Composite module with aperture multiplication function and preparation method thereof

Abstract

The invention provides a caliber multiplication function composite module. The function composite module structurally comprises a thin condensing lens group, a solar cell, a solar cell circuit board, an antenna array, a thermal control layer and a supporting structure. The function composite module is composed of a plurality of thin concentrator solar cells and an antenna array, the concentrator solar cell structure can be adjusted according to the antenna working frequency, and the maximum utilization rate of the aperture is achieved. The layout mode that gaps of antenna arrays are filled with the solar cells is adopted, incident light above the antenna is transferred to the solar cells through the thin condensing lens, an incident light source within the aperture range is fully utilized for power generation, and meanwhile direct heating of the antenna arrays by sunlight is avoided. According to the functional composite module, common-caliber integration of the power generation unit and the electric load is achieved, the efficient photoelectric conversion rate and high-gain radiation are achieved, and the unfolding area and the launching cost of the aircraft are effectively reduced.

Description

Technical Field

[0001] The present invention belongs to the field of spacecraft energy systems, and in particular relates to a composite module with a caliber multiplication function and a preparation method thereof. Background Art

[0002] With the increasing demand for power in equipment payloads, lightweight integration of energy and payloads is an inevitable development trend under limited carrying capacity. The following two methods are usually used to integrate solar cells and antennas.

[0003] Transparent film antennas, metal mesh antennas, etc. are integrated on the light-facing side of solar cells. By increasing the thickness of the transparent conductive film, the width and number of the metal mesh, etc., the radiation efficiency of the antenna is reduced, resulting in a reduction in the light flux incident on the solar cell. There is a mutual restriction between the antenna radiation efficiency and the solar cell power generation efficiency. At the same time, due to the increase in the leakage of high-frequency microwave signals through the grid, the integration of grid antennas and solar cells is mainly concentrated in the L-guide X-band.

[0004] The traditional solar cell and slot antenna, patch antenna, plug-in antenna and other co-surface integration has the problem of solar cells and antennas competing for effective patch area, and in order to prevent AC and DC signal interference, the solar cell and antenna array need to be separated by a certain distance, resulting in low solar cell patch area rate and limited power generation efficiency. Due to the large number of high-frequency antenna arrays and small spacing, this integration method is not suitable for high-frequency antennas above C frequency.

[0005] To solve the above problems, this patent proposes to integrate concentrating solar cells with array antennas, collect light through the upper concentrator, increase the light intensity per unit area of ​​the solar cells, and integrate with waveguide slot antennas, patch antennas, etc. without reducing the light-facing aperture of the solar array, to achieve an array composite of solar cells and antennas with the same size aperture. Summary of the invention

[0006] The present invention discloses a solar cell array and antenna array composite module and a preparation method. The functional composite module is composed of a plurality of thin concentrating solar cells and an antenna array, and a thin concentrating lens is used to transfer the incident light above the antenna to the solar cell, so as to achieve array aperture reuse without reducing the solar cell layout rate and antenna aperture utilization rate.

[0007] A composite module with an aperture multiplication function comprises at least: a thin focusing lens group (S11), a solar cell (S12), a solar cell circuit board (S13), an antenna array (S14), a thermal control layer (S15), and a supporting structure (S16); wherein:

[0008] The solar cell (S12) is arranged on the solar cell circuit board (S13) in the same plane as the radiation patch of the antenna array (S14), and the radiation patch of the antenna array (S14) is sparsely arranged;

[0009] The thin condensing lens group (S11) is pasted on the upper surface of the radiation patch of the solar cell (S12) and the antenna array (S14);

[0010] The thermal control layer (S15) is located on the lower surface of the solar cell circuit board (S13) and the first high-frequency dielectric layer of the antenna array (S14);

[0011] The support structure (S16) is located below the thermal control layer (S15).

[0012] Preferably, the thin condenser lens group (S11) includes at least one thin condenser lens, and each thin condenser lens includes a glass support structure (S21) and an effective Fresnel condenser structure (S22);

[0013] The effective Fresnel focusing structure (S22) is prepared on the glass support structure (S21) by using nano-imprinting technology to form an integrated thin Fresnel focusing lens.

[0014] Preferably, the total thickness of the thin Fresnel focusing lens is not more than 1 mm, and the radius of the light absorption surface is 5 mm-10 mm, which can be adjusted; the focusing multiple of the focusing lens is 100-10 times, which can be adjusted, corresponding to a focusing spot radius of 0.5 mm-3.16 mm.

[0015] Preferably, at least one solar cell (S12) and a solar cell circuit board (S13) form a solar cell assembly (S23); the thin concentrating lens group (S11) and the solar cell assembly (S23) form a thin concentrating solar cell array;

[0016] A plurality of solar cells (S12) are connected in series through an internal circuit of a solar cell circuit board (S13); a back electrode of the solar cell (S12) is attached to a first welding window (S26) of a circuit board through a conductive adhesive, and a front electrode of the solar cell (S12) is welded to a second welding window (S27) of the circuit board through a lead wire; after the series welding, the operating voltage of the solar cell assembly (S23) reaches above 55V;

[0017] In order to meet the requirements of space applications, the adhesive between the solar cell (S12) and the solar cell circuit board (S13) is made of space-grade silicone rubber.

[0018] Preferably, the solar cell circuit board (S13) has a built-in battery series circuit, is designed according to the common-caliber battery array layout, and uses a 35 μm thick rolled copper foil for power transmission;

[0019] The solar cell circuit board (S13) is formed by high-temperature hot pressing of two layers of polyimide film (S24) and copper foil circuit (S25), and the thickness of the polyimide is 50 μm. A first welding window (S26) and a second welding window (S27) are prepared on the solar cell circuit board by laser hollowing, and an antenna array mounting hole (S28) is hollowed out, and the aperture of the opening is more than 1 mm larger than the size of the antenna radiation patch.

[0020] Preferably, the solar cell (S12) is one of gallium arsenide, silicon cell, cadmium telluride, and calcium ion solar cell. The solar cell adopts a polygonal structure, and the radius of the circumscribed circle of the polygonal solar cell is the same as the radius of the focusing spot, which is 1mm-3.16mm. For example, the size of the solar cell with a square structure is 0.7mm-5mm, and a front electrode welding area is reserved on the solar cell, which is led out by wire bonding welding.

[0021] Preferably, the antenna array (S14) is a multi-layer structure, including an antenna radiation patch (S30), a first high-frequency dielectric plate (S31), an antenna floor, a second high-frequency dielectric layer (S32), a feeder (S33), and a radio frequency module (S34); wherein,

[0022] The antenna radiation patch (S30) may be in any shape of square, rectangular, circular or ring;

[0023] The first high-frequency dielectric layer (S31) is a separated unit module, having the same shape as the antenna radiation patch (S30), and each side is about 1 mm away from the boundary of the radiation antenna (S30);

[0024] The antenna thermal control layer (15) also serves as the antenna floor;

[0025] The second high-frequency dielectric layer (S32) is located below the antenna thermal control layer (15);

[0026] The radio frequency module (S34) is fixed on the lower surface of the second high-frequency dielectric layer (S32);

[0027] The feed line (S33) passes through the first high-frequency dielectric layer (S31), the insulating opening on the antenna thermal control layer (15) and the second high-frequency dielectric layer (S32) to be connected to the radio frequency module (S34).

[0028] Preferably, the thermal control layer (S15) is made of 35 μm thick copper foil with a nanographene coating prepared on the surface.

[0029] Preferably, the heat control layer (S15) is connected to the heat radiation enhancement zone (S35) via a heat conduction path (S36).

[0030] The thermal radiation enhancement area (S35) uses high-emissivity coating material SR107 white paint with a thickness of 160μm to improve the heat dissipation efficiency of the conformal module.

[0031] In order to improve the heat exchange capacity between the thermal control layer (S15) and the solar cell circuit board (S13), a contact surface thermal conductive material is added between the two; the interface thermal conductive material adopts any one of high thermal conductivity thermal conductive paste and thermal conductive mud, and the contact surface thermal conductive material has a thermal conductivity of ≥10W / m·K.

[0032] A method for preparing a composite module with a caliber multiplication function, characterized by comprising the following steps:

[0033] Step 1: According to the antenna frequency and power requirements, the size and layout of the radiation patch of the antenna array (S14) and the solar cell (S12) are designed, and the focusing magnification of the thin focusing lens group is designed;

[0034] Step 2: According to the antenna array (S14), a sparsely arranged planar antenna array is prepared;

[0035] Step 3: According to the size and layout design of the solar cell (S12), a common aperture solar cell circuit (S13) board is prepared to avoid interference with the circuit of the antenna array (S14);

[0036] Step 4: The solar cell circuit board (S13) and the antenna array (S14) are combined, and laser engraving is performed on a designated area on the solar cell circuit board (S13) to expose the radiation patch of the antenna array (S14);

[0037] Step 5: preparing a small-sized polygonal solar cell (S12), and using a fine lead welding method to lead out the solar cell electrode;

[0038] Step 6: The solar cell (S12) is pasted on the solar cell circuit board (S13) by means of conductive adhesive, and the welding of the cell electrode and the circuit window of the solar cell circuit board (S13) is completed;

[0039] Step 7: Prepare the thin focusing lens group meeting the requirements of step 1 on glass or organic glass by nanoimprinting and laser micro-engraving technology, wherein the thickness of the lens is less than 1 mm;

[0040] Step 8: The thin focusing lens group is installed above the radiation patch of the solar cell and antenna array (S14) through space-grade silicone rubber.

[0041] Specifically, the thickness of the thin concentrator lens should be ≤1mm, the radius of the light absorption surface of a single thin concentrator lens is 5mm-10mm, and the concentrating efficiency is ≥99%; preferably, the thin concentrator lens is made of glass or glass, and microstructures are processed on it to prepare an ultra-short focal length concentrator to focus the incident sunlight. Multiple areas can be focused under a single concentrator. In particular, the thin concentrator lens is designed based on the core absorption spectrum of a multi-junction gallium arsenide solar cell.

[0042] The solar cell is a square high-efficiency multi-junction gallium arsenide solar cell with a cell size of 0.7mm-5mm. Preferably, the solar cell is designed as a regular polygon, the front electrode of the cell is led out by wire bonding, and the back electrode is directly bonded to the solar cell circuit board by conductive glue.

[0043] The solar cell circuit is formed by hot pressing two layers of polyimide film and copper foil circuit at high temperature, and the substrate is hollowed out by laser in the antenna radiation patch design area.

[0044] The common aperture antenna adopts a patch antenna, including a radiation patch, an antenna floor, a feeder and a radio frequency module. Preferably, the antenna radiation patch is square, an array ring, and has a size of 3mm-16mm. A sparse array layout design is adopted, and the distance between the battery and the antenna is controlled to be more than 1mm. In particular, the antenna operating frequency is in the C-Ka frequency band, and the antenna substrate adopts a multi-layer high-frequency dielectric board.

[0045] Preferably, in order to meet the high and low temperature application environment in space, a thin focusing lens group is adhered to the upper surface of the solar cell and antenna radiation patch through space-grade transparent silicone rubber using standard tooling.

[0046] The thermal control layer used in the co-caliber composite module should be made of high thermal conductivity materials with a thermal conductivity of ≥350W / m·K. Preferably, copper metal materials, diamond materials, graphene materials and various composite materials can be used. In particular, in order to improve the heat exchange capacity between the thermal control layer and the composite module, an interface thermal conductive material should be added between the two, and the contact surface thermal conductive material has a thermal conductivity of ≥10W / m·K.

[0047] The beneficial effects of the present invention are as follows: the ineffective area between the array antenna radiation patches is fully utilized, and the micro-concentrating solar cells are used for common aperture compounding. The light source above the antenna array is concentrated to the upper surface of the solar cell through the concentrating technology, and the light flux within the aperture range is fully utilized. While not affecting the radiation performance of the antenna, the efficiency of the solar cell in utilizing sunlight is improved. Through the compounding of energy and antenna, the deployment area of ​​the satellite is effectively reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 Cross-section of the composite module with caliber multiplication function;

[0049] Figure 2 Diagram of the relative positions of solar cells and antenna radiating elements.

[0050] Figure 3 Thin concentrated solar cell array structure diagram;

[0051] Figure 4 Solar cell circuit board diagram;

[0052] Figure 5 Structural diagram of the co-aperture antenna array and thermal control layer. DETAILED DESCRIPTION

[0053] To further illustrate the content, features and uses of the invention, the present invention is described in more detail below in conjunction with specific embodiments. Examples of the embodiments are shown in the accompanying drawings, in which the same or similar reference numerals throughout represent the same or elements having the same functions. The present invention can be implemented in many different forms, and the embodiments are only used to illustrate the present invention and are not intended to limit the scope of the present invention.

[0054] The present invention discloses a composite module with an aperture multiplication function, which at least comprises: a thin focusing lens group S11, a solar cell S12, a solar cell circuit board S13, an antenna array S14, a thermal control layer S15, and a supporting structure S16; wherein:

[0055] The solar cell S12 is arranged on the solar cell circuit board S13 and is in the same plane as the radiation patch of the antenna array S14. The radiation patch of the antenna array S14 is sparsely arranged.

[0056] The thin focusing lens group S11 is pasted on the upper surface of the radiation patch of the solar cell S12 and the antenna array S14;

[0057] The thermal control layer S15 is located on the lower surface of the solar cell circuit board S13 and the first high-frequency dielectric layer of the antenna array S14;

[0058] The support structure S16 is located below the thermal control layer S15.

[0059] According to an embodiment of the present invention, the thin condenser lens group S11 includes at least one thin condenser lens, and each thin condenser lens includes a glass support structure S21 and an effective Fresnel condenser structure S22;

[0060] The effective Fresnel focusing structure S22 is prepared on the glass support structure S21 by using nano-imprint technology to form an integrated thin Fresnel focusing lens.

[0061] According to one embodiment of the present invention, the total thickness of the thin Fresnel focusing lens is no more than 1 mm, and the radius of the light absorption surface is 5 mm-10 mm, which can be adjusted; the focusing multiple of the focusing lens is 100-10 times, which can be adjusted, corresponding to a focusing spot radius of 0.5 mm-3.16 mm.

[0062] According to one embodiment of the present invention, at least one solar cell S12 and a solar cell circuit board S13 constitute a solar cell assembly S23; the thin concentrating lens group S11 and the solar cell assembly S23 constitute a thin concentrating solar cell array;

[0063] Multiple solar cells S12 are connected in series through the internal circuit of the solar cell circuit board S13; the back electrode of the solar cell S12 is attached to the first welding window S26 of the circuit substrate through conductive adhesive, and the front electrode of the solar cell S12 is welded to the second welding window S27 of the circuit board through a lead wire; after the series welding, the working voltage of the solar cell assembly S23 reaches more than 55V;

[0064] In order to meet the requirements of space applications, the adhesive between the solar cell S12 and the solar cell circuit board S13 is made of space-grade silicone rubber.

[0065] According to one embodiment of the present invention, the solar cell circuit board S13 has a built-in battery series circuit, which is designed according to the common-aperture battery array layout and uses a 35 μm thick rolled copper foil for power transmission;

[0066] The solar cell circuit board S13 is formed by two layers of polyimide film S24 and copper foil circuit S25 through high-temperature hot pressing, and the thickness of polyimide is 50μm; the first welding window S26 and the second welding window S27 are prepared on the solar cell circuit board by laser hollowing, and the antenna array mounting hole S28 is hollowed out, and the aperture of the opening is more than 1mm larger than the size of the antenna radiation patch.

[0067] According to an embodiment of the present invention, the solar cell S12 is one of gallium arsenide, silicon cell, cadmium telluride, and calcium ion solar cell. The solar cell adopts a polygonal structure, and the radius of the circumscribed circle of the polygonal solar cell is the same as the radius of the focusing spot, which is 1mm-3.16mm. For example, the size of the solar cell with a square structure is 0.7mm-5mm, and a front electrode welding area is reserved on the solar cell, which is led out by wire bonding welding.

[0068] According to one embodiment of the present invention, the antenna array S14 is a multi-layer structure, including an antenna radiation patch S30, a first high-frequency dielectric plate S31, an antenna floor, a second high-frequency dielectric layer S32, a feeder S33, and a radio frequency module S34; wherein,

[0069] The antenna radiation patch S30 can be in any shape of square, rectangular, circular or ring;

[0070] The first high-frequency dielectric layer S31 is a separated unit module, which has the same shape as the antenna radiation patch S30, and each side is about 1 mm away from the boundary of the radiation antenna S30;

[0071] The antenna thermal control layer 15 also serves as the antenna floor;

[0072] The second high-frequency dielectric layer S32 is located below the antenna thermal control layer 15;

[0073] The radio frequency module S34 is fixed to the lower surface of the second high frequency dielectric layer S32;

[0074] The feed line S33 passes through the first high-frequency dielectric layer S31, the insulating opening on the antenna thermal control layer 15 and the second high-frequency dielectric layer S32 to be connected to the radio frequency module S34.

[0075] According to an embodiment of the present invention, the thermal control layer S15 is made of 35 μm thick copper foil with a nano-graphene coating prepared on the surface.

[0076] According to one embodiment of the present invention, the heat control layer S15 is connected to the heat radiation enhancement area S35 via a heat conduction path S36.

[0077] The thermal radiation enhancement area S35 uses high-emissivity coating material SR107 white paint with a thickness of 160μm to improve the heat dissipation efficiency of the conformal module.

[0078] In order to improve the heat exchange capacity between the thermal control layer S15 and the solar cell circuit board S13, a contact surface thermal conductive material is added between the two; the interface thermal conductive material adopts any one of high thermal conductivity thermal conductive paste and thermal conductive mud, and the contact surface thermal conductive material has a thermal conductivity of ≥10W / m·K.

[0079] A method for preparing a composite module with a caliber multiplication function, characterized by comprising the following steps:

[0080] Step 1: According to the antenna frequency and power requirements, the size and layout of the radiation patch of the antenna array S14 and the solar cell S12 are designed, and the focusing magnification of the thin focusing lens group is designed;

[0081] Step 2: According to the antenna array S14, a sparsely arranged planar antenna array is prepared;

[0082] Step 3: According to the size and layout design of the solar cell S12, prepare a common aperture solar cell circuit S13 board to avoid interference with the circuit of the antenna array S14;

[0083] Step 4: The solar cell circuit board S13 and the antenna array S14 are combined, and laser engraving is performed on a designated area of ​​the solar cell circuit board S13 to expose the radiation patch of the antenna array S14;

[0084] Step 5: Prepare a small-sized polygonal solar cell S12, and use fine wire welding to lead out the solar cell electrode;

[0085] Step 6: The solar cell S12 is pasted on the solar cell circuit board S13 by means of conductive adhesive, and the battery electrode is welded to the circuit window of the solar cell circuit board S13;

[0086] Step 7: Prepare the thin focusing lens group meeting the requirements of step 1 on glass or organic glass by nanoimprinting and laser micro-engraving technology, wherein the thickness of the lens is less than 1 mm;

[0087] Step 8: The thin focusing lens group is installed above the solar cell and antenna array S14 radiation patch through space-grade silicone rubber.

[0088] Example 1

[0089] The present invention proposes a composite module with a caliber multiplication function. Figure 1 As shown, the aperture multiplication function composite module mainly includes: a thin focusing lens group S11, a solar cell S12, a solar cell circuit board S13, an antenna array S14, a thermal control layer S15, and a support structure S16.

[0090] The solar cell S12 is arranged on the solar cell circuit board S13 and is in the same plane as the radiation patch of the antenna array S14. The radiation patch of the antenna array S14 is sparsely arranged.

[0091] The thin focusing lens group S11 is pasted on the upper surface of the radiation patch of the solar cell S12 and the antenna array S14;

[0092] The thermal control layer S15 is located on the lower surface of the solar cell circuit board S13 and the first high-frequency dielectric layer of the antenna array S14;

[0093] The support structure S16 is located below the thermal control layer S15.

[0094] The thin focusing lens group S11 is a square structure with a size of 10 cm×10 cm, including 25 focusing areas. The structure is designed according to the effective spectrum absorption range of the solar cell S12 so that the sunlight passing through the light-absorbing surface is focused on the focusing spot.

[0095] The thin condenser lens group S11 includes a plurality of thin condenser lenses, each of which includes a glass support structure S21 and an effective Fresnel condenser structure S22. The effective Fresnel condenser structure S22 is prepared on the glass city structure S21 by nano-imprinting technology to form an integrated micro condenser lens group.

[0096] The total thickness of the thin condenser lens is 1mm, the radius of the light absorption surface of a single thin condenser lens is 10mm, and the radius of the focusing spot after 100 times focusing is 1mm.

[0097] A plurality of solar cells S12 and a solar cell circuit board S13 form a solar cell array S23.

[0098] The thin concentrating lens group S11 and the solar cell array S23 form a thin concentrating solar cell array. Figure 3 Shown is a structural diagram of a thin concentrating solar cell array.

[0099] In particular, in order to meet the high and low temperature application environment in space, a thin focusing lens group is adhered to the upper surface of the radiation patch of the solar cell S12 and the antenna array S14 through space-grade transparent silicone rubber using standard tooling.

[0100] The solar cell S12 is a multi-junction gallium arsenide solar cell with a square structure and a size of 1.4 mm×1.4 mm. A front electrode welding area is reserved on the upper surface of the solar cell with a size of 0.2 mm×0.2 mm, which is led out by wire bonding.

[0101] like Figure 4 The solar cell circuit board S13 is shown in FIG. It is made of double-layer polyimide S24 and 35μm copper foil circuit by high temperature hot pressing, and the thickness of polyimide is 50μm.

[0102] In particular, the copper foil circuit includes a line S25 and a first welding window S26 and a second welding window S27. The first welding window S26 and the second welding window S27 are formed by removing the polyimide layer by laser hollowing.

[0103] In particular, an antenna array mounting hole (S28) is hollowed out on the solar cell circuit board S13, and the aperture is about 2 mm larger than the size of the antenna radiation patch.

[0104] The solar cell circuit board S13 is designed according to the common aperture cell array layout and uses 35 μm thick rolled copper foil for power transmission.

[0105] Multiple solar cells S12 are connected in series through the internal circuit of the solar cell circuit board S13. The back electrode of the solar cell S12 is attached to the first welding window S26 of the circuit board through conductive glue, and the front electrode of the solar cell S12 is welded to the second welding window S27 of the circuit board through a lead wire. After the series welding, the working voltage of the solar cell array S23 reaches more than 55V.

[0106] like Figure 5 The common aperture antenna array S14 is a multi-layer structure, including an antenna radiation patch S30, a first high-frequency dielectric plate S31, an antenna floor, a second high-frequency dielectric layer S32, a feeder S33, and a radio frequency module S34.

[0107] The antenna radiation patch S30 is a square patch, the square patch antenna array size is 10 mm, a sparse array layout design is adopted, the antenna radiation patch spacing is 20 mm, and the distance between the solar cell S12 and the antenna radiation patch S30 is about 6 mm.

[0108] The first high-frequency dielectric layer S31 is a separate unit module, located between the antenna floor and the antenna radiation patch S30, and the first high-frequency dielectric layer S31 is larger than the antenna radiation patch S30 by more than 1 mm. The first high-frequency dielectric layer S31 uses Rogers RO4350 dielectric board with a dielectric constant between 3.5-4.

[0109] The line floor is also the thermal control layer S15 of the composite module, using a 35 μm thick copper foil. In particular, a nanographene coating can be prepared on the surface of the copper foil of the thermal control layer S15.

[0110] The thermal control layer S15 is provided with the first high-frequency dielectric layer S31 and the solar cell circuit board S13. In particular, in order to improve the heat exchange capacity between the thermal control layer S15 and the solar cell circuit board S13, a contact surface thermal conductive material is added between the two. Preferably, the interface thermal conductive material can be a high thermal conductivity thermal conductive paste, thermal conductive mud, etc., and the contact surface thermal conductive material has a thermal conductivity of ≥10W / m·K.

[0111] The second high-frequency dielectric layer S32 is located below the antenna thermal control layer 15 and is made of a Rogers RO4350 dielectric board with a dielectric constant between 3.5 and 4.

[0112] The radio frequency module S34 is fixed to the lower surface of the second high-frequency dielectric layer S32.

[0113] The feed line S33 passes through the first high-frequency dielectric layer S31, the insulating opening on the antenna thermal control layer 15 and the second high-frequency dielectric layer S32 to be connected to the radio frequency module S34.

[0114] The thermal control layer S15 is connected to the thermal radiation enhancement area S35 through a heat conduction path S36. The thermal radiation enhancement area S35 is located below the second high-frequency dielectric layer S32 and is spaced apart from the RF module S34. In particular, the thermal radiation enhancement area S35 uses a high-emissivity coating material SR107 white paint with a thickness of 160 μm to improve the heat dissipation efficiency of the conformal module.

[0115] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

Claims

1. A composite module with caliber multiplication function, characterized in that: The module at least comprises: a thin focusing lens group (S11), a solar cell (S12), a solar cell circuit board (S13), an antenna array (S14), a thermal control layer (S15), and a supporting structure (S16); wherein, The solar cell (S12) is arranged on the solar cell circuit board (S13) in the same plane as the radiation patch of the antenna array (S14), and the radiation patch of the antenna array (S14) is sparsely arranged; The thin condensing lens group (S11) is pasted on the upper surface of the radiation patch of the solar cell (S12) and the antenna array (S14); The thermal control layer (S15) is located on the lower surface of the solar cell circuit board (S13) and the first high-frequency dielectric layer of the antenna array (S14); The support structure (S16) is located below the thermal control layer (S15).

2. The aperture multiplication function composite module according to claim 1, characterized in that: The thin condenser lens group (S11) includes at least one thin condenser lens, and each thin condenser lens includes a glass support structure (S21) and an effective Fresnel condenser structure (S22); the effective Fresnel condenser structure (S22) is prepared on the glass support structure (S21) by nano-imprinting technology to form an integrated thin Fresnel condenser lens.

3. The aperture multiplication function composite module according to claim 1, characterized in that: The total thickness of the thin Fresnel condenser lens is no more than 1mm, and the radius of the light absorption surface is 5mm-10mm, which can be adjusted; the focusing multiple of the condenser lens is 100-10 times, which can be adjusted, corresponding to a focusing spot radius of 0.5mm-3.16mm.

4. The aperture multiplication function composite module according to claim 1, characterized in that: At least one solar cell (S12) and a solar cell circuit board (S13) form a solar cell assembly (S23); the thin concentrating lens group (S11) and the solar cell assembly (S23) form a thin concentrating solar cell array; A plurality of solar cells (S12) are connected in series through an internal circuit of a solar cell circuit board (S13); a back electrode of the solar cell (S12) is attached to a first welding window (S26) of a circuit board through a conductive adhesive, and a front electrode of the solar cell (S12) is welded to a second welding window (S27) of the circuit board through a lead wire; after the series welding, the operating voltage of the solar cell assembly (S23) reaches above 55V; In order to meet the requirements of space applications, the adhesive between the solar cell (S12) and the solar cell circuit board (S13) is made of space-grade silicone rubber.

5. The aperture multiplication function composite module according to claim 1, characterized in that: The solar cell circuit board (S13) has a built-in battery series circuit, which is designed according to the common-aperture battery array layout and uses a 35 μm thick rolled copper foil for power transmission; The solar cell circuit board (S13) is formed by high-temperature hot pressing of two layers of polyimide film (S24) and copper foil circuit (S25), and the thickness of the polyimide is 50 μm. A first welding window (S26) and a second welding window (S27) are prepared on the solar cell circuit board by laser hollowing, and an antenna array mounting hole (S28) is hollowed out, and the aperture of the opening is more than 1 mm larger than the size of the antenna radiation patch.

6. The aperture multiplication function composite module according to claim 1, characterized in that: The solar cell (S12) is one of gallium arsenide, silicon cell, cadmium telluride, and calcium ion solar cell. The solar cell adopts a polygonal structure. The radius of the circumscribed circle of the polygonal solar cell is the same as the radius of the focusing spot, which is 1mm-3.16mm.

7. The aperture multiplication function composite module according to claim 1, characterized in that: The antenna array (S14) is a multi-layer structure, including an antenna radiation patch (S30), a first high-frequency dielectric plate (S31), an antenna floor, a second high-frequency dielectric layer (S32), a feeder (S33), and a radio frequency module (S34); wherein, The antenna radiation patch (S30) may be in any shape of square, rectangular, circular or ring; The first high-frequency dielectric layer (S31) is a separated unit module, having the same shape as the antenna radiation patch (S30), and each side is about 1 mm away from the boundary of the radiation antenna (S30); The antenna thermal control layer (15) also serves as the antenna floor; The second high-frequency dielectric layer (S32) is located below the antenna thermal control layer (15); The radio frequency module (S34) is fixed on the lower surface of the second high-frequency dielectric layer (S32); The feed line (S33) passes through the first high-frequency dielectric layer (S31), the insulating opening on the antenna thermal control layer (15) and the second high-frequency dielectric layer (S32) to be connected to the radio frequency module (S34).

8. The aperture multiplication function composite module according to claim 1, characterized in that: The thermal control layer (S15) is made of a 35 μm thick copper foil with a nanographene coating prepared on the surface.

9. The aperture multiplication function composite module according to claim 1, characterized in that: The heat control layer (S15) is connected to the heat radiation enhancement area (S35) via a heat conduction path (S36). The thermal radiation enhancement area (S35) uses high-emissivity coating material SR107 white paint with a thickness of 160μm to improve the heat dissipation efficiency of the conformal module; In order to improve the heat exchange capacity between the thermal control layer (S15) and the solar cell circuit board (S13), a contact surface thermal conductive material is added between the two; the interface thermal conductive material adopts any one of high thermal conductivity thermal conductive paste and thermal conductive mud, and the contact surface thermal conductive material has a thermal conductivity of ≥10W / m·K.

10. A method for preparing a composite module with caliber multiplication function as claimed in any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1: According to the antenna frequency and power requirements, the size and layout of the radiation patch of the antenna array (S14) and the solar cell (S12) are designed, and the focusing magnification of the thin focusing lens group is designed; Step 2: According to the antenna array (S14), a sparsely arranged planar antenna array is prepared; Step 3: According to the size and layout design of the solar cell (S12), a common aperture solar cell circuit (S13) board is prepared to avoid interference with the circuit of the antenna array (S14); Step 4: The solar cell circuit board (S13) and the antenna array (S14) are combined, and laser engraving is performed on a designated area on the solar cell circuit board (S13) to expose the radiation patch of the antenna array (S14); Step 5: preparing a small-sized polygonal solar cell (S12), and using a fine lead welding method to lead out the solar cell electrode; Step 6: The solar cell (S12) is pasted on the solar cell circuit board (S13) by means of conductive adhesive, and the welding of the cell electrode and the circuit window of the solar cell circuit board (S13) is completed; Step 7: Prepare the thin focusing lens group meeting the requirements of step 1 on glass or organic glass by nanoimprinting and laser micro-engraving technology, wherein the thickness of the lens is less than 1 mm; Step 8: The thin focusing lens group is installed above the radiation patch of the solar cell and antenna array (S14) through space-grade silicone rubber.

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