged in a two-dimensional periodic array;

[0057] like Figure 3As shown, the support unit 1 includes a hyperbolic support 11 and corner reinforcement structures 12. The hyperbolic support 11 is constructed as a columnar structure that tapers in the middle and expands at both ends. There are two corner reinforcement structures 12, with one corner reinforcement structure 12 located at one axial end of the hyperbolic support 11 and the other corner reinforcement structure 12 located at the other axial end of the hyperbolic support 11.

[0058] The corner reinforcement structure 12 includes radial support members 121 and circumferential support members 122. There are multiple radial support members 121 and at least one circumferential support member 122. Each radial support member 121 extends radially along the end face of the hyperbolic strut 11, with one end connected to the center of the end face and the other end connected to a connection point at the periphery of the end face.

[0059] The hyperbolic support 11 has end faces at both ends of its axial direction, and the geometric center of the end face is the center of the end face. When the hyperbolic support 11 is a cylindrical structure, the end face is circular and the center is the center of the circle; when it is a prism structure, the end face is a regular polygon and the center is its geometric center.

[0060] It should be noted that the connection of one end of the radial support member 121 to the center of the end face includes the following two implementation methods: (1) the inner ends of multiple radial support members 121 (i.e., the end closest to the axis of the support unit) converge and connect to the geometric center of the end face; (2) a circumferential support member 122 is coaxially arranged at the geometric center of the end face, and the inner ends of multiple radial support members 121 are connected to the periphery of the circumferential support member 122, thereby using the circumferential support member 122 as the central connection node. In both of the above cases, the radial support member 121 extends along the radial direction of the end face, its outer end is connected to the periphery of the end face, and its inner end is connected to the central area of ​​the end face directly or indirectly, thereby realizing the radial support function of the structure.

[0061] A circumferential support member 122 is arranged around the center of the end face, and the circumferential support member 122 is connected to the radial support member 121 to form a spider web structure. The spider web structure here refers to a spider web-like topology structure formed by multiple radial support members 121 distributed radially and intersecting with at least one ring of circumferential support members 122.

[0062] In a specific application scenario, the inner core layer 100 is located in the chassis of a flying car as part of the load-bearing structure. In this application, the corner reinforcement structure 12 is approximately parallel to the plane of the flying car chassis, and the axis of the hyperbolic strut 11 is approximately parallel to the thickness direction of the chassis. Thus, each strut unit 1 uses the corner reinforcement structure 12 as its end skeleton, with multiple radial support members 121 radially distributed and intersecting with the circumferential support members 122, forming a spider web-like planar network with multi-path force transmission capability. This network can quickly transfer and evenly distribute loads in any direction within the chassis plane to the hyperbolic strut 11. The corner reinforcement structure 12 is connected to the periphery of the end face of the hyperbolic strut 11 through the outer ends of each radial support member 121, thereby forming a local three-dimensional stabilizing unit with the hyperbolic strut 11, achieving efficient interlayer load transfer between the panel 200, the corner reinforcement structure 12, and the hyperbolic strut 11. When the chassis is subjected to external impact or compressive load in the thickness direction, the hyperbolic strut 11, with its geometric anti-bending shape of contraction in the middle and expansion at both ends, undergoes controllable progressive buckling deformation, achieving stable energy absorption. At the same time, the corner reinforcement structure 12, through its spider web configuration, helps to disperse end stress and suppress buckling from extending to the middle, significantly improving the overall structure's impact resistance, buffering capacity, and damage tolerance.

[0063] As can be seen from the technical solution, the embodiments provided by the present invention have the following advantages:

[0064] (1) The hyperbolic strut 11 adopts a geometric configuration of contraction in the middle and expansion at both ends. While significantly reducing the amount of material used, it retains a large cross section at the end to ensure the connection strength with the panel 200 and the corner reinforcement structure 12, thereby achieving better specific stiffness and specific strength as a whole. It is particularly suitable for weight-sensitive transportation equipment (such as flying cars).

[0065] (2) The spider web-like support network in the corner reinforcement structure 12 is formed by the interweaving of radial and circumferential support members 122, forming a multi-path force transmission system with rotational symmetry. When the sandwich panel is subjected to in-plane shear, bending or local impact loads, the load can be quickly guided to the central area through the radial members, and the circumferential support members 122 coordinate the deformation in each direction, effectively avoiding stress concentration and improving the overall load uniformity and stability of the structure;

[0066] (3) The ends of the hyperbolic column 11 are high-stress areas under compression or impact loads, which are prone to local buckling. Therefore, in this embodiment, a corner reinforcement structure 12 is provided at the ends to significantly enhance the structural continuity from the periphery of the end face to the center, improve the local bending and shear stiffness, thereby delaying buckling and improving structural stability.

[0067] (4) The spider web structure imitates the biological configurations in nature that efficiently distribute loads (such as spider webs and leaf vein networks), while the hyperbolic profile originates from the natural protective structure of a tortoise shell, adopting a mechanical adaptation strategy of contraction in the middle and expansion at both ends. The two are combined, with the outer end of the radial support member 121 of the spider web structure connected to the periphery of the end face of the hyperbolic support 11, directly introducing the in-plane load into the high-stiffness end region of the hyperbolic support 11, while the axial deformation of the hyperbolic support 11 is constrained by the end of the spider web structure, inhibiting buckling expansion; thus, a continuous and efficient three-dimensional force transmission path and a multi-layered composite energy absorption structure are formed from the in-plane load, the corner reinforcement structure 12, the end of the hyperbolic support 11 to the thickness direction energy dissipation, which can achieve efficient energy absorption and stress dispersion under vertical impact and multi-directional load, thereby significantly improving the impact resistance of the flying car chassis.

[0068] Example 2

[0069] like Figure 3 and Figure 4 As shown, the hyperbolic support 11 is further composed of two symmetrically arranged frustums 111 coaxially joined together. The two frustums 111 are connected to each other at their minor diameter end faces 1112 (e.g., by welding, integral molding, or fixing by connectors), thereby forming an overall hyperbolic profile that tapers in the middle and expands at both ends. Each frustum 111 has a major diameter end face 1111 and a minor diameter end face 1112, both of which have the same number of sides and are constructed as regular N-gons (N ≥ 3). That is, the major diameter end face 1111 and the minor diameter end face 1112 are both geometrically similar regular polygons, differing only in size.

[0070] like Figure 5 As shown, in a two-dimensional periodic array, two adjacent support units 1 are connected to each other through adjacent corner points P on their respective large-diameter end faces 1111. Thus, this invention constructs a continuous in-plane force flow channel within the inner core layer 100 through the interconnection of adjacent support units 1 at corner points P on their large-diameter end faces 1111. When the sandwich panel is subjected to in-plane shear, torsion, or local lateral loads, the load can be directly transferred between adjacent support units 1 through the corner point P connection structure, improving the overall shear stiffness and the structural collaborative load-bearing capacity.

[0071] It is important to further emphasize that the end face of a regular N-gon (especially when N is even) possesses rotational symmetry and an alternating edge-corner geometry, which means that in a two-dimensional periodic arrangement, each corner point P naturally corresponds to a corner point P of a neighboring unit. Utilizing this characteristic for corner point P interconnection eliminates the need for additional complex connectors, enabling a compact arrangement with high fill rate and low void ratio, while ensuring the determinism and manufacturability of the connection positions, making it more suitable for mass production.

[0072] like Figure 6As shown, the spiderweb layer in the corner reinforcement structure 12 and the hyperbolic strut 11 form multiple spatial triangular units at the connection points on the periphery of the end face, constituting a three-dimensional truss-like stable network. This network provides effective out-of-plane constraints in the panel 200-core interface region, significantly improving the overall shear stiffness and buckling stability of the sandwich panel. In the event of local load exceeding limits or buckling failure of individual strut units 1, since adjacent units are interconnected through corner points P of the large-diameter end face 1111, and each corner reinforcement structure 12 contains continuous circumferential support members 122 and radial support members 121, the spiderweb structure in the unfailed area can serve as a redundant force transmission path, redistributing the load along the in-plane direction to the surrounding healthy strut units 1, thereby avoiding the rapid propagation of local damage.

[0073] As can be seen from the above embodiments, the hyperbolic frustum 111 configuration achieves lightweighting and axial energy absorption. The end corner reinforcement structure 12 enhances the end face stiffness of a single support unit 1, and the corner points P of adjacent units are interconnected to form an in-plane overall network. These three elements are coupled step by step to form a three-level reinforcement system, from internal reinforcement of units to end reinforcement of units to synergistic reinforcement between units. This allows the sandwich panel to possess high stiffness, high stability, and high energy absorption capacity while maintaining lightweight properties. In addition, the closed or semi-closed cavity formed by the sidewalls of the hyperbolic support 11, the corner reinforcement structure 12, and adjacent units can undergo controllable collapse deformation under external impact, achieving plastic energy dissipation of the material. At the same time, the air in the cavity generates a damping effect during rapid compression, forming an aerodynamic buffer mechanism. The synergistic effect of these two elements further improves the structure's vibration reduction, energy absorption, and impact resistance performance.

[0074] like Figure 3 As shown, the smaller diameter end face 1112 is coaxially arranged with the larger diameter end face 1111, and the smaller diameter end face 1112 is rotated by an angle M relative to the larger diameter end face 1111 about the axis of the hyperbolic support 11, such that each corner point P of the smaller diameter end face 1112 is located on the perpendicular bisector of the corresponding edge of the larger diameter end face 1111; each corner point P of the smaller diameter end face 1112 is connected to the two endpoints of the corresponding edge of the larger diameter end face 1111 through two oblique trusses 1113; where M=π / N.

[0075] Here, the angle M in degrees of rotation of the minor diameter end face 1112 relative to the major diameter end face 1111 about the axis of the hyperbolic support 11 is in radians.

[0076] This means that in the two frustums 111 constituting the hyperbolic support 11, the smaller diameter end face 1112 is coaxially arranged with the larger diameter end face 1111, and the smaller diameter end face 1112 is rotated about the axis of the hyperbolic support 11 by a predetermined angle M relative to the larger diameter end face 1111, where M = π / N. This rotation angle ensures that each corner point P of the smaller diameter end face 1112 is projected exactly on the perpendicular bisector of the corresponding edge of the larger diameter end face 1111. In this geometry, each corner point P of the smaller diameter end face 1112 is connected to the two endpoints (i.e., two adjacent corner points P) of the corresponding edge on the larger diameter end face 1111 through two diagonal struts 1113. Thus, each pair of adjacent corner points P of the large-diameter end face 1111 and the corresponding corner point P of the small-diameter end face 1112 together form a triangular unit. Multiple such triangular units are distributed circumferentially, forming a spatial truss-type sidewall structure composed of the diagonal truss 1113, the edges of the large-diameter end face 1111, and the contour of the small-diameter end face 1112. This structure achieves a continuous, efficient, and low-material-density geometric transition from the large-diameter end face 1111 to the small-diameter end face 1112, avoiding solid infill or thick-walled designs. Each triangular unit composed of the large-diameter corner point α, the small-diameter corner point, and the large-diameter corner point β has higher geometric stability. This triangularized sidewall structure effectively suppresses buckling instability of the diagonal truss 1113 under compressive loads, further reducing weight without sacrificing load-bearing capacity.

[0077] like Figure 3 As shown, further, N is an even number and greater than or equal to 4. This means that the major diameter end face 1111 and the minor diameter end face 1112 of the hyperbolic support 11 are both regular polygons with an even number of sides, such as squares, hexagons, and octagons. The end faces are geometrically symmetrical with both central and axial symmetry: any straight line passing through the geometric center, if it passes through a corner point P, must also pass through its opposite corner point P; if it passes through the midpoint of an edge, it must also pass through the midpoint of its opposite edge. Based on this, when the minor diameter end face 1112 is rotated relative to the major diameter end face 1111 by an angle M = π / N, it can be ensured that the corner point P of each minor diameter end face 1112 is precisely aligned with the perpendicular bisector of the corresponding edge of the major diameter end face 1111, thus providing a geometric basis for the symmetrical arrangement of the diagonal trusses 1113. Furthermore, an even number of sides ensures that the corner points P of the large-diameter end faces 1111d of adjacent support units 1 can be connected in a two-dimensional periodic array arrangement (such as a square or hexagonal close-packed array), which facilitates the realization of a stable and regular corner point P interconnection structure.

[0078] like Figure 3 and Figure 5As shown, further, one end of the radial support member 121 is connected to the center of the end face, and the other end of the radial support member 121 is connected to the corner point P of the large-diameter end face 1111. As can be seen from the above embodiment, since the large-diameter end face 1111 of the hyperbolic support column 11 is constructed as a regular N-gon (where N is an even number not less than 4), it has N geometrically defined corner points P on its periphery. Each radial support member 121 extends from the center of the end face along one axis of symmetry of the regular polygon, precisely terminating and fixing at a corresponding corner point P. Thus, the N radial support members 121 are evenly radially distributed, forming a star-shaped skeleton with the center as the intersection point and the corner point P as the outer end node. This star-shaped skeleton intersects with at least one circumferential support member 122 arranged around the center, together forming a spiderweb-like corner reinforcement structure 12, and the outer end nodes of all radial support members 121 are anchored to the corner point P of the large-diameter end face 1111. Corner point P, as a geometric abrupt change region on the end face of a regular polygon, has high local stiffness and resistance to deformation. Anchoring the radial support member 121 here can effectively avoid connection failure caused by local buckling or shear slip on the straight edge, and significantly improve the interface bearing capacity and fatigue durability between the corner reinforcement structure 12 and the hyperbolic column 11.

[0079] It should also be noted that, as previously stated, in the two-dimensional periodic array, adjacent support elements 1 are interconnected through adjacent corner points P of their respective large-diameter end faces 1111. Since the radial support member 121 is also anchored to corner point P, corner point P simultaneously serves three functions: as the structural vertex of the hyperbolic support 11; as the outer end anchoring point of the corner reinforcement structure 12; and as the node for interconnection between elements. This greatly simplifies the structural topology, avoids additional connectors, and ensures that loads can be efficiently transferred between the panel 200, corner point P, radial support member 121, circumferential support member 122, and adjacent elements.

[0080] like Figure 3As shown, further, the angle between the facet of the frustum 111 and the major diameter end face 1111 of the frustum 111 is 0°~30°. The hyperbolic column 11 is formed by two symmetrically arranged frustums 111 joined together at their minor diameter end faces 1112, and the sidewall of each frustum 111 is composed of several facets. The angle between the facet of the frustum 111 and the major diameter end face 1111 of the frustum 111 is defined as γ, and the value of γ is in the range of 0°<γ≤30°. When the angle between the axial direction (Z direction) of the hyperbolic column 11 and the XY plane increases (i.e., γ decreases), the pressure angle between the loading direction and the main deformation direction of the column decreases, so that the component of the external load in the axial direction of the column is maximized and the transverse shear component is minimized. When γ≤30° (i.e., axial tilt angle≥150°), the pressure angle is small enough, and the load is mainly transmitted along the axis of the column, avoiding early buckling or peeling of the panel 200 due to excessive transverse force, thereby making the stress distribution of the entire structure more uniform and improving the load-bearing efficiency. If a steeper inclination angle is adopted (such as γ being 0°, corresponding to an axial angle close to 180°), although the pressure angle can be further reduced, it will lead to a reduction in the number of sidewalls or connection points shared by adjacent support units 1 in the periodic array, resulting in a decrease in the number of effective supports per unit area and a decrease in overall stiffness.

[0081] By limiting γ≤30°, this invention ensures that each support unit 1 has an independent and complete hexagonal large-diameter end face 1111 (side length L) while maintaining a small pressure angle. Adjacent units can be reliably connected through corner points P, maintaining high unit density and high support redundancy, while taking into account both lightweight and load-bearing capacity.

[0082] Specifically, the large-diameter end face 1111 lies in the XY plane, and the frustum 111 extends along the Z-axis, with its facets converging obliquely from each edge of the large-diameter end face 1111 to the small-diameter end face 1112. The included angle γ is the minimum dihedral angle between any facet and the plane containing the large-diameter end face 1111. When γ = 0°, the facets and end faces are coplanar, and the structure degenerates into a flat plate; as γ increases, the inclination of the facets increases, and the sidewalls of the support column become steeper. This invention controls γ within the range of 0° to 30°, so that the hyperbolic support column 11 presents a gradually shrinking quasi-hyperbolic profile, which retains sufficient axial height to achieve effective support while avoiding excessive steepness that could lead to local stress concentration or manufacturing difficulties.

[0083] This angle design originates from the biomimetic abstraction of the alternating arch-concave composite surface inside the tortoise shell: the tortoise shell achieves multi-directional load distribution through continuous curvature changes; this invention simplifies it into a combination of frustums 111 with controllable tilt angles, which, while ensuring manufacturability, reproduces its multi-path force transmission mechanism guided by curvature gradient.

[0084] In summary, by limiting the angle between the facet of the frustum 111 and the large-diameter end face 1111 to 0°~30°, this invention, guided by the biomimetic principles of tortoise shell surface mechanics, controls the pressure angle, buckling mode, and unit arrangement density of the hyperbolic support 11, achieving an optimal balance between lightweight, high energy absorption, high stability, and manufacturability. This angle range is not arbitrarily chosen, but rather a structural parameter that enables multi-path force transmission, staged energy absorption, and high unit integration.

[0085] For example, the large-diameter end face 1111 and the small-diameter end face 1112 are regular hexagons. The side length of the large-diameter end face 1111 is L, the total height of the hyperbolic support 11 is 2L, the diameter of the small-diameter end is about 0.15L, and γ is 30° to make the length and height of the side wall of the frustum 111 coordinated, avoiding the collapse caused by being too thin or the waste of material caused by being too thick.

[0086] like Figure 3 As shown, the corner reinforcement structure 12 further includes chordal support members 123. One end of each chordal support member 123 is vertically connected to the radial support member 121, and the other end is connected to the periphery of the end face. Thus, the chordal support frame, the radial support member 121 and the periphery of the end face together form a local triangular reinforcement structure.

[0087] Specifically, on the large-diameter end face 1111 of the hyperbolic support 11, multiple radial support members 121 extend radially from the center of the end face to various corner points P or midpoints of edges of the large-diameter end face 1111. Between these radial support members 121, chordal support members 123 are added, one end of which is vertically connected to a radial support member 121 (usually near the outer side of the large-diameter end face 1111), and the other end is fixed to an appropriate position on the periphery of the end face. This arrangement allows each group of chordal support members 123, the adjacent radial support members 121, and the periphery of the end face to form a closed triangular region, thereby significantly enhancing the stiffness and stability of this region.

[0088] This design is inspired by the unique topology of spider webs in nature. Spider webs are formed by the interweaving of radial and circumferential threads, creating a highly efficient load-bearing and energy-absorbing network structure. This invention borrows this principle, introducing radial support members 121 and chordal support members 123 into the traditional hexagonal honeycomb unit, strengthening the geometric stability and load transfer path of the corner regions. The corner regions are the weakest points of the hyperbolic support column 11, most susceptible to local buckling under compressive or impact loads. By setting the chordal support members 123, a closed triangular reinforcement zone is formed between the radial support members 121 and the periphery of the end face, effectively improving the bending stiffness of the corners and avoiding early failure due to local stress concentration. The material increase of the chordal support members 123 is relatively limited, yet it significantly improves the overall stiffness and energy absorption efficiency, achieving performance improvement while maintaining lightweight characteristics.

[0089] It is important to emphasize that, as a result, the corner reinforcement structure 12 exhibits typical staged energy absorption and progressive buckling characteristics. When the hyperbolic strut 11 is subjected to axial compression or impact loads, the circumferential support member 122 first undergoes elastic deformation; as the load increases, the radial support line and the corner connection area successively enter the plastic stage, forming a multi-stage buckling energy absorption process. Unlike the concentrated collapse or instantaneous failure mode in traditional structures, this progressive deformation mode makes the energy absorption process more stable, helps to extend the energy absorption time of the structure and increase the total energy absorbed. At the same time, the corner reinforcement unit still has a certain residual load-bearing capacity after deformation, enabling the structure to maintain local stability after damage, achieving high damage tolerance and stress self-recovery capability.

[0090] Example: A specific implementation of the inner core layer 100 (taking a regular hexagonal end face as an example).

[0091] like Figures 1-6 As shown, in a preferred embodiment, the inner core layer 100 is composed of a plurality of support units 1 arranged regularly in a plane in a hexagonal close-packed manner (i.e., a honeycomb-shaped periodic array). Each support unit 1 includes a hyperbolic support 11 and corner reinforcement structures 12 located at both ends of its axial direction.

[0092] The hyperbolic support 11 is formed by joining two symmetrical regular hexagonal frustums 111 at their minor diameter end faces 1112. The major diameter end face 1111 of each regular hexagonal frustum 111 is a regular hexagon with a side length denoted as L. The minor diameter end face 1112 is also a regular hexagon with a side length less than L. The minor diameter end face 1112 is rotated 30° (i.e., M=π / 6) relative to the major diameter end face 1111 about the support axis, such that each corner point P of the minor diameter end face 1112 is directly opposite the midpoint of the corresponding edge of the major diameter end face 1111. Each corner point P of the minor diameter end face 1112 is connected to the two endpoints of the edge by two diagonal trusses 1113, thereby forming a triangular spatial truss structure composed of 12 diagonal trusses 1113 on the side wall.

[0093] The total height of the hyperbolic support 11 (i.e. the sum of the heights of the two frustums 111) is 2L, and the whole structure has a hyperbolic profile that contracts in the middle and expands at both ends.

[0094] At both axial ends of each hyperboloidal strut 11, corner reinforcement structures 12 are provided. The corner reinforcement structures 12 are located in the plane containing the large-diameter end face 1111 and include:

[0095] Six radial support members 121: extending along the six axes of symmetry of a regular hexagon, with one end converging at the geometric center of the end face (or connected to the central circumferential support member 122), and the other end connected to the six corner points P of the large-diameter end face 1111 respectively;

[0096] Four coaxially arranged circumferential support members 122 are all located in the plane of the large-diameter end face 1111 of the hyperbolic support column 11, and share the geometric center of this end face as the axis. The diameters of the four circumferential support members 122 are 0.35L, 0.7L, 1.05L, and 1.6L, respectively, where L is the side length of the regular hexagon of the large-diameter end face 1111. A ring with a diameter of 0.35L serves as the inner end connection center of the radial support members 121: the inner ends of each radial support member 121 do not directly converge at the geometric center point, but are connected to the periphery of this smallest ring, thus using this ring as the central node to achieve uniform force transition and stress dispersion. The remaining three larger-diameter circumferential support members 122 are arranged radially outwards and intersect with each radial support member 121 at different radii.

[0097] Twelve chordal support members 123: arranged in pairs, with each pair of chordal support members 123 symmetrical with respect to the radial support members 121. One end of each chordal support member 123 is perpendicularly connected to the outer region of a radial support member 121, and the other end is connected to the periphery between two adjacent edges (e.g., the midpoint of the edge or a nearby corner point P), thus forming twelve local triangular reinforcement regions together with the radial support member 121 and the periphery of the end face. The length of each chordal support member 123 is 0.25L.

[0098] The diameter of the truss that constitutes support unit 1 is 0.07L.

[0099] In the two-dimensional array, adjacent support units 1 are interconnected through adjacent corner points P on their respective large-diameter end faces 1111. Taking a hexagonal close-packed layout with regular hexagonal end faces as an example: each large-diameter end face 1111 has six corner points P, and in the array, each corner point P is shared by three adjacent support units 1. By setting a connection structure (such as welding, integral molding, or connecting pin) at this common corner point P, the three units are rigidly interconnected at this point, thereby constructing a continuous and interconnected in-plane force transmission network inside the inner core layer 100.

[0100] Example 3

[0101] like Figure 1 and Figure 2 As shown, the number of inner core layers 100 is at least two and they are located between the two panels 200. That is, at least two inner core layers 100 are stacked between the two panels 200.

[0102] Furthermore, an epoxy structural adhesive layer 300 is provided between the panel 200 and the inner core layer 100. This is used to achieve reliable connection and load transfer between the layers.

[0103] For example, a sandwich panel consists of three parts:

[0104] The top and bottom layers are carbon fiber reinforced composite material panels 200 (CFRP).

[0105] The middle part is a metal inner core layer 100, which is composed of corner-reinforced spider web hyperbolic bionic support units 1 arranged in a two-dimensional periodic array. The preferred material is AlSi10Mg aluminum alloy, which is suitable for additive manufacturing processes such as laser powder bed melting (LPBF).

[0106] The layers are bonded together with high-strength epoxy structural adhesive to form a stable multi-layered composite system.

[0107] The inner core layer 100 adopts a spatially periodic array design: individual pillar units 1 are repeatedly arranged along the X and Y directions to form a three-dimensional lattice structure with uniform geometric features. To further improve impact resistance and structural stability, this invention employs a multi-layered inner core stacked arrangement. Figure 5 (This illustrates a double-layer stacking scenario). The number of stacking layers can be adjusted according to the actual operating conditions required by the flying car, such as its curb weight, landing speed, and forced landing energy. For example, it can be set to 2, 3, or more layers to meet the energy absorption targets of different types of aircraft.

[0108] When sandwich panels are subjected to external impact or compressive loads, the load transfer and energy absorption processes exhibit a multi-level coordinated mechanism:

[0109] The upper panel 200 first bears the initial impact and distributes the load to the first inner core array below it;

[0110] The hyperbolic strut 11 in the first inner core undergoes progressive buckling, and the corner reinforcement structure 12 disperses stress through a spider web network, achieving the first stage of energy dissipation;

[0111] The remaining load that is not fully absorbed continues to be transferred to the next core layer, triggering the second stage of buckling and energy absorption;

[0112] The lower core layer also provides supporting reaction force to the upper layer, suppressing excessive collapse and maintaining the residual load-bearing capacity of the structure.

[0113] The CFRP panels 200 on the upper and lower surfaces not only provide high specific strength and high specific stiffness, but also exert effective out-of-plane constraints on the inner core layer 100, preventing lateral instability of the support unit 1 under compression. In addition, the epoxy structural adhesive used not only has high-strength bonding performance, but also exhibits certain viscoelastic damping characteristics under dynamic loads, which can further dissipate interfacial shear energy, improve interlayer debonding resistance and damage tolerance of the overall structure.

[0114] In summary, this invention constructs an advanced sandwich panel system that combines lightweight, high energy absorption, high stability, and customizability through the integrated design of periodic array of support units 1, multi-layer core stacking, high-performance panel 200, and functional adhesive layer. It is particularly suitable for critical load-bearing structures that are sensitive to safety and weight, such as electric vertical take-off and landing flying car (eVTOL) chassis.

[0115] Example 4

[0116] like Figures 7-11 As shown, a second aspect of the present invention provides a flying car chassis, which includes a chassis body, a quick-release structure 400, and a corner-reinforced spider web hyperbolic bionic strut sandwich panel 1000 according to the first aspect of the present invention.

[0117] The quick-release structure 400 includes a first snap-fit ​​part 2 provided on the corner reinforced spider web hyperbolic bionic support sandwich panel 1000 and a second snap-fit ​​part 3 provided on the chassis body;

[0118] The first latching part 2 includes two latching hook groups spaced apart along a first direction D1 and a connecting plate 22 connecting the two latching hook groups. Each latching hook group includes two latching hooks 211 spaced apart along a second direction D2.

[0119] The two hook groups are a first hook group 21a and a second hook group 21b. The first hook group 21a includes two hooks 211 spaced apart along the second direction D2; the second hook group 21b includes two hooks 211 spaced apart along the second direction D2.

[0120] The first direction D1 is perpendicular to the second direction D2 and is parallel to the connecting plate 22;

[0121] The hook 211 includes a first hook arm 2111 and a second hook arm 2112 connected together. The first hook arm 2111 extends along a third direction D3 perpendicular to the connecting plate 22. The second hook arm 2112 extends in a direction approximately parallel to the second direction D2 and toward the other hook 211 of the hook group. The connecting plate 22 is used to connect the corner-reinforced spider web hyperbolic bionic support sandwich panel 1000.

[0122] The second snap-fit ​​part 3 includes a snap-fit ​​body 31, an elastic part 32, and two stop parts 33 that are slidably disposed on the snap-fit ​​body 31 along the second direction D2. The connecting plate 22 is also provided with a positioning post 23, and the snap-fit ​​body 31 is also provided with a positioning groove 35 that is inserted and engaged with the positioning groove 35.

[0123] Therefore, through the cooperation of the hook assembly and the locking body 31, operators can complete the assembly or disassembly of the sandwich panel and the chassis body without using tools. The specific steps are as follows:

[0124] Align the first snap-fit ​​part 2 on the sandwich panel with the second snap-fit ​​part 3 on the chassis body;

[0125] The snap-fit ​​body 31 is inserted between the two snap-fit ​​groups, and the elastic part 32 drives the stop part 33 to open and automatically lock;

[0126] The positioning pin 23 and the positioning groove 35 are inserted into each other to ensure accurate positioning.

[0127] This design significantly reduces maintenance time, especially for flying cars that frequently require inspection or replacement of parts, greatly improving maintenance efficiency.

[0128] For example, the flying car chassis includes a four-layer corner-reinforced spiderweb hyperbolic bionic strut sandwich panel 1000 with dimensions of 400mm × 400mm.

[0129] The sandwich panel includes:

[0130] The upper and lower layers are carbon fiber reinforced composite material panels 200 (CFRP), each with a thickness of 2 mm;

[0131] Two metal core layers 100 are set in the middle. Each layer is made of AlSi10Mg aluminum alloy by laser powder bed melting (LPBF) additive manufacturing process. The core layer 100 is composed of the aforementioned corner-reinforced spider web hyperbolic bionic support unit 1 arranged in a hexagonal close-packed pattern in a periodic array. The large diameter end face 1111 of a single support unit 1 is a regular hexagon (side length L=10mm), and the total height is 2L=20mm.

[0132] The layers are bonded together with high-strength epoxy structural adhesive to form a stable multi-layered composite system.

[0133] To enable rapid installation, reliable connection, and convenient replacement of the sandwich panel on the flying car chassis, quick-release structures 400 are integrated around the edges of the CFRP panels 200.

[0134] The first snap-fit ​​part 2 is integrally formed with the CFRP panel 200, and is manufactured as a whole using the same CFRP material through molding or CNC machining. This design avoids the risk of interface failure caused by the connection of dissimilar materials, and ensures structural continuity and lightweight.

[0135] The second connection is screwed to the flying car chassis by bolts 34, specifically by M8×25 mm bolts 34 for reliable connection to the steel structure of the flying car chassis.

[0136] The second snap-fit ​​part 3 includes a snap-fit ​​body 31, an elastic part 32, and two stop parts 33 that are slidably disposed on the snap-fit ​​body 31 along the second direction D2.

[0137] The snap-fit ​​body 31 is provided with two sliding grooves extending along the second direction D2. The stop part 33 includes a stop body and a button. The stop body is connected to the button and is movably disposed in the sliding groove. An elastic part 32 is provided between the groove wall and the stop body. The elastic part 32 is constructed as a spring.

[0138] The slide groove passes through and engages one end of the main body 31 in the second direction D2, forming a clearance opening. The button passes through the clearance opening and is also provided with a limiting baffle. The size of the limiting baffle is larger than the size of the clearance opening to restrict the button from entering the slide groove completely.

[0139] The connecting plate 22 is also provided with a positioning post 23, and the snap-fit ​​body 31 is also provided with a positioning groove 35 that is inserted and matched with the positioning groove 35.

[0140] When the button is pressed, the button drives the stop body to move and disengage from the hook 211, thus disassembling the sandwich panel; after the button is released, the spring returns to its original position, and the stop body engages with the hook 211 to quickly fix the sandwich panel.

[0141] This quick-release structure 400 enables tool-less disassembly and rapid replacement of sandwich panels after damage, significantly improving maintenance efficiency and modular replacement capabilities. Furthermore, the number and placement of the clips can be flexibly designed according to the size, number of layers, and load distribution of the sandwich panels to ensure structural strength and load transfer stability at the joints. This design not only enhances the ease of maintenance and scalability of the flying car chassis but also ensures reliable structural connection performance even after multiple disassemblies and reassemblies.

[0142] Other components and operations of the flying car chassis in this embodiment are known to those skilled in the art and will not be described in detail here. In the description of this invention, "first feature" and "second feature" may include one or more of these features. The vertical, horizontal, and front-back directions are defined as shown in the figures.

[0143] In the description of this invention, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features not in direct contact but through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature.

[0144] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0145] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A corner-reinforced spider web hyperbolic bionic support sandwich panel, characterized in that, It includes an inner core layer and panels fixedly connected to both sides of the inner core layer; The inner core layer includes multiple pillar units arranged in a two-dimensional periodic array; The support unit includes a hyperbolic support that tapers in the middle and expands at both ends, and corner reinforcement structures respectively located at both ends of the hyperbolic support along its axial direction. The corner reinforcement structure includes a plurality of radial support members and at least one circumferential support member. Each of the radial support members extends radially along the end face of the hyperbolic column, with one end connected to the center of the end face and the other end connected to a connection point at the periphery of the end face. The circumferential support member is arranged around the center of the end face, and the circumferential support member is connected to the radial support member to form a spider web structure.

2. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 1, characterized in that, The hyperbolic support includes two symmetrically arranged frustums, which are joined together at their minor diameter ends. The major diameter ends of the two frustums are located at both ends of the axial direction of the hyperbolic support. The minor diameter end face and the major diameter end face of the frustum have the same number of sides and are both constructed as regular N-gons. In the two-dimensional periodic array, two adjacent support units are connected to each other through adjacent corner points on their respective large-diameter end faces.

3. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 2, characterized in that, The small-diameter end face is coaxially arranged with the large-diameter end face, and the small-diameter end face is rotated by an angle M relative to the large-diameter end face about the axis of the hyperbolic support, such that each corner point of the small-diameter end face is located on the perpendicular bisector of the corresponding edge of the large-diameter end face. The corner point of each of the smaller diameter end faces is connected to the two endpoints of the corresponding edge of the larger diameter end face by two diagonal trusses; Where M = π / N.

4. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 3, characterized in that, The N is an even number and greater than or equal to 4.

5. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 4, characterized in that, One end of the radial support member is connected to the center of the end face, and the other end of the radial support member is connected to the corner of the large-diameter end face.

6. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 2, characterized in that, The angle between the facet of the frustum and the major diameter end face of the frustum is 0° to 30°.

7. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 1, characterized in that, The corner reinforcement structure also includes chordal support members, one end of each chordal support member being vertically connected to the radial support member, and the other end being connected to the periphery of the end face, so that the chordal support frame, the radial support member, and the periphery of the end face together form a local triangular reinforcement structure.

8. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 1, characterized in that, The number of inner core layers is at least two and they are located between the two panels.

9. The corner-reinforced spider web hyperbolic bionic support sandwich panel according to claim 1, characterized in that, An epoxy structural adhesive layer is provided between the panel and the inner core layer.

10. A flying car chassis, characterized in that, include: Chassis body; Corner-reinforced spider web hyperbolic bionic support sandwich panel according to any one of claims 1-9; The quick-release structure includes a first snap-fit ​​part provided on the corner-enhanced spider web hyperbolic bionic support sandwich panel and a second snap-fit ​​part provided on the chassis body; The first latching part includes two latching hook groups spaced apart along a first direction and a connecting plate connecting the two latching hook groups, each latching hook group including two latching hooks spaced apart along a second direction; The first direction is perpendicular to the second direction and is parallel to the connecting plate; The hook includes a first hook arm and a second hook arm connected together. The first hook arm extends along a third direction perpendicular to the connecting plate. The second hook arm extends in a direction that is approximately parallel to the second direction and toward another hook in the hook group. The connecting plate is used to connect the corner-reinforced spider web hyperbolic bionic support sandwich panel. The second snap-fit ​​portion includes a snap-fit ​​body, an elastic portion, and two stop portions that slide along a second direction on the snap-fit ​​body. The snap-fit ​​body snaps between two snap-fit ​​groups. The elastic portion is used to drive the two stop portions to slide in opposite directions along the second direction so that the two stop portions are supported between two first snap arms. The second snap arms are used to apply a supporting force toward the connecting plate to the stop portions. The snap-fit ​​body and the connecting plate are provided with a positioning post on one side and a positioning groove on the other side that is inserted into the positioning groove.

Images