A composite laminated reflective panel and its preparation method

Abstract

This invention aims to provide a composite laminated reflective panel and its preparation method. The composite laminated reflective panel prepared by plying and layering small pieces can be parabolic, spherical, or any irregularly shaped curved surface. The prepared composite laminated reflective panel exhibits quasi-isotropic properties within any region, or quasi-isotropic properties both inside and outside the surface, or quasi-isotropic properties both inside and outside the surface, while minimizing bending-torsional coupling effects and exhibiting quasi-zero expansion characteristics within any region. When the preparation method proposed in this invention is applied to the preparation of reflective panels for composite solid-surface reflectors, it can ensure high geometric accuracy under curing and on-orbit temperature alternation conditions, demonstrating significant application prospects.

Description

Technical Field

[0001] This invention relates to the field of reflector manufacturing, and more particularly to a composite material laminated reflective panel and its preparation method. Background Technology

[0002] Carbon fiber composites possess characteristics such as lightweight, high specific stiffness, dimensional stability, and corrosion resistance, making them typical high-performance materials. Using them to replace metal materials in antenna reflector structures can not only reduce antenna system accuracy variations caused by environmental temperature changes but also effectively reduce the system mass of the antenna reflector structure, improve antenna system reliability, and extend service life, demonstrating significant application prospects. Currently, the reflector panels of reflector structures made using carbon fiber composites are mostly aluminum honeycomb sandwich structures. This structure consists of a carbon fiber composite skin, an adhesive layer, and a metal aluminum honeycomb layer, all co-cured and integrally formed. However, due to the mismatch in thermal deformation of the materials during the co-curing of the carbon fiber composite skin, adhesive layer, and metal aluminum honeycomb layer, the final reflector using an aluminum honeycomb sandwich structure has relatively poor overall surface accuracy.

[0003] The macroscopic mechanical properties of composite laminates are directly determined by their layup configuration. Without proper layup design, the final cured composite laminate may warp under coupled forces such as tension-shear, bending-torsion, or tension-bending, thus affecting the manufacturing precision of the product. Furthermore, without specific layup optimization, the laminate will exhibit anisotropic characteristics in both in-plane and out-of-plane stiffness. When anisotropic laminate structures are subjected to external loads, such as thermal loads or other mechanical loads, complex non-uniform deformation characteristics and failure mechanisms will emerge.

[0004] Currently, based on traditional composite laminate theory, there are some methods for achieving quasi-isotropy and quasi-zero expansion in planar laminate structures through layup design. Antenna reflectors often have reflective panels that are parabolic, spherical, or arbitrarily irregularly shaped curved surfaces. However, no reports have been found on layup methods for composite laminate reflective panels with arbitrary curved surfaces that achieve near-homogeneity and quasi-zero expansion within arbitrary curved surface regions through layup design. Summary of the Invention

[0005] To overcome the aforementioned technical deficiencies, the present invention aims to provide a composite laminated reflective panel and its preparation method. The composite laminated reflective panel prepared by plying and layering small pieces, as proposed in this invention, can be parabolic, spherical, or any irregularly shaped curved surface. The prepared composite laminated reflective panel exhibits quasi-isotropic properties within any region, or quasi-isotropic properties both inside and outside the surface, or quasi-isotropic properties both inside and outside the surface, while minimizing bending-torsional coupling effects and exhibiting quasi-zero expansion characteristics within any region. When the preparation method proposed in this invention is applied to the preparation of reflective panels for composite solid-surface reflectors, it can ensure high geometric accuracy under curing and on-orbit temperature alternation conditions, demonstrating significant application prospects.

[0006] In one aspect, this invention provides a method for preparing a composite laminated reflective panel, comprising the following steps: determining the layup method of the composite laminated reflective panel, the layup method including layup angle and layup sequence; determining the shape of the small plies; determining the splicing and laying method of each layer of small plies according to the shape of the small plies; determining the splicing and laying combination method of any two layers of small plies, ensuring that the seam lines of the layers with different splicing and laying methods overlap each other or that the seam line of one layer partially covers the seam line of another layer; determining the layup direction of each layer of small plies, wherein the composite laminated reflective panel comprises at least four layers, and the number of layers containing at least two different layup directions of small plies in the same layer is at least four; and according to the determined splicing and laying method and layup direction of each layer of small plies... Small planar materials are prepared using unidirectional continuous fiber-reinforced prepreg. Based on the splicing and laying method and direction of each layer of small planar materials, these planar materials are spliced ​​and laid to form a layer with an arbitrary preset curved surface geometry. Based on the splicing and laying method of any two layers of small planar materials, small planar materials are spliced ​​and laid on the already spliced ​​and laid layers according to the preset splicing and laying method and direction. After completing the laying of a preset number of layers, a laminated structure with an arbitrary preset curved surface geometry is obtained. The obtained laminated structure is then cured to produce a composite material laminated reflective panel with quasi-isotropic properties in any region, or quasi-isotropic properties both in and out of the surface, or quasi-isotropic properties both in and out of the surface, while minimizing bending-torsional coupling effect and exhibiting quasi-zero expansion properties in any region.

[0007] Preferably, in the above preparation method, the half-thickness layup of the composite material laminated reflective panel is [Θ] = [θ]. (1) θ (2) , ...,θ (p) Then, the complete layup of the composite laminate reflective panel is: [Θ] s =[θ(1) θ (2) , ..., θ (p-1) ,θ (p) θ (p+1) θ (p+2) , ...,θ (2p-1) ,θ (2p) ], complete layup [Θ] s Let θ be the symmetric set of half-thickness ply [Θ], where the ply angle of the i-th layer of the composite laminate reflective panel is θ. (i) 1≤i≤2p, and i is an integer. The piling order is to stack the first layer to the second p layer in sequence. The i-th layer and the second p-i+1-th layer are symmetrical layers. The piling angles of the two symmetrical layers are the same, and the piling direction, shape, and splicing method of the small piling pieces in the two layers are the same.

[0008] Preferably, in the above preparation method, within half the thickness of the composite laminated reflective panel, in the splicing and bonding combination of any two layers of small pieces, the layup angles are θ. (i) and θ (k) If |θ (i) |≠|θ (k) If |θ|, then the splicing and laying methods of the two layers of small plywood are different, and the seam lines of the two layers of small plywood overlap each other or the seam line of one layer partially covers the seam line of the other layer; if |θ| (i) |=|θ (k) If the two layers of small plies are laid in the same way, and the seam lines of the small plies in the two layers overlap, then the splicing and laying methods of the small plies in the two layers with plies of 0° and 90° are the same. If the half-thickness ply of the composite laminate reflective panel contains a ply with a ply angle of 0° and a ply with a ply angle of 90°, then the splicing and laying methods of the small plies in the two layers with plies of 0° and 90° are the same. If the half-thickness ply of the composite laminate reflective panel contains a ply with a ply angle of 0° but does not contain a ply with a ply angle of 90°, then the splicing and laying methods of the small plies in the ply with a ply angle of 0° are arbitrary, and the small plies in this layer can cover the seam lines of the small plies in the adjacent plies or the seam lines of the small plies in this layer can be covered by the small plies in the adjacent plies.

[0009] Preferably, in the above preparation method, the small plylets are of arbitrary polygonal or curved shape. Preferably, in the above preparation method, the ply direction of the small plylets within each ply layer is rotated; within the same ply layer, the ply angles corresponding to the ply directions of adjacent small plylets have the same absolute value and opposite signs, and the ply angles corresponding to the ply directions of alternating small plylets are the same; when the half-thickness ply of the composite laminate reflective panel simultaneously includes plylets with a ply angle of 0° and plylets with a ply angle of 90°, then the plylets with a ply angle of 0° and the plylets with a ply angle of 90° are... In a 90° ply, the ply angle of a small ply adjacent to a small ply with a 0° ply angle is 90°, and the ply angle of small ply alternating with a small ply with a 0° ply angle is 0°. When the half-thickness ply of a composite laminated reflective panel includes plyes with a 0° ply angle but does not include plyes with a 90° ply angle, the ply angle corresponding to the ply direction of the small ply with a 0° ply angle is 0°, and no ply direction rotation is performed. Within the half-thickness of the composite laminated reflective panel, any ply angle of +|θ (i) If no ply orientation rotation is performed within a ply of |, then the ply angle is -|θ. (i) Within a single layup, the layup orientation of smaller plies is not rotated. When a half-thickness layup of a composite laminate reflective panel contains both layups with a 0° angle and layups with a 90° angle, if the layup orientation of the smaller plies in the 0° angle layup is not rotated, then the layup orientation of the smaller plies in the 90° angle layup is also not rotated. A maximum of two layups with non-rotating layup orientations can be contained within a half-thickness layup of a composite laminate reflective panel.

[0010] Preferably, in the above preparation method, the half-thickness layup of the composite material laminated reflective panel is selected from the candidate set {Θ}, which is composed of all permutations of all elements obtained after each element of the basic angle set θ is copied q≥1 times.

[0011] Preferably, in the above preparation method, the layup in any region of the composite material laminated reflective panel is... r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. A symmetric set of r = 1, 2, ... and a half-thickness ply. In the case of r = 1, 2, ..., the absolute values ​​of the ply angles of any two adjacent plies are not equal.

[0012] Preferably, in the above preparation method, the layup in any region of the composite material laminated reflective panel is... r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. Symmetric set of r = 1, 2, ..., half-thickness ply r = 1, 2, ..., is obtained by the following steps: using all elements [Θ] in the candidate set {Θ} respectively... r The symmetric set of r = 1, 2, ..., ... [Θ] r ] s The stiffness matrix [K] of the composite laminate panel is obtained by laying up layers r = 1, 2, ...

[0013]

[0014] The obtained stiffness matrix [K] is then optimized using the following objective function.

[0015]

[0016] or

[0017]

[0018] The optimized half-thickness layup r = 1, 2, ... or half-thickness ply r = 1, 2, ... as half-thickness ply r = 1, 2, ...

[0019] Preferably, in the above preparation method, any element θ of the basic angle set θ (k) The condition -π / 2 < θ is satisfied. (k) ≤π / 2, where k=1,2,...,N, N≥2, and N is an integer.

[0020] When N=2, the basic angle set is

[0021] Furthermore, when N = 2n and n ≥ 2n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n) ],and

[0022]

[0023] Furthermore, when N = 2n - 1 and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n-1) ],and:

[0024]

[0025] In another aspect, the present invention provides a composite laminated reflective panel having an arbitrary preset curved surface geometry, comprising: at least one small ply prepared from a unidirectional continuous fiber-reinforced prepreg; at least four layers formed by splicing the small ply in a preset ply direction and splicing method, wherein the number of layers containing at least two different ply directions within the same layer is at least four; any two layers have a preset ply splicing method, ensuring that the seam lines of the small ply in layers with different splicing methods overlap each other or that the seam line of one layer partially covers the seam line of another layer; any ply region has a symmetrical and balanced ply pattern and quasi-zero expansion characteristics; any ply region satisfies the following conditions: quasi-isotropic characteristics in-plane, or quasi-isotropic characteristics both in-plane and out-of-plane, or quasi-isotropic characteristics both in-plane and out-of-plane with minimal bending-torsional coupling effect.

[0026] Preferably, in the above-mentioned composite laminated reflective panel, the half-thickness layup of the composite laminated reflective panel is [Θ] = [θ]. (1) θ (2) , ...,θ (p) Then, the complete layup of the composite laminate reflective panel is: [Θ] s =[θ (1) θ (2) , ..., θ (p-1) ,θ (p) θ (p+1) θ (p+2) , ...,θ (2p-1) ,θ (2p) ], complete layup [Θ] s Let θ be the symmetric set of half-thickness ply [Θ], where the ply angle of the i-th layer of the composite laminate reflective panel is θ. (i) 1≤i≤2p, and i is an integer. The piling order is to stack the first layer to the second p layer in sequence. The i-th layer and the second p-i+1-th layer are symmetrical layers. The piling angles of the two symmetrical layers are the same, and the piling direction, shape, and splicing method of the small piling pieces in the two layers are the same.

[0027] Preferably, in the above-mentioned composite laminated reflective panel, within half the thickness of the composite laminated reflective panel, in the splicing and tiling combination of any two layers of small pieces, the layup angles are respectively θ. (i) and θ (k) If |θ (i) |≠|θ (k) If |θ|, then the splicing and laying methods of the two layers of small plywood are different, and the seam lines of the two layers of small plywood overlap each other or the seam line of one layer partially covers the seam line of the other layer; if |θ|(i) |=|θ (k) If the two layers of small plies are laid in the same way, and the seam lines of the small plies in the two layers overlap, then the splicing and laying methods of the small plies in the two layers with plies of 0° and 90° are the same. If the half-thickness ply of the composite laminate reflective panel contains a ply with a ply angle of 0° and a ply with a ply angle of 90°, then the splicing and laying methods of the small plies in the two layers with plies of 0° and 90° are the same. If the half-thickness ply of the composite laminate reflective panel contains a ply with a ply angle of 0° but does not contain a ply with a ply angle of 90°, then the splicing and laying methods of the small plies in the ply with a ply angle of 0° are arbitrary, and the small plies in this layer can cover the seam lines of the small plies in the adjacent plies or the seam lines of the small plies in this layer can be covered by the small plies in the adjacent plies.

[0028] Preferably, in the above-mentioned composite material laminated reflective panel, the small plywood is of any polygonal shape or any curved shape.

[0029] Preferably, in the above-mentioned composite laminated reflective panel, the ply direction of each small ply is rotated; within the same layer, the ply angles corresponding to the ply directions of adjacent small ply have the same absolute value and opposite signs, and the ply angles corresponding to the ply directions of alternating small ply are the same; when the half-thickness ply of the composite laminated reflective panel simultaneously includes ply with a ply angle of 0° and ply with a ply angle of 90°, then the ply with a ply angle of 0° and the ply with a ply angle of 90° are... In a ply with a 90° ply angle, the ply angle of the adjacent ply with a 0° ply angle is 90°, and the ply angle of the ply alternating ply with a 0° ply angle is 0°. When the half-thickness ply of the composite laminate reflective panel includes ply with a 0° ply angle but does not include ply with a 90° ply angle, the ply angle corresponding to the ply direction of the ply with a 0° ply angle is 0°, and no ply direction rotation is performed. Within the half-thickness of the composite laminate reflective panel, any ply angle of +|θ (i) If no ply orientation rotation is performed within a ply of |, then the ply angle is -|θ. (i) Within a single layup, the layup orientation of smaller plies is not rotated. When a half-thickness layup of a composite laminate reflective panel contains both layups with a 0° angle and layups with a 90° angle, if the layup orientation of the smaller plies in the 0° angle layup is not rotated, then the layup orientation of the smaller plies in the 90° angle layup is also not rotated. A maximum of two layups with non-rotating layup orientations can be contained within a half-thickness layup of a composite laminate reflective panel.

[0030] Preferably, in the above-mentioned composite material laminated reflective panel, the half-thickness ply of the composite material laminated reflective panel is selected from the candidate set {Θ}, which is composed of all permutations of all elements obtained by copying each element of the basic angle set θ q≥1 times.

[0031] Preferably, in the above-mentioned composite laminate reflective panel, the layup in any region of the composite laminate reflective panel is as follows: r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. A symmetric set of r = 1, 2, ... and a half-thickness ply. In the case of r = 1, 2, ..., the absolute values ​​of the ply angles of any two adjacent layers are not equal.

[0032] Preferably, in the above-mentioned composite laminate reflective panel, the layup in any region of the composite laminate reflective panel is as follows: r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. The symmetric set r = 1, 2, ..., the half-thickness ply r = 1, 2, ... are all elements [Θ] in the candidate set {Θ} r The symmetric set [Θ] of r = 1, 2, ... r ] s By performing layup, the stiffness matrix [K] of the composite laminate panel is obtained.

[0033]

[0034] Optimize according to the following objective function.

[0035]

[0036] or

[0037]

[0038] The obtained half-thickness layup r = 1, 2, ... or half-thickness ply r = 1, 2, ...

[0039] Preferably, in the above-mentioned composite laminate reflective panel, any element θ of the basic angle set θ (k) The condition -π / 2 < θ is satisfied. (k) ≤π / 2, where k=1,2,...,N, N≥2, and N is an integer.

[0040] When N=2, the basic angle set is Furthermore, when N = 2n and n ≥ 2, the basic angle set is θ = [θ(1) θ (2) , ...,θ (2n) ],and

[0041]

[0042] Furthermore, when N = 2n - 1 and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n-1) ],and

[0043]

[0044] Compared with existing technologies, the above technical solution has the following advantages:

[0045] 1. The composite laminated reflective panel prepared by small-block layup can be a parabola, a sphere, or any irregularly shaped curved surface;

[0046] 2. By setting specific layup angles and layup methods, it can be ensured that the prepared composite laminated reflective panel has quasi-isotropic properties in any region, or quasi-isotropic properties both in and out of the plane, or quasi-isotropic properties both in and out of the plane, while minimizing the bending-torsional coupling effect and having quasi-zero expansion properties in any region.

[0047] 3. This invention first uses mature CAE software or surface flattening software to obtain the pattern of small pieces of each layer of composite laminate reflective panel through simulation calculations, etc. Then, small pieces are prepared using unidirectional continuous fiber reinforced prepreg, and splicing and laying are completed according to the preset layup angle and layup method to obtain composite laminate reflective panel with arbitrary curved surface geometry. The operation method is simple and easy to implement. Attached Figure Description

[0048] Figure 1a This illustrates a basic layup configuration conforming to a preferred embodiment of the present invention: a square shape at 0°.

[0049] Figure 1b This illustrates a basic layup pattern conforming to another preferred embodiment of the invention: a crisscross pattern at 0°.

[0050] Figure 1c This illustrates a basic layup pattern conforming to another preferred embodiment of the invention: a 45° herringbone pattern;

[0051] Figure 2a This illustrates a basic layup configuration conforming to a preferred embodiment of the present invention: small opening - large opening 0°;

[0052] Figure 2bThis illustrates a basic layup arrangement conforming to another preferred embodiment of the present invention: a small opening to a large opening at a 45° angle;

[0053] Figure 2c This illustrates a basic slab arrangement conforming to another preferred embodiment of the present invention: Oda-Oda 45°;

[0054] Figure 2d This illustrates a basic planar arrangement conforming to another preferred embodiment of the present invention: small opening - large field 0°;

[0055] Figure 2e This illustrates a basic planar arrangement conforming to another preferred embodiment of the present invention: large opening - small opening 0°;

[0056] Figure 2f This illustrates a basic layup configuration conforming to another preferred embodiment of the invention: small opening - large field 45°;

[0057] Figure 2g This illustrates a basic slab arrangement conforming to another preferred embodiment of the present invention: a large opening to a small opening at 45°.

[0058] Figure 3a This illustrates a splicing and tiling combination method for two layers with unequal absolute values ​​of arbitrary ply angles, conforming to a preferred embodiment of the present invention: based on Figure 2f ;

[0059] Figure 3b This illustrates a splicing and tiling combination method for two layers with unequal absolute values ​​of arbitrary ply angles, conforming to another preferred embodiment of the present invention: based on Figure 2c ;

[0060] Figure 3c This illustrates a splicing and tiling combination method for two layers with unequal absolute values ​​of arbitrary ply angles, conforming to another preferred embodiment of the present invention: based on Figure 2b ;

[0061] Figure 4a This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to a preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2f and Figure 1b The half-thickness layup of the corresponding composite laminated reflective panel is: [-60° / 0° / 60°].

[0062] Figure 4b This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2f and Figure 1aThe half-thickness layup of the corresponding composite laminated reflective panel is: [-60° / 0° / 60°].

[0063] Figure 4c This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2b and Figure 1a The half-thickness layup of the corresponding composite laminated reflective panel is: [-60° / 0° / 60°].

[0064] Figure 4d This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2f and Figure 1b The half-thickness layup of the corresponding composite laminated reflective panel is: [0° / 45° / 90° / -45°].

[0065] Figure 4e This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2f and Figure 1c The corresponding half-thickness layup of the composite laminated reflective panel is: [-45° / 0° / 90° / 45°].

[0066] Figure 4f This illustrates the splicing and laying method of the small plies within half the thickness of a composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small ply: based on Figure 2f , 2c and Figure 1c The corresponding half-thickness layup of the composite laminate reflective panel is: [-45° / 0° / -67.5° / 67.5° / 90° / -22.5° / 22.5° / 45°].

[0067] Figure 5 The diagram illustrates the splicing and laying method of the small pieces of each layer of an eight-layer composite laminated reflective panel conforming to a preferred embodiment of the present invention, and the layup direction of each small piece: [0° / 45° / 90° / -45°]. s .

[0068] Figure 6 The diagram illustrates the splicing and laying method of the small pieces of each layer of an eight-layer composite laminated reflective panel conforming to another preferred embodiment of the present invention, and the layup direction of each small piece: [-45° / 90° / 0° / 45°]. s .

[0069] Figure 7 A preferred example of a composite laminate panel layup is shown.

[0070] Figure label:

[0071] 120 - Basic tiling unit; 130 - Pile coordinate system; 140 - Pile joint line; 141 - Pile pattern; 142 - Edge tiling piece; 150 - Pile direction. Detailed Implementation

[0072] The advantages of the present invention will be further illustrated below with reference to the accompanying drawings and specific embodiments.

[0073] This invention provides a method for preparing a composite laminated reflective panel. The panel is made by splicing small pieces of unidirectional continuous fiber-reinforced prepreg together according to a predetermined layup direction and splicing method to form a composite laminated reflective panel with an arbitrary predetermined curved surface geometry. According to the following preparation method, the prepared composite laminated reflective panel exhibits quasi-zero expansion characteristics in any region; simultaneously, it possesses in-plane quasi-isotropic characteristics in any region, or quasi-isotropic characteristics both in-plane and out-of-plane, or quasi-isotropic characteristics both in-plane and out-of-plane, while minimizing the bending-torsional coupling effect.

[0074] The preset geometry of the composite laminate reflective panel is a parabola, a sphere, or an arbitrarily shaped curved surface. Directly using large-area unidirectional continuous fiber-reinforced prepreg for layup of the composite laminate reflective panel will inevitably result in wrinkles, making it impossible to obtain a smooth and high-precision composite laminate reflective panel, thus affecting the mechanical properties and functionality of the reflector. Directly using small-piece splicing and laying cannot guarantee the basic homogeneity and quasi-zero expansion characteristics of the composite laminate reflective panel in any region.

[0075] This invention provides a method for preparing a composite material laminated reflective panel, the specific steps of which are as follows:

[0076] (1) Determine the layup method of the composite laminated reflective panel

[0077] Determining the layup method of the composite laminate reflective panel includes determining the layup angle and layup sequence of each layer. The composite laminate reflective panel of this embodiment is a laminated structure with an arbitrary preset curved surface geometry formed by layup, which is then cured to obtain the composite laminate panel. Preferably, the composite laminate reflective panel of this embodiment contains at least four layups, and the number of layups containing at least two different small piece layup directions within the same layer is at least four. This ensures that the prepared composite laminate reflective panel exhibits quasi-isotropic properties in any region, or quasi-isotropic properties both in-plane and out-of-plane, or quasi-isotropic properties both in-plane and out-of-plane, while minimizing bending-torsional coupling effects and exhibiting quasi-zero expansion properties in any region. To illustrate the above advantages and feasibility of this embodiment, specific layup examples are provided as follows:

[0078] The half-thickness ply of the composite laminate reflective panel (the "half-thickness ply" refers to a ply that comprises half the thickness of all the plies) is [Θ] = [θ]. (1) θ (2) , ...,θ (p) The complete layup of the composite laminated reflective panel is as follows:

[0079] [Θ] s =[θ (1) θ (2) , ..., θ (p-1) ,θ (p) θ (p+1) θ (p+2) , ...,θ (2p-1) ,θ (2p) ], complete layup [Θ] s Let be a symmetric set of half-thickness ply [Θ]. The ply angle of the i-th layer in the composite laminate reflective panel is θ. (i) 1≤i≤2p, and i is an integer. The piling order is to stack the first layer to the second p layer in sequence. The i-th layer and the second p-i+1-th layer are symmetrical layers. The piling angles of the two symmetrical layers are the same, and the piling direction, shape, and splicing method of the small piling pieces in the two layers are the same.

[0080] In this embodiment, any element θ of the basic angle set θ (k) The condition -π / 2 < θ is satisfied. (k) ≤π / 2, where k=1,2,...,N, N≥2, and N is an integer.

[0081] When N=2, the basic angle set is

[0082] Furthermore, when N = 2n and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n) ],and

[0083]

[0084] Furthermore, when N = 2n - 1 and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n-1) ],and

[0085]

[0086] The half-thickness ply of the composite laminate reflective panel is selected from the candidate set {Θ}, which is composed of all permutations of all elements obtained by copying each element of the basic angle set θ q≥1 times.

[0087] Preferably, the layup in any area of ​​the composite laminated reflective panel can be... r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. A symmetric set of r = 1, 2, ... and a half-thickness ply. In the range r = 1, 2, ..., the absolute values ​​of the ply angles of any two adjacent layers are not equal. The resulting composite laminate reflective panel exhibits in-plane quasi-isotropic properties in any region, and any two layers within half the thickness of the composite laminate reflective panel can achieve mutual overlap of the seams between adjacent layers, or the seam line of one layer can be partially covered by the seam line of another layer. The ply of the composite laminate reflective panel is defined as... For any fixed layup of r = 1, 2, ..., see the preferred layup example of a composite laminate reflective panel that meets the requirements. Figure 7 Table 1.

[0088] Preferably, the layup of the composite laminated reflective panel can be optimized to obtain a preferred half-thickness layup. r = 1, 2, ..., and this half-thickness layer is then laid up. Symmetric sets of r = 1, 2, ... r = 1, 2, ... represents the layup within any region of the composite laminated reflective panel. Specific optimization methods may include using all elements [Θ] in the candidate set {Θ}. r The symmetric set [Θ] of r = 1, 2, ... r ] s After performing the layup, the stiffness matrix [K] of the composite laminate panel is calculated.

[0089]

[0090] The obtained stiffness matrix [K] is then optimized using the following objective function.

[0091]

[0092] or

[0093]

[0094] The optimization objective function Fun1([Θ r The preferred half-thickness layup obtained is r = 1, 2, ..., with its symmetric set Using any fixed ply of r = 1, 2, ... as the ply of the composite laminated reflective panel, according to the preparation method of the composite laminated reflective panel of this patent, the prepared composite laminated reflective panel has quasi-isotropic properties both in-plane and out-of-plane in any region. The optimization objective function Fun2([Θ r The preferred half-thickness layup method obtained is: r = 1, 2, ..., with its symmetric set Using any fixed layup of r = 1, 2, ... as the layup of the composite laminated reflective panel, according to the preparation method of the composite laminated reflective panel of this patent, the prepared composite laminated reflective panel has quasi-isotropic characteristics both in-plane and out-of-plane in any region, while minimizing the bending-torsional coupling effect. Based on the above optimization results, preferably, the layup of the composite laminated reflective panel can be selected from... Any fixed ply with r = 1, 2, ... r = 1, 2, ... can be... r = 1, 2, ... or r = 1, 2, ... . Preferred layup examples of composite laminated reflective panels that meet the requirements are shown in the figure. Figure 7 Table 2.

[0095] (2) Determine the splicing and laying method of each small piece in the composite laminated reflective panel.

[0096] Determine the shape of the small paving pieces for each layer, and based on the shape of the small paving pieces, determine the splicing and laying method for the small paving pieces in each layer.

[0097] First, determine the ply coordinate system of the composite laminated reflective panel. Using this ply coordinate system as a reference, determine the splicing and laying method of each layer's small ply pieces, the splicing and laying combination method of any two layers' small ply pieces, and the ply direction of each layer's small ply pieces.

[0098] If the edge curve of the composite laminate reflective panel is a planar curve, then the plane containing the edge curve of the composite laminate reflective panel is the working surface for laying and splitting the composite laminate reflective panel; if the edge curve of the composite laminate reflective panel is a spatial non-planar curve, then discrete points of a certain density are arranged on the edge curve of the composite laminate reflective panel, and the best fitting plane of these discrete points is the working surface for laying and splitting the composite laminate reflective panel.

[0099] The edge curve of the composite laminate reflective panel is projected onto the layup section of the composite laminate reflective panel along the plane normal. If the projected curve is a regular circle, ellipse, or regular polygon, its geometric center is taken as the origin of the layup coordinate system of the composite laminate reflective panel. If the projected curve is irregular, a regular curve, such as a circle, ellipse, or regular polygon, is used to perform optimal curve fitting on discrete points on the projected curve, and the geometric center of this optimally fitted curve is taken as the origin of the layup coordinate system of this type of composite laminate reflective panel; or the geometric center of the projected curve is taken as the origin of the layup coordinate system of this type of composite laminate reflective panel. Any direction within the layup section of the composite laminate reflective panel is defined as the X-axis, and the direction perpendicular to it, based on the right-hand side, is defined as the Y-axis. The normal of the layup section is defined as the Z-axis, establishing the layup coordinate system 130 for the composite laminate reflective panel.

[0100] Then, determine the shape of the small paving pieces in each layer and the splicing and laying method of the small paving pieces in each layer.

[0101] Specifically, the small plywood, as the smallest unit within each layer of the composite laminated reflective panel, is also referred to herein as the basic plywood unit 120 of the composite laminated reflective panel. Preferably, the basic plywood unit 120 in this embodiment is quadrilateral in shape. It should be understood that, depending on the needs of actual applications, the basic plywood unit 120 can also be set to other geometric shapes, and such settings do not depart from the inventive concept of the present invention and are also within the protection scope of the present invention.

[0102] Preferably, this embodiment also lists the following basic tiling methods to fully illustrate the splicing and tiling method of each small tiling piece in each layer: 1) □-shaped 0°: composed of a square-shaped basic tiling unit 120, the geometric center of which is located at the origin of the ply coordinate system 130, and the two mutually perpendicular sides of the basic tiling unit 120 are parallel to the X-axis and Y-axis of the ply coordinate system 130, respectively. See Figure 1a2) Grid-shaped 0°: Composed of four basic square-shaped ply units 120. The center of this grid shape is located at the origin of the ply coordinate system 130. The two perpendicular midlines of the grid shape coincide with the X-axis and Y-axis of the ply coordinate system. See [link / reference] Figure 1b 3) 45° (grid pattern): The basic layup pattern in 2) undergoes an angular deflection around the Z-axis of the 130° ply coordinate system. For example, the basic layup pattern obtained by a 45° deflection is shown in [reference needed]. Figure 1c Based on the above basic tiling methods, the tiling can be expanded in the same way, or the tiling angle can be deflected and the tiling expanded based on the above basic tiling methods, or the tiling can be expanded by combining the above basic tiling methods, thus obtaining the splicing and laying method of small tiling pieces in each layer.

[0103] (3) Determine the splicing and laying combination method of any two small pieces in the composite laminated reflective panel.

[0104] Preferably, in the composite laminated reflective panel, the layup angle of any two layers within half the thickness is θ for the i-th layer. (i) The ply angle of the k-th layer is θ. (k) If |θ (i) |≠|θ (k) If |θ|, then the splicing and laying methods of the two layers of small ply tiles are different, and the seam lines of the two layers of small ply tiles overlap each other or the seam line of one layer is partially covered by the seam line of the other layer; if |θ| (i) |=|θ (k) If the two layers of small paving tiles are laid in the same way, then the seam lines of the two layers of small paving tiles overlap.

[0105] Where, |θ (i) |≠|θ (k) The two layers are independent layers. Preferably, this embodiment lists several basic tiling combinations consisting of basic tiling units 120 for two independent layers to fully illustrate the splicing and tiling combination methods of any two layers of small tiling pieces. The seam covering method of the two independent layers is not limited to the following examples.

[0106] 1) Small-mouth-Large-mouth 0°: A combination of two 0° basic tile patterns consisting of square basic tile units 120 with side lengths a and 2a. See also Figure 2a .

[0107] 2) Small-mouth to large-mouth 45°: A 0° basic tile arrangement composed of 120 square basic tile units with side length a, and a side length of... A basic tiling pattern consisting of 120 square basic tiling units arranged in a 45° "U" shape. See also... Figure 2b .

[0108] 3) Small field - large field 45°: A combination of the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length a forming a cross - shaped pattern and the 45° basic tiling pattern of the square - shaped basic tiling unit 120 with side length a forming a cross - shaped pattern. See ... Figure 2c

[0109] 4) Small opening - large field 0°: A combination of the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length a forming a square - opening pattern and the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length 2a forming a cross - shaped pattern. See Figure 2d ...

[0110] 5) Large opening - small field 0°: A combination of the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length 3a / 2 forming a square - opening pattern and the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length a forming a cross - shaped pattern. See Figure 2e ...

[0111] 6) Small opening - large field 45°: A combination of the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length... forming a square - opening pattern and the 45° basic tiling pattern of the square - shaped basic tiling unit 120 with side length a forming a cross - shaped pattern. See Figure 2f ...

[0112] 7) Large opening - small field 45°: A combination of the 45° basic tiling pattern of the square - shaped basic tiling unit 120 with side length 2a forming a square - opening pattern and the 0° basic tiling pattern of the square - shaped basic tiling unit 120 with side length... forming a cross - shaped pattern. See Figure 2g ... Among them, Figures 2a-2g the solid line represents the tiling seam line 140 of the basic tiling unit 120 in one layer of the independent layer, and the dashed line represents the tiling seam line 140 of the basic tiling unit 120 in the other layer of the independent layer.

[0113] Preferably, based on the above - mentioned basic tiling combination method, the splicing and tiling combination method of small pieces of any two layers of the composite material laminated reflector panel can be obtained through a linear array. See Figures 3a-3c ... Examples are given of the splicing and tiling combination methods of small pieces of two independent layers with different absolute values of the lay - up angles. Among them, the solid line and the dashed line respectively represent the tiling seam lines 140 of two independent layers in the tiling dissection working surface of the reflector panel, and |θ (i) |≠|θ (k) |. Among them, Figure 3a the splicing and tiling combination method in... is obtained based on Figure 2f ...; Figure 3b the splicing and tiling combination method in... is obtained based on​ Figure 2c Obtained; Figure 3c The splicing and laying combination method in is based on Figure 2b Obtained.

[0114] Preferably, among them, the splicing and laying methods of the small patches at the edges are all conformable to the shape of the projection curve of the edge curve of the reflection panel along the normal direction of the patch剖分plane. Preferably, when the basic patch unit is in the shape of a quadrilateral, the shape of the small patches at the boundary, that is, the shape of the edge small patch 142, is the shape formed by the intersection of the quadrilateral and the projection curve of the edge curve of the reflection panel along the normal direction of the patch剖分plane (see Figures 3a-3c ).

[0115] Preferably, the basic patch unit 120 can also be any quadrilateral, such as a non-square, see Figure 6 . When |θ (i) | ≠ |θ (k) |, the basic patch combination method formed by the two independent layers from the basic patch units is the Tianzi-Zigou combination method. In particular, the basic patch unit of the Zigou-shaped basic patch method is formed by connecting the four points far from the center point of the Tianzi shape at the four internal stitching lines of the Tianzi-shaped basic patch method as vertices. The splicing and laying methods of the small patches of each layer of the finally formed eight-layer composite material laminated reflection panel and the laying direction of the small patches of each layer are shown in Figure 6 .

[0116] (4) Determine the laying direction of the small patches of each layer in the composite material laminated reflection panel

[0117] In this embodiment, the laying angle corresponding to the laying direction of the basic patch unit 120 of each layer closest to the origin of the laying coordinate system 130 of the composite material laminated reflection panel is the same as the laying angle of that layer. The laying of the composite material laminated reflection panel is selected from any laying preferred result in Table 1 or Table 2 of the preferred examples. After the laying of the composite material laminated reflection panel is determined, the laying angle of each layer of the composite material laminated reflection panel can be obtained. Based on this laying angle, according to the method of the embodiment, determine the shape of the small patches of each layer, the laying method of the small patches of each layer, the splicing and laying combination method of the small patches of any two layers, and the laying direction of the small patches within each layer.

[0118] Within the same layer, adjacent ply sections have the same absolute value and opposite sign for their ply angles, while alternating ply sections have the same ply angle. When a half-thickness ply of a composite laminate reflective panel contains both layers with a ply angle of 0° and layers with a ply angle of 90°, the ply angle of the ply section adjacent to the ply section with a ply angle of 0° is 90°, and the ply angle of the ply section alternating with the ply section with a ply angle of 0° is 0°. When a half-thickness ply of a composite laminate reflective panel contains layers with a ply angle of 0° but not layers with a ply angle of 90°, the ply angle corresponding to the ply direction of the ply section in the 0° layer is always 0°, and no ply direction rotation is performed. Furthermore, within the half-thickness of the composite laminate reflective panel, any ply angle of +|θ (i) If no ply orientation rotation is performed within a ply of |, then the ply angle is -|θ. (i) Within a single layup, the layup orientation of smaller plies is not rotated. When a half-thickness layup of a composite laminate reflective panel contains both layups with a 0° angle and layups with a 90° angle, if the layup orientation of the smaller plies in the 0° angle layup is not rotated, then the layup orientation of the smaller plies in the 90° angle layup is also not rotated. A maximum of two layups with non-rotating layup orientations can be contained within a half-thickness layup of a composite laminate reflective panel.

[0119] Specifically, in this embodiment, the composite laminate reflective panel can be achieved through symmetrical layup. The layup angle of the i-th layer of the composite laminate reflective panel is θ. (i) If 1 ≤ i ≤ 2p, and i is an integer, then the i-th layer and the 2p-i+1-th layer are symmetrical layers. The ply angles of the two symmetrical layers are the same, and the ply direction, shape, and splicing method of the small ply tiles in both layers are also the same. (See also...) Figure 5 and Figure 6 This section describes the splicing and laying method of the small plies of each layer in two examples of composite laminated reflective panels containing eight layers, as well as the layup direction of each small ply. Figure 5 The layup of the eight-layer composite laminated reflective panel is selected from Table 1. Figure 5 The layup of the eight-layer composite laminated reflective panel is selected from Table 2.

[0120] Preferably, it is only necessary to ensure that the composite laminated reflective panel has quasi-isotropy and essentially zero expansion characteristics within any area, while ensuring the strength of the reflective panel after molding, and that the seams of adjacent small ply sheets overlap. In this case, the ply of the composite laminated reflective panel is selected from any of the preferred ply results in Appendix 1 of the preferred examples. The ply orientation of each small ply sheet is determined according to the above method. See [link to relevant documentation] Figures 4a-4dTo utilize the ply optimization results selected from Appendix 1 of the preferred examples, the splicing and laying methods of the small plies in each layer within half the thickness of several preferred composite laminated reflective panels and the layup direction of each small ply are obtained. Figure 5 To utilize the ply optimization results selected from Appendix 1 of the preferred examples, a preferred ply method and ply direction for the small ply sheets of each layer of an eight-layer composite laminated reflective panel are obtained.

[0121] Preferably, to ensure that the composite laminated reflective panel has quasi-isotropy both inside and outside the surface in any region and possesses essentially zero expansion characteristics, the layup of the composite laminated reflective panel is selected from any of the preferred layup results in Appendix 2 of the preferred examples. Determine the layup orientation of each small tile in each layer using the method described above. (See also...) Figure 4e-4f To utilize the ply selection results selected from Appendix 2 of the preferred examples The splicing and laying method of small pieces in each layer within half the thickness of the two preferred composite laminated reflective panels and the laying direction of each small piece are obtained. Figure 6 To utilize the ply selection results selected from Appendix 2 of the preferred examples A preferred eight-layer composite laminated reflective panel is obtained, which has a preferred layup method and layup direction for each layer of the small-piece plywood.

[0122] In particular, with Figure 4f The embodiments are further described in detail. Figure 4f The embodiments are selected from the preferred examples, Appendix 2, ply selection results. (p=8, q=1). This preferred embodiment ensures that the composite laminated reflective panel exhibits quasi-isotropy both in-plane and out-of-plane properties and possesses essentially zero expansion characteristics in any region. Therefore, based on this preferred layup result, the layups in any region of the prepared composite laminated reflective panel must be selected from… r = 1, 2, ..., 16 (p = 8, q = 1). Choose [-45° / 0° / -67.5° / 67.5° / 90° / -22.5° / 22.5° / 45°] s For the layup of composite laminated reflective panels. Figure 4fThe diagram illustrates the splicing and laying method of each small ply of the half-thickness layup of the composite laminate reflective panel, as well as the layup direction of each small ply. The layup angle of the first layer is -45°, and the layup angle of the corresponding small ply is either 45° or -45°. The layup angle of the second layer is 0°. Because this half-thickness layup of the composite laminate reflective panel includes both layups with a layup angle of 0° and layups with a layup angle of 90°, the layup angle of the small ply corresponding to the layup with a layup angle of 0° is either 0° or 90°. The absolute values ​​of the layup angles of the first and second layers are not equal. In this embodiment, the splicing and combination method of the small ply of the first and second layers ensures that the seam lines of the two layers overlap. The preferred layup results are shown in Appendix 2 of the Preferred Examples. (p=8, q=1), and satisfy the requirement that the layup in any region of the composite laminated reflective panel must be selected from... For plots with r = 1, 2, ..., 16 (p = 8, q = 1), the second layer has a ply angle of 0°. The corresponding third and fourth layers have ply directions that alternate between 67.5° and -67.5°, with any number of alternations. For plots with a second layer ply angle of 90°, the corresponding third and fourth layers have ply directions that alternate between 22.5° and -22.5°, with any number of alternations. The absolute values ​​of the ply angles of the second and third layers are not equal. In this embodiment, the ply arrangement of the second and third layers ensures that the seam line of one layer is partially covered by the seam line of the other layer. The ply angle of the third layer is -67.5°, and the ply angle of the fourth layer is 67.5°; the absolute values ​​of these two ply angles are equal. Therefore, the ply arrangement of the third and fourth layers is the same. If the ply angle of the fifth layer is 90°, then the splicing and laying method of the small ply tiles in this layer is the same as that of the second layer, which has a ply angle of 0°. Similarly, according to the preferred ply optimization results in Appendix 2 of the preferred examples... (p=8, q=1) and the layup in any area of ​​the composite laminated reflective panel must be selected from... For ply plots with p = 1, 2, ..., 16 (p = 8, q = 1), the fifth layer has a ply angle of 90°, and the corresponding sixth and seventh layers have ply angles alternating between 22.5° and -22.5°. For ply plots with a fifth layer ply angle of 0°, the corresponding sixth and seventh layers have ply angles alternating between 67.5° and -67.5°. The absolute values ​​of the ply angles of the sixth and seventh layers are equal; therefore, the splicing direction of these two layers is the same. The splicing direction of the ply plots of the eighth layer (45°) is the same as that of the first layer (-45°). The half-thickness ply of the composite laminate reflective panel is selected from the preferred examples in Appendix 2, ply optimization results. (p=8, q=1), the splicing and laying method of each layer of small pavers and the laying direction of each layer of small pavers are described in [reference needed]. Figure 4f.

[0123] (5) Preparation of small-piece paving and reflective panel installation

[0124] Preferably, according to the splicing and laying method of each layer of small plywood and the layup direction of each layer of small plywood obtained in the above embodiments, the splicing and laying pattern 141 of each layer of composite laminated reflective panel is sequentially realized in the plywood splitting working surface of the reflective panel; then, the splicing and laying pattern 141 of each layer of small plywood obtained above is used to divide the reflective panel with a preset curved surface shape along the normal of the plywood splitting working surface of the reflective panel. The reflective panel is divided into several small curved surfaces with small curvature, and these small curved surfaces are all part of the overall curved reflective panel; then, using mature CAE software or surface flattening software, the planar small plywood pattern after flattening these small curved surfaces can be obtained, that is, the shape of the small plywood. The small plywood of each layer of composite laminated reflective panel is made using this planar small plywood pattern. Based on the shape of the small plywood determined in the above embodiments, preferably, unidirectional continuous fiber reinforced prepreg is used to prepare the small plywood. Based on the aforementioned determined splicing and laying method and layup direction of each layer of the composite laminated reflective panel, the prepared small pieces are spliced ​​and laid to form a layup with an arbitrary preset curved surface geometry. According to the splicing and laying method of any two layers of small pieces, small pieces are spliced ​​and laid on the already spliced ​​and laid layup according to the preset splicing and laying method and layup direction. After completing the laying of the preset number of layers, a laminated structure with an arbitrary preset curved surface geometry is obtained. The obtained laminated structure is cured to produce a composite laminated reflective panel with quasi-isotropic properties in any region, or quasi-isotropic properties both in and out of the surface, or quasi-isotropic properties both in and out of the surface, while minimizing the bending-torsional coupling effect, and having quasi-zero expansion properties in any region.

[0125] Another aspect of the present invention is to provide a composite material laminated reflective panel prepared using the preparation methods of the above embodiments. See also... Figure 5 and Figure 6As can be seen, the composite material laminated reflective panel provided in this embodiment has an arbitrary preset curved surface geometry and mainly includes: at least one small piece of unidirectional continuous fiber-reinforced prepreg, at least four layers of plywood spliced ​​from the small pieces of ploughing according to a preset plying direction and splicing method, wherein the number of plywoods containing at least two different plying directions in the same layer is at least four, any two layers of plywood have a preset plywood splicing combination method, ensuring that the seam lines of the small pieces of ploughing with different splicing methods overlap each other or that the seam line of one layer of plywood is partially covered by the seam line of another layer of plywood; any plywood area has a symmetrical and balanced plywood method and quasi-zero expansion characteristics; any plywood area satisfies the following: quasi-isotropic characteristics in-plane, or quasi-isotropic characteristics in-plane and out-of-plane, or quasi-isotropic characteristics in-plane and out-of-plane with minimal bending-torsional coupling effect.

[0126] Based on the above embodiments, in some other preferred embodiments of the composite laminate reflective panel, the half-thickness ply of the composite laminate reflective panel is [Θ] = [θ]. (1) θ (2) , ...,θ (p) The complete layup of the composite laminated reflective panel is as follows:

[0127] [Θ] s =[θ (1) θ (2) , ..., θ (p-1) ,θ (p) θ (p+1) θ (p+2) , ...,θ (2p-1) ,θ (2p) ],

[0128] Complete layup [Θ] s Let θ be the symmetric set of half-thickness ply [Θ], where the ply angle of the i-th layer of the composite laminate reflective panel is θ. (i) 1≤i≤2p, and i is an integer. The piling order is to stack the first layer to the second p layer in sequence. The i-th layer and the second p-i+1-th layer are symmetrical layers. The piling angles of the two symmetrical layers are the same, and the piling direction, shape, and splicing method of the small piling pieces in the two layers are the same.

[0129] Based on the above embodiments, in some other preferred embodiments of the composite material laminated reflective panel, within half the thickness of the composite material laminated reflective panel, in the splicing and tiling combination of any two layers of small pieces, the layup angles are respectively θ. (i) and θ (k) If |θ (i) |≠|θ (k)If |θ|, then the splicing and laying methods of the two layers of small ply tiles are different, and the seam lines of the two layers of small ply tiles overlap each other or the seam line of one layer is partially covered by the seam line of the other layer; if |θ| (i) |=|θ (k) If the two layers of small plies are laid in the same way, and the seam lines of the two layers of small plies overlap, then the splicing and laying methods of the small plies of the two layers of 0° and 90° are the same. If the half-thickness ply of the composite laminate reflective panel includes both plies with a ply angle of 0° and plies with a ply angle of 90°, then the splicing and laying methods of the small plies of the plies with a ply angle of 0° are arbitrary, and the small plies of this layer can cover the seam lines of the small plies of the adjacent plies or the seam lines of the small plies of this layer can be covered by the small plies of the adjacent plies.

[0130] In some preferred embodiments of the composite material laminated reflective panel based on the above embodiments, the small ply is of any polygonal shape or any curved shape. Preferably, the small ply can be quadrilateral.

[0131] Based on the above embodiments, in some other preferred embodiments of the composite laminate reflective panel, the layup direction of the small plies in each layer is rotated; within the same layer, the absolute values ​​of the layup angles corresponding to the layup directions of adjacent small plies are the same and opposite in sign, and the layup angles corresponding to the layup directions of alternating small plies are the same; when the half-thickness layup of the composite laminate reflective panel simultaneously includes layups with a layup angle of 0° and layups with a layup angle of 90°, then the layup angle of the small plies adjacent to the small plies with a layup angle of 0° is 90°, and the layup angle of the small plies alternating with the small plies with a layup angle of 0° is 0°; when the half-thickness layup of the composite laminate reflective panel includes layups with a layup angle of 0° but does not include layups with a layup angle of 90°, then the layup angles corresponding to the layup directions of the small plies of the layups with a layup angle of 0° are all 0°, and no layup direction rotation is performed. Within half the thickness of the composite laminated reflective panel, any layup angle is +|θ (i) If no ply orientation rotation is performed within a ply of |, then the ply angle is -|θ. (i) Within a single layup, the layup orientation of smaller plies is not rotated. When a half-thickness layup of a composite laminate reflective panel contains both layups with a 0° angle and layups with a 90° angle, if the layup orientation of the smaller plies in the 0° angle layup is not rotated, then the layup orientation of the smaller plies in the 90° angle layup is also not rotated. A maximum of two layups with non-rotating layup orientations can be contained within a half-thickness layup of a composite laminate reflective panel.

[0132] In some other preferred embodiments based on the above embodiments, the half-thickness ply of the composite material laminated reflective panel is selected from the candidate set {Θ}, which is composed of all permutations of all elements obtained by copying each element of the basic angle set θ q≥1 times.

[0133] Based on the above embodiments, in some other preferred embodiments of the composite laminate reflective panel, the layup in any region of the composite laminate reflective panel is... r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. A symmetric set of r = 1, 2, ... and a half-thickness ply. In the case of r = 1, 2, ..., the absolute values ​​of the ply angles of any two adjacent layers are not equal.

[0134] Based on the above embodiments, in some other preferred embodiments of the composite laminate reflective panel, the layup in any region of the composite laminate reflective panel is... r = 1, 2, ..., which represents the half-thickness layup of the composite laminated reflective panel. The symmetric set r = 1, 2, ..., the half-thickness ply r = 1, 2, ... are all elements [Θ] in the candidate set {Θ} r The symmetric set [Θ] of r = 1, 2, ... r ] s By performing layup, the stiffness matrix [K] of the composite laminate panel is obtained.

[0135]

[0136] Optimize according to the following objective function.

[0137]

[0138] or

[0139]

[0140] The obtained half-thickness layup r = 1, 2, ... or half-thickness ply r = 1, 2, ...

[0141] Based on the above embodiments, in some other preferred embodiments of the composite laminate reflective panel, any element θ of the basic angle set θ (k) The condition -π / 2 < θ is satisfied. (k) ≤π / 2, where k=1,2,...,N, N≥2, and N is an integer.

[0142] When N=2, the basic angle set is

[0143] Furthermore, when N = 2n and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n) ],and

[0144]

[0145] Furthermore, when N = 2n - 1 and n ≥ 2, the basic angle set is θ = [θ (1) θ (2) , ...,θ (2n-1) ],and

[0146]

[0147] It should be understood that the composite laminate reflective panels described in the above embodiments can be prepared by the preparation method proposed in this invention, and therefore have all the characteristics of the composite laminate reflective panels prepared by the preparation method of this invention. Therefore, the relevant preferred or special examples of composite laminate reflective panels listed in the embodiment section of the preparation method of this invention are also applicable to the relevant embodiments of the above composite laminate reflective panels, and will not be repeated here.

[0148] It should be noted that the embodiments of the present invention have better implementability and are not intended to limit the present invention in any way. Any person skilled in the art may use the above-disclosed technical content to change or modify it into equivalent effective embodiments. However, any modifications or equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A method of making a composite laminated reflector panel, characterized in that, The method comprises the following steps: The layup method of the composite laminated reflective panel is determined, including the layup angle and layup sequence; wherein, the half-thickness layup of the composite laminated reflective panel is selected from a candidate set. Complete layup For half-thickness layup The symmetric set, the candidate set From the basic angle set Each element passes through The permutation of all elements obtained after the first copy; the basic angle set. any element ,satisfy ,in, , , It is an integer. When the basic angle set is ; Further, when and the set of basic angles is and Further, when and the set of basic angles is and determining the shape of the small patch; determining the splicing and paving mode of the small patch of each layer according to the shape of the small patch; wherein the absolute values of the layer angles corresponding to the layer directions of adjacent small patches in the same layer are the same and the signs are opposite, and the layer angles corresponding to the layer directions of the small patches between layers are the same; determining the splicing and paving combination mode of the small patches of any two layers, so as to ensure that the splicing lines of the layers with different splicing and paving modes are overlapped with each other or the splicing line of one layer partially covers the splicing line of the other layer; determining the layer direction of the small patch of each layer, wherein the composite laminated reflective panel comprises at least four layers, and the number of layers with at least two different layer directions of the small patch in the same layer is at least four layers; preparing the small patch by using unidirectional continuous fiber reinforced prepreg according to the splicing and paving mode of the small patch of each layer and the layer direction of the small patch of each layer; splicing and paving the small patch according to the splicing and paving mode of the small patch of each layer and the layer direction of the small patch of each layer to form a layer with an arbitrary preset curved surface geometry; splicing and paving the small patch on the layer with completed splicing and paving according to the splicing and paving mode of the small patch and the layer direction of the small patch; completing the paving of the preset number of layers to obtain a laminated structure with an arbitrary preset curved surface geometry; curing the obtained laminated structure to obtain a composite laminated reflective panel with quasi-isotropic characteristics in any region, or with quasi-isotropic characteristics in the plane and out of the plane, or with quasi-isotropic characteristics in the plane and out of the plane and minimum bending-torsional coupling effect, and with quasi-zero expansion characteristics in any region.

2. The preparation method of claim 1, wherein the complete layer of the composite laminated reflective panel is: The half-thickness ply of the composite laminated reflector panel is , 3. The preparation method of claim 2, wherein when the half-thickness layer of the composite laminated reflective panel comprises the layer with the layer angle of 0° and the layer with the layer angle of 90°, the splicing and paving mode of the small patch in the two layers with the layer angles of 0° and 90° is the same; ， Among them, the composite laminated reflective panel's first The layer layup angle is , ,and The integer represents the number of layers, and the layer order is from the first layer to the second layer. Layers are stacked sequentially, the first layer... Layer and First The layers are symmetrical layers, and the two layers of the symmetrical layers have the same lay-up angle. Furthermore, the lay-up direction, shape, and splicing method of the small pieces in the two layers of the symmetrical layers are all the same. when the half-thickness layer of the composite laminated reflective panel comprises the layer with the layer angle of 0° and does not comprise the layer with the layer angle of 90°, the splicing and paving mode of the small patch of the layer with the layer angle of 0° is arbitrary and the small patch of the layer can cover the splicing line of the small patch of the adjacent layer or the splicing line of the small patch of the layer can be covered by the small patch of the adjacent layer. In the half-thickness of the composite laminated reflecting panel, the ply angles of the patching and laying combination mode of small pieces of any two layers are respectively and , If the two layers of small tiles are different in the way of splicing and paving, and the splicing lines of the two layers of small tiles cover each other or the splicing lines of one layer of paving partially cover the splicing lines of the other layer of paving; If the two layers of small tiles are laid in the same manner and the joint lines of the two layers of small tiles coincide.

4. The preparation method of claim 2, wherein the small patch is an arbitrary polygonal shape or an arbitrary curvilinear shape.

5. The preparation method of claim 2, wherein the layer direction of the small patch in each layer is alternated. ​ ​ ​ ​ When the half-thickness ply of the composite laminated reflector panel contains both the ply with a ply angle of 0° and the ply with a ply angle of 90°, the ply angle of the small piece of the ply with a ply angle of 0° adjacent to the small piece of the ply with a ply angle of 0° is 90°, and the ply angle of the small piece of the ply with a ply angle of 0° between the small pieces of the ply with a ply angle of 0° is 0°; When the half-thickness ply of the composite laminated reflector panel contains the ply with a ply angle of 0° and does not contain the ply with a ply angle of 90°, the ply direction of the small piece of the ply with a ply angle of 0° corresponds to the ply angle of 0°, and the ply direction rotation is not performed; Within the half-thickness of the composite laminated reflecting panel, the ply angle of any ply is not rotated in the direction of the ply within the ply of small pieces, the ply angle is not rotated in the direction of the ply within the ply of small pieces either. When the half-thickness ply of the composite laminated reflector panel contains both the ply with a ply angle of 0° and the ply with a ply angle of 90°, if the ply direction of the small piece of the ply with a ply angle of 0° does not rotate, the ply direction of the small piece of the ply with a ply angle of 90° also does not rotate; The half-thickness ply of the composite laminated reflector panel contains at most two layers of small pieces of the ply direction non-rotation ply.

6. The preparation method of claim 2, wherein, The layup of any area in the composite laminated reflective panel is It is a half-thickness layup of composite laminated reflective panels. A symmetric set, and a half-thickness ply In this context, the absolute values ​​of the ply angles of any two adjacent ply layers are not equal.

7. The preparation method of claim 2, wherein, The plies in any region of the composite laminated reflector panel are symmetric set of half-thickness plies of the composite laminated reflector panel ​ half-thickness layup obtained from the following steps: The alternative set of all elements , of the symmetric set of the stiffness matrix of the composite laminate panel, Using the stiffness matrix obtained The optimization is performed by optimizing an objective function, Or with the optimized half-thickness lay-up or half-thickness lay-up as half-thickness lay-up .

8. A composite laminated reflector panel, characterized by The composite laminated reflector panel has any preset curved surface geometry, including: At least one small piece of the small piece of the unidirectional continuous fiber reinforced prepreg is prepared, At least four layers of plies are obtained by splicing the small pieces according to the preset ply direction and splicing and laying mode, wherein the number of plies containing at least two different ply directions of small pieces in the same layer is at least four layers, Any two layers of plies have a preset small piece splicing and laying combination mode to ensure that the splicing seams of the small pieces of the plies with different splicing and laying modes overlap each other or the splicing seam of one layer of plies partially covers the splicing seam of another layer of plies; Any ply region has a symmetric and balanced ply mode and has a quasi-zero expansion characteristic; Any ply region satisfies the quasi-isotropic characteristic in the plane, or both in-plane and out-of-plane quasi-isotropic characteristics, or both in-plane and out-of-plane quasi-isotropic characteristics with minimum bending-torsion coupling effect. Wherein, The half-thickness layup of the composite laminated reflective panel is selected from the alternative set. Complete layup For half-thickness layup The symmetric set, the candidate set From the basic angle set Each element passes through The permutation of all elements obtained after the first copy; the basic angle set. any element ,satisfy ,in, , , It is an integer. When the basic angle set is ; Further, when and the set of basic angles is and Further, when and the set of basic angles is and ； In the same ply, the absolute values of the ply angles corresponding to the ply directions of the adjacent small pieces are the same and the signs are opposite, and the ply angles corresponding to the ply directions of the small pieces between the adjacent small pieces are the same.

9. The composite laminated reflector panel of claim 8, wherein, The half-thickness ply of the composite laminated reflector panel is , The complete ply of the composite laminated reflector panel is: ， The first layer of the composite laminated reflecting panel is The layer angle of the first layer is , The first layer and the last layer are symmetrical layers The integer is 1, and the layer sequence is that the first layer to the last layer are sequentially stacked The first layer and the last layer are symmetrical layers The layer angles of the two layers of the symmetrical layers are the same The layer directions, the shapes and the splicing manners of the small pieces of the two layers of the symmetrical layers are the same.

10. The composite laminated reflector panel of claim 9, wherein, In the half-thickness of the composite laminated reflecting panel, the ply angles of the patching and laying combination mode of small pieces of any two layers are respectively and , If the two layers of small tiles are different in the way of splicing and paving, and the splicing lines of the two layers of small tiles cover each other or the splicing lines of one layer of paving layer partially cover the splicing lines of the other layer of paving layer; If the two layers of small tiles are laid in the same way and the two layers of small tiles are laid in the same way and the two layers of small tiles are laid in the same way and the two layers of small tiles are laid in the same way and the two layers of small tiles are laid in the same way and the two In addition, when the half-thickness ply of the composite laminated reflector panel contains both the ply with a ply angle of 0° and the ply with a ply angle of 90°, the splicing and laying modes of the small pieces of the two plies with ply angles of 0° and 90° are the same. When the half-thickness ply of the composite laminated reflecting panel contains the ply with the ply angle of 0° and does not contain the ply with the ply angle of 90°, the splicing manner of the small patches of the ply with the ply angle of 0° is arbitrary and the splicing joint line of the small patches of the ply can be covered by the small patches of the adjacent ply or the splicing joint line of the small patches of the ply can be covered by the small patches of the adjacent ply.

11. The composite laminated reflecting panel according to claim 9, wherein, the small patches are in any polygonal shape or any curvilinear polygonal shape.

12. The composite laminated reflecting panel according to claim 9, wherein, the ply direction of the small patches in each ply is alternated; When the half-thickness ply of the composite laminated reflecting panel contains the ply with the ply angle of 0° and the ply with the ply angle of 90°, the ply angle of the small patch adjacent to the small patch with the ply angle of 0° in the ply with the ply angle of 0° and the ply with the ply angle of 90° is 90°, and the ply angle of the small patch interposed between the small patches with the ply angle of 0° is 0°; When the half-thickness ply of the composite laminated reflecting panel contains the ply with the ply angle of 0° and does not contain the ply with the ply angle of 90°, the ply direction of the small patches of the ply with the ply angle of 0° is 0°, and the ply direction is not alternated; Within the half-thickness of the composite laminated reflecting panel, the ply angle of any ply is not rotated in the direction of the ply within the ply of small pieces, the ply angle is not rotated in the direction of the ply within the ply of small pieces either. When the half-thickness ply of the composite laminated reflecting panel contains the ply with the ply angle of 0° and the ply with the ply angle of 90°, if the ply direction of the small patches of the ply with the ply angle of 0° is not alternated, the ply direction of the small patches of the ply with the ply angle of 90° is also not alternated; The half-thickness ply of the composite laminated reflecting panel contains at most two layers of the ply with the non-alternated ply direction of the small patches.

13. The composite laminated reflecting panel according to claim 9, wherein, The plies in any region of the composite laminated reflector panel are symmetric set of half-thickness plies of the composite laminated reflector panel, and the half-thickness plies where the absolute values of the ply angles of any two adjacent plies are not equal.​ 14. The composite laminated reflecting panel according to claim 9, wherein, The plies in any region of the composite laminated reflector panel are which is a symmetric set of half-thickness plies of the composite laminated reflector panel ​ The half-thickness layup is the symmetric set of all elements in the alternative set , the symmetric set of all elements is the symmetric set of all elements , the optimization is performed according to the following optimization objective function, or the obtained half-thickness layup or half-thickness layup .

Images