A spacecraft solar panel integrated metasurface array antenna

Abstract

This invention discloses a metasurface array antenna integrated with a spacecraft solar panel. The array antenna includes: a stacked unit array dielectric substrate, an I-shaped feed network dielectric substrate, a bottom feed network dielectric substrate, and a solar panel. The unit array dielectric substrate includes multiple arrayed substrate integrated cavity units and a metasurface structure located at the center of the aperture surface of the substrate integrated cavity. The metasurface structure includes several periodically spaced rectangular metal patches. The I-shaped feed network dielectric substrate includes multiple I-shaped feed network units that feed the unit array dielectric substrate. The bottom feed network dielectric substrate feeds energy into the multiple I-shaped feed network units. The solar panel is isolated from the array antenna by a metal ground plane and is responsible for collecting the illumination energy from the back of the array antenna. By integrating the broadband high-gain array antenna with the solar panel, performance improvement is effectively achieved.

Description

Technical Field

[0001] This invention belongs to the field of antenna technology, and more specifically, relates to an integrated metasurface array antenna for spacecraft solar panels. Background Technology

[0002] With the rapid development of information and communication technologies, satellite communication technology has also made significant progress. As the front end of a wireless communication system, the antenna is responsible for transmitting and receiving signals, largely determining the overall system performance. However, it also occupies a considerable amount of space resources in spacecraft. To save space and reduce weight, the integrated design of solar panels and antennas can achieve lightweighting and integration. When mounted on spacecraft, this allows for efficient use of valuable space resources and reduced launch costs. Therefore, new demands are being placed on high-performance, easily integrated solar panel antennas.

[0003] As a type of substrate integrated waveguide antenna, substrate integrated cavity antennas offer advantages over other antenna structures, including high gain, low profile, effective surface wave suppression, and ease of integration. Past research on substrate integrated cavity antennas has primarily focused on improving aperture efficiency by introducing parasitic patches of different shapes and arrangements onto the aperture surface to achieve high-gain linear and circular polarization radiation. However, the electric field distribution on the aperture surface limits the antenna bandwidth, which to some extent restricts its application in the communications field. In recent years, metasurface structures have attracted widespread attention from researchers. Using metasurfaces as radiators enables broadband antenna designs, but achieving high gain remains a challenge.

[0004] In summary, existing antenna designs suffer from the problem of simultaneously achieving both broadband and high gain; furthermore, they also present difficulties in coplanar integration with solar panels. Summary of the Invention

[0005] In view of the shortcomings of related technologies, the purpose of this invention is to provide a metasurface array antenna integrated with a spacecraft solar panel, which aims to solve the problem that it is difficult to achieve both broadband and high gain in the antenna design of the prior art; at the same time, there is also the difficulty of coplanar integration with the solar panel.

[0006] To achieve the above objectives, the present invention provides a spacecraft solar panel integrated metasurface array antenna, comprising: a stacked unit array dielectric substrate, an I-shaped feed network dielectric substrate, a bottom feed network dielectric substrate, and a solar panel;

[0007] The unit array dielectric substrate serves as the front side of the array antenna, and includes multiple substrate integrated cavity units arranged in an array. Each substrate integrated cavity unit includes a substrate integrated cavity surrounded by metal through holes and a metasurface structure located at the center of the aperture surface of the substrate integrated cavity. The metasurface structure includes several rectangular metal patches arranged at periodic intervals.

[0008] At low frequencies, the metasurface structure acts as the main radiator and operates in the fundamental mode; at high frequencies, the substrate integrated cavity acts as the main radiator and operates in the higher-order mode. The metasurface structure is used to change the higher-order mode distribution of the substrate integrated cavity so that its maximum radiation direction is along the normal direction of the substrate integrated cavity. The resonant frequencies corresponding to the two operating modes do not coincide.

[0009] The I-shaped feed network dielectric substrate includes multiple I-shaped feed network units, each of which is surrounded by a first substrate integrated waveguide formed by metal vias. The first substrate integrated waveguide is used to feed the substrate integrated cavity unit.

[0010] The underlying feed network dielectric substrate includes a second substrate integrated waveguide surrounded by metal vias, the second substrate integrated waveguide being used to feed energy into a plurality of the I-shaped feed network units;

[0011] The solar panel is isolated from the array antenna by a metal floor on the underlying feed network dielectric substrate. The solar panel is responsible for collecting the illumination energy from the back of the array antenna and powering the spacecraft connected to the array antenna.

[0012] Optionally, solar cells are periodically arranged on the solar panel;

[0013] The energy harvesting direction of the solar panel is opposite to the radiation direction of the array antenna.

[0014] Optionally, the diagonal of the rectangular metal patch in the metasurface structure is at 45° to the diagonal of the aperture face of the substrate integrated cavity.

[0015] Optionally, adjacent substrate integrated cavities on the unit array dielectric substrate share a row of metal vias.

[0016] Optionally, the unit array dielectric substrate, the I-shaped power supply network dielectric substrate, and the bottom power supply network dielectric substrate all include an upper metal layer on the upper surface and a lower metal layer on the lower surface.

[0017] The lower metal layer of the substrate integrated cavity unit and the upper metal layer of the I-shaped power supply network unit are respectively provided with a first power supply gap that fits together. The first power supply gap is used to feed the energy of the I-shaped power supply network unit into the substrate integrated cavity unit.

[0018] The lower metal layer of the I-shaped feed network unit and the upper metal layer of the second integrated waveguide are respectively provided with a second feed gap that fits into each other. The second feed gap is used to feed the energy of the second substrate integrated waveguide into the I-shaped feed network unit.

[0019] The lower metal layer of the underlying feed network dielectric substrate includes a coplanar waveguide transition structure for feeding external energy into the second substrate integrated waveguide.

[0020] The lower metal layer of the underlying power supply network dielectric substrate serves as a metal floor, which is bonded to the solar panel.

[0021] Optionally, a first feeding slot is provided at the center of the lower metal layer of one of the substrate integrated cavity units; four waveguide longitudinal slots are opened at the end of the I-shaped waveguide of the I-shaped feeding network unit as the first feeding slots, and four first feeding slots are provided on the upper metal layer of one of the I-shaped feeding network units.

[0022] Optionally, a second feed slot is provided on the lower metal layer of one of the I-shaped feed network units; a waveguide longitudinal slot is opened at the end of the power divider structure of the bottom feed network dielectric substrate as a second feed slot, and four second feed slots are provided on the upper metal layer of one of the second integrated waveguides.

[0023] Optionally, the long side of the second feed slot in the I-shaped feed network unit is parallel to the propagation direction of the adjacent waveguide; the long side of the first feed slot in the I-shaped feed network unit is parallel to the propagation direction of the adjacent waveguide; by adjusting the distance between the first feed slot and the second feed slot and the waveguide wall, the antenna achieves impedance matching.

[0024] Optionally, the first substrate integrated waveguide and the second substrate integrated waveguide further include multiple impedance-adjusting vias and multiple offset waveguides;

[0025] The impedance adjustment via and offset waveguide are used to adjust impedance matching.

[0026] Optionally, the substrate integrated cavity is a rectangular cavity.

[0027] Compared with the prior art, the above-described technical solutions conceived in this invention can achieve the following beneficial effects:

[0028] 1. This invention provides a spacecraft solar panel integrated metasurface array antenna, comprising a unit array dielectric substrate, an I-shaped feed network dielectric substrate, and a bottom feed network dielectric substrate. The unit array dielectric substrate includes multiple substrate integrated cavity units arranged in an array. By adding a metasurface structure to the aperture surface of the substrate integrated cavity, not only are additional radiation modes introduced at low frequencies, increasing the operating bandwidth, but the field distribution of the higher-order mode radiation modes of the substrate integrated cavity is also modulated at high frequencies through the metasurface structure. A rectangular metal patch cuts off the reverse magnetic current on the aperture surface of the substrate integrated cavity, changing the higher-order mode distribution of the substrate integrated cavity, so that its maximum radiation direction is along the normal direction of the substrate integrated cavity. By combining the two radiation modes, the bandwidth of the antenna is effectively expanded. At low frequencies, the metasurface of the substrate integrated cavity unit, along with the feed slot and the substrate integrated cavity, forms a back-cavity slot-coupled feed metasurface radiation mode. Compared to traditional metasurface antennas, this effectively improves gain and reduces inter-element coupling during array deployment. Simultaneously, the substrate integrated cavity operates in a higher-order mode, resulting in a larger radiating aperture. Therefore, the spacecraft solar panel integrated metasurface array antenna of this invention achieves higher gain compared to traditional substrate integrated cavity array antennas. Since the two high-gain radiation modes enable the antenna to achieve good radiation performance over a wide bandwidth, the resonant frequencies of the two modes are effectively separated through reasonable design of the metasurface unit and cavity dimensions, achieving broadband high-gain radiation.

[0029] 2. This invention provides a spacecraft solar panel integrated metasurface array antenna. In the surface structure, the diagonal of the rectangular metal patch is at 45° with the diagonal of the aperture face of the substrate integrated cavity. Under the same size, the electric length of the induced current on the metasurface structure is increased, the size of the metasurface structure is reduced, and the shielding of the electric field on the aperture face at high frequencies is reduced.

[0030] 3. This invention provides a spacecraft solar panel integrated metasurface array antenna. The adjacent substrate integrated cavities on the unit array dielectric substrate share a row of metal through holes, which minimizes the array spacing, effectively reduces the array size and reduces the processing difficulty.

[0031] 4. This invention provides a spacecraft solar panel integrated metasurface array antenna. In the prior art, solar panels are usually placed outside the array antenna, which has the problems of large size and interference coupling. This invention reduces the interference coupling between the two by placing the solar panel on the back of the array antenna and is isolated by a metal floor, and makes the best use of aperture and space. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the structure of a spacecraft solar panel integrated metasurface array antenna provided in an embodiment of the present invention;

[0033] Figure 2 This is a top view of the cell array dielectric substrate provided in an embodiment of the present invention;

[0034] Figure 3 This is a top view of the I-shaped power supply network dielectric substrate provided in an embodiment of the present invention;

[0035] Figure 4 This is a top view of the underlying power supply network dielectric substrate provided in an embodiment of the present invention;

[0036] Figure 5 This is a top view of the solar panel provided in an embodiment of the present invention;

[0037] Figure 6 This is a schematic diagram of the return loss and gain curves of an integrated metasurface array antenna for a spacecraft solar panel, provided in an embodiment of the present invention.

[0038] In the above figures, 1 is a unit array dielectric substrate, 2 is an I-shaped feed network dielectric substrate, 3 is a bottom feed network dielectric substrate, 4 is a solar panel, 10 is a substrate integrated cavity unit, 101 is a substrate integrated cavity, 102 is a metasurface structure, 103 is a rectangular metal patch, 104 is a 2×2 antenna subarray, 20 is an I-shaped feed network unit, 201 is a first feed slot, 202 is a first impedance adjustment via, 203 is a first substrate integrated waveguide, 204 is a second impedance adjustment via, 205 is an offset waveguide at the waist of the I-shaped structure, 206 is other impedance adjustment vias, 207 is offset waveguides in the upper and lower halves of the I-shaped structure, 301 is a second feed slot, 302 is a third impedance adjustment via, 303 is a fourth impedance adjustment via, 304 is a second substrate integrated waveguide, 305 is a coplanar waveguide transition structure, and 401 is a solar cell. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0040] The following description, in conjunction with a preferred embodiment, illustrates the content involved in the above embodiments.

[0041] like Figures 1-4 As shown, a spacecraft solar panel integrated metasurface array antenna includes: a stacked unit array dielectric substrate 1, an I-shaped feed network dielectric substrate 2, a bottom feed network dielectric substrate 3, and a solar panel 4.

[0042] The unit array dielectric substrate 1 serves as the front side of the array antenna and includes multiple substrate integrated cavity units 10 arranged in an array. Each substrate integrated cavity unit 10 includes a substrate integrated cavity 101 surrounded by metal through holes and a metasurface structure 102 located at the center of the aperture surface of the substrate integrated cavity 101. The metasurface structure 102 includes several rectangular metal patches 103 arranged periodically at intervals.

[0043] At low frequencies, the metasurface structure 102 acts as the main radiator, operating in the fundamental mode. At high frequencies, the substrate integrated cavity 101 acts as the main radiator, operating in the higher-order mode. The metasurface structure 102 is used to change the higher-order mode distribution of the substrate integrated cavity 101, so that its maximum radiation direction is along the normal direction of the substrate integrated cavity 101. The resonant frequencies corresponding to the two operating modes do not coincide.

[0044] The I-shaped feed network dielectric substrate 2 includes a plurality of I-shaped feed network units 20. Each I-shaped feed network unit 20 is surrounded by a first substrate integrated waveguide 203 formed by metal vias. The first substrate integrated waveguide 203 is used to feed the substrate integrated cavity unit 10.

[0045] The underlying feed network dielectric substrate 3 includes a second substrate integrated waveguide 304 surrounded by metal vias, which is used to feed energy into a plurality of the I-shaped feed network units 20.

[0046] The solar panel 4 is isolated from the array antenna by a metal ground plane on the underlying feed network dielectric substrate 3. The solar panel 4 is responsible for collecting the illumination energy from the back of the array antenna and powering the spacecraft connected to the array antenna.

[0047] This embodiment presents a spacecraft solar panel integrated metasurface array antenna, constructed by arranging multiple substrate integrated cavity units 10 in an array. Within each substrate integrated cavity unit 10, a substrate integrated cavity 101 is combined with a metasurface structure 102. Multimode resonance theory is used to achieve a broadband, high-gain antenna design suitable for various frequency scenarios. The unit array dielectric substrate 1 serves as the front of the array antenna, while a solar panel 4 is positioned on the back. By integrating the solar panel with the array antenna, it collects the illumination energy from the back of the antenna to power the spacecraft. This achieves integrated high-performance array antenna and solar panel, while simultaneously saving space resources and reducing launch costs, enabling efficient utilization of space resources.

[0048] At low frequencies, metasurface structure 102 acts as the main radiator, operating in the fundamental mode TM. 10In this mode; in a high-frequency environment, the substrate integrated cavity 101 acts as the main radiator, operating in TM mode. 211 In this mode, the metasurface structure 102 alters the high-order mode distribution of the substrate integrated cavity 101, causing its maximum radiation direction to align with the normal direction of the substrate integrated cavity 101. Specifically, the rectangular metal patch 103 in the metasurface structure 102 cuts off the reverse magnetic current on the aperture surface of the substrate integrated cavity 101, changing the high-order mode distribution of the substrate integrated cavity 101, thereby causing its maximum radiation direction to align with the normal direction of the substrate integrated cavity 101. On one hand, energy resonates within the substrate integrated cavity 101, forming a high-order mode radiation pattern. The metasurface structure 102 adjusts the field distribution of high-order modes within the substrate integrated cavity 101. Simultaneously, the metasurface structure 102, composed of the rectangular metal patch 103, also introduces the fundamental mode radiation pattern of the rectangular metal patch 103 as a radiator. The arrangement of the rectangular metal patches 103 in the metasurface structure 102 and the shape of the formed metasurface structure 102 are not limited. The metasurface structure 102 composed of periodically arranged rectangular metal patches 103 is located at the center of the aperture surface of the substrate integrated cavity 101.

[0049] Since the higher-order mode resonant frequencies of the substrate integrated cavity 101 and the fundamental mode resonant frequency of the metasurface structure 102 do not coincide, and the interval between the higher-order mode resonant frequencies and the fundamental mode resonant frequencies is adjustable, the effect of widening the bandwidth can be achieved by adjusting the interval between the resonant frequencies of the two modes. Because the substrate integrated cavity 101 operates at high frequencies, its radiation aperture is larger than when operating in the fundamental mode, thus achieving higher gain. Therefore, by rationally designing the dimensions of the metasurface structure 102 and the substrate integrated cavity 101, the resonant frequencies of the two modes are effectively separated, achieving broadband high-gain radiation.

[0050] By adding a metasurface structure to the aperture surface of the substrate integrated cavity, it not only functions as the primary radiator at low frequencies but also modulates the field distribution of higher-order mode radiation modes at high frequencies. Combining these two radiation modes effectively expands the antenna bandwidth. Through the rational design of the metasurface structure and the dimensions of the substrate integrated cavity, high-gain radiation is achieved while simultaneously expanding the antenna bandwidth.

[0051] like Figure 2 As shown, optionally, rectangular metal patches 103 are arranged in a 3×3 array in a periodic manner, and an additional metal patch is introduced at each of the four corners to form a metasurface structure 102, which is used to increase the aperture of the metasurface structure. The diagonal of the rectangular metal patches 103 in the metasurface structure forms a 45° angle with the aperture face diagonal of the substrate integrated cavity 101.

[0052] The shape of the metasurface structure 102 can be rectangular, circular, or other irregular shapes, for example, such as... Figure 2 As shown, the diagonal of the rectangular metal patch 103 forms a 45° angle with the diagonal of the aperture surface of the substrate integrated cavity 101. These patches are arranged along the two diagonals of the upper surface of the substrate integrated cavity 101, defining the rectangular range corresponding to the metasurface structure 102. Within this range, several rectangular metal patches 103 are periodically arranged at intervals, ultimately forming the metasurface structure 102 as shown. When transmitting current, the current travels along the diagonal of the rectangular metal patch 103 in the metasurface structure 102. Therefore, the path length of the current on the metasurface structure 102 can be increased. Simultaneously, with the same current path length, the size of the metasurface structure is reduced, thus decreasing the shielding of the electric field on the aperture surface of the substrate integrated cavity 101 at high frequencies.

[0053] Continue to refer to Figure 2 In this unit array dielectric substrate 1, adjacent substrate integrated cavities 101 share a row of metal vias. This minimizes the array spacing, effectively reducing the array size and lowering the processing difficulty.

[0054] refer to Figure 5 As shown, solar panels 4 have periodically arranged solar cells 401 on them. The energy collection direction of the solar panels 4 is opposite to the radiation direction of the array antenna to avoid the array antenna from blocking sunlight.

[0055] Furthermore, the spacecraft solar panel integrated metasurface array antenna includes a unit array dielectric substrate, an I-shaped feed network dielectric substrate, and a bottom feed network dielectric substrate arranged in a tightly stacked manner. The bottom feed network dielectric substrate contains a coplanar waveguide transition structure that feeds external energy into the bottom feed network dielectric substrate, and then transmits the energy to the I-shaped feed network dielectric substrate through feed gaps. The I-shaped feed network dielectric substrate then transmits the energy to the unit array dielectric substrate through feed gaps. Through the power divider structure and the number of feed gaps in the dielectric substrate, a one-to-many energy feeding is achieved.

[0056] For details, please refer to Figure 1 , Figure 3 and Figure 4 The unit array dielectric substrate 1, the I-shaped power supply network dielectric substrate 2, and the bottom power supply network dielectric substrate 3 all include an upper metal layer on the upper surface and a lower metal layer on the lower surface.

[0057] The lower metal layer of the substrate integrated cavity unit 10 and the upper metal layer of the I-shaped power supply network unit 20 are respectively provided with a first power supply gap 201 that is attached to each other. The first power supply gap 201 is used to feed the energy of the I-shaped power supply network unit 20 into the substrate integrated cavity unit 10.

[0058] The lower metal layer of the I-shaped feed network unit 20 and the upper metal layer of the second integrated waveguide 304 are respectively provided with a second feed gap 301 that is attached to each other. The second feed gap 301 is used to feed the energy of the second substrate integrated waveguide 301 (bottom feed network dielectric substrate 3) into the I-shaped feed network unit 20.

[0059] The lower metal layer of the bottom feed network dielectric substrate 3 includes a coplanar waveguide transition structure 305, which is used to feed external energy into the second substrate integrated waveguide 301.

[0060] The lower metal layer of the underlying power supply network dielectric substrate 3 serves as a metal floor, which is bonded to the solar panel 4.

[0061] In this embodiment, a first feed slot 201 is provided at the center of the lower metal layer of one of the substrate integrated cavity units 10; four waveguide longitudinal slots are opened at the end of the I-shaped waveguide of the I-shaped feed network unit 20, serving as the first feed slots 201; four first feed slots 201 are provided on the upper metal layer of one of the I-shaped feed network units 20. A second feed slot 301 is provided on the lower metal layer of one of the I-shaped feed network units 20; a waveguide longitudinal slot is opened at the end of the power divider structure of the bottom feed network dielectric substrate 3, serving as the second feed slot 301; four second feed slots 301 are provided on the upper metal layer of one of the second integrated waveguides 304. The shape of the feed slot can be rectangular, I-shaped, butterfly-shaped, etc., and a rectangle is preferred in this embodiment.

[0062] Specifically, such as Figure 3 As shown, in the I-shaped feed network unit 20, the "I-shaped" waveguide serves as a power divider structure. In the I-shaped feed network unit 20, two first feed slots 201 are located on both sides of the bottommost part of the upper half of the "I-shaped" waveguide, and two other first feed slots 201 are located on both sides of the bottommost part of the lower half of the "I-shaped" waveguide. In the I-shaped feed network unit 20, one second feed slot 301 is located on one side of the waist of the "I-shaped" waveguide. The second feed slots 301 in two adjacent I-shaped feed network units 20 are located on different sides of the waist of the "I-shaped" waveguide.

[0063] Specifically, such as Figure 4 As shown, the "I-shaped" waveguide in the second integrated waveguide 304 serves as a power divider structure; the four second feed gaps 301 in the second integrated waveguide 304 are respectively located on both sides of the uppermost part of the upper half and both sides of the lower half of the "I-shaped" waveguide.

[0064] The above structure constitutes a 1-to-4 feeding structure for the I-shaped power supply network unit 20 to the substrate integrated cavity unit 10, and a 1-to-4 feeding structure for the bottom power supply network dielectric substrate 3 to the I-shaped power supply network unit 20. It simplifies the design difficulty of the power supply network in a limited space, avoids the loss problem caused by complex power supply structures, and effectively realizes the broadband design of the power supply network.

[0065] Furthermore, such as Figure 3 and Figure 4 As shown, the second feed slot 301 in the I-shaped feed network unit 20 has its long side parallel to the waveguide propagation direction; the first feed slot 201 in the I-shaped feed network unit 20 is attached to the center position of the lower surface of the substrate integrated cavity 10, and its long side is parallel to the waveguide propagation direction; by adjusting the distance between the first feed slot 201 and the second feed slot 301 and the waveguide wall, the antenna achieves impedance matching.

[0066] The first feed slot 201 and the second feed slot 301 are at a certain distance from the waveguide walls of the first substrate integrated waveguide 203 and the second substrate integrated waveguide 304. Adjusting the distance enables the antenna to achieve impedance matching, thereby enabling the antenna to be in a high-gain radiation mode.

[0067] Furthermore, at low frequencies, the metasurface structure 102 of the substrate integrated cavity unit 10, together with the first feed slot 201 and the substrate integrated cavity 101, forms a back cavity slot coupled feed metasurface radiation mode, which effectively improves the gain and reduces the mutual coupling between array elements during arraying compared to traditional metasurface antennas.

[0068] like Figure 3 and Figure 4 As shown, optionally, the first substrate integrated waveguide 203 and the second substrate integrated waveguide 304 further include multiple impedance adjustment vias and multiple offset waveguides;

[0069] The impedance adjustment via and offset waveguide are used to adjust impedance matching.

[0070] Specifically, such as Figure 3 As shown, a first impedance adjustment via 202 is provided on the side of the first feed slot 201 away from the waveguide wall, and a second impedance adjustment via 204 is provided on the side of the second feed slot 301 away from the waveguide wall. Other impedance adjustment vias 206 are also provided in the I-shaped feed network unit 20. For example... Figure 4 As shown, a third impedance adjustment via 302 is provided on the side of the second feed gap 301 away from the waveguide wall, and three fourth impedance adjustment vias 303 are provided near the power divider structure.

[0071] Specifically, such as Figure 3As shown, in the I-shaped feed network unit 20, the upper and lower half of the I-shaped waveguide uses offset waveguides 207 at the middle position, with the offset direction perpendicular to the waveguide propagation direction; the waist of the I-shaped waveguide uses offset waveguides 205 on both sides, with the offset direction perpendicular to the waveguide propagation direction. Figure 4 As shown, an offset waveguide is used on the waveguide of the power divider structure of the second substrate integrated waveguide 304, and the offset direction is set according to the impedance adjustment requirements.

[0072] By changing the position of the impedance adjustment via, adjusting the distance between the feed slot and the waveguide, setting the position and offset direction of the offset waveguide, and adjusting the impedance matching, the antenna impedance matching is achieved, enabling the antenna to be in a high-gain radiation mode.

[0073] The embodiments of the present invention employ a low-temperature co-fired ceramic process or a multilayer printed circuit board process.

[0074] In one specific embodiment, such as Figure 1-5 As shown, the solar panel 4 is the same size as the array antenna, and the solar panel 4 is bonded to the metal ground plane of the bottom feed network dielectric substrate. The bottom feed network dielectric substrate 3 includes a power divider structure, which is used to distribute energy equally and in phase to four second feed slots 301 to couple to the upper I-shaped feed unit 20. The I-shaped feed unit 20 redistributes the energy coupled from the second feed slots 301 to four first feed slots 202 through the power divider structure to couple to the substrate integrated cavity 101 of the substrate integrated cavity unit 10. Each I-shaped feed unit 20 corresponds to four substrate integrated cavity units 10, and the four substrate integrated cavity units 10 constitute a 2×2 antenna subarray 104.

[0075] Specifically, the substrate uses a TP-2 series composite board with a dielectric constant of 4.4. The array layer dielectric substrate of the substrate integrated cavity unit 10 has a thickness of 3.54 mm, and the thickness of the I-shaped feed network dielectric substrate 2 and the bottom feed network dielectric substrate 3 are both 1.54 mm. The array layer dielectric substrate 1 of the substrate integrated cavity unit 10 includes a substrate integrated cavity 101 surrounded by metal vias and a metasurface structure 102 located on the upper surface of the cavity; the diameter of each metal via is 1 mm, and the center-to-center distance between adjacent metal vias is 1.5 mm. The substrate integrated cavity 101 is designed as a rectangular cavity with dimensions of 19 mm × 19 mm × 3.54 mm, which allows the generation of a high-order resonant mode TM211 within the substrate integrated cavity 101. A rectangular metal patch 103 is located at the center of the surface of the substrate integrated cavity 101, and its diagonal is arranged at a 45° angle to the diagonal of the aperture face of the substrate integrated cavity 101, forming the metasurface structure 102.

[0076] The I-shaped feed network substrate 2 includes an I-shaped feed network unit 20 composed of a substrate integrated waveguide, four first feed slots 201 on the upper surface, one second feed slot 301 on the lower surface, and multiple impedance adjustment vias. The first substrate integrated waveguide 203 has a width of 11 mm and is short-circuited at the end of the slot by a row of metal vias. The dimensions of the first feed slot 201 on the upper surface are 7.98 mm × 0.56 mm, with its long side parallel to the waveguide propagation direction and the cavity edge, and the slot is located at the center of the lower surface of the cavity. To achieve impedance matching, the center of the first feed slot 201 is offset from the waveguide centerline by 3.47 mm and from the short-circuit via at the waveguide end by 5.32 mm. The first impedance adjustment via 202 is located on one side of the centerline of the first feed slot 201, 5.81 mm from the slot. The second feed slot 301 on the lower surface is 5.49 mm away from the waveguide centerline, and the second impedance adjustment via 204 is located on one side of the centerline of the second feed slot 301, at a distance of 6.48 mm from the second feed slot 301.

[0077] The bottom-layer feed network layer dielectric substrate 3 includes a substrate integrated waveguide 304 surrounded by metal vias, four rectangular first feed slots 301 on the upper surface of the substrate integrated waveguide, a coplanar waveguide transition structure 305 on the lower surface, and multiple impedance adjustment vias. The substrate integrated waveguide is 11 mm wide and is short-circuited at the slot ends by a row of metal vias. The second feed slot 301 on the upper surface has dimensions of 10.5 mm × 0.48 mm, with its long side parallel to the waveguide propagation direction and the cavity edge. To achieve impedance matching, the center of the second feed slot 301 is offset from the waveguide centerline by 4.68 mm and is 6.16 mm away from the short-circuit via at the waveguide end. The third impedance adjustment via 302 is located on one side of the centerline of the second feed slot 301, at a distance of 7.44 mm from the second feed slot 301. The fourth impedance adjustment via is 9.13 mm away from one side of the waveguide wall.

[0078] Figure 6 The impedance bandwidth and gain bandwidth of the integrated metasurface array antenna for spacecraft solar panels provided by this invention are shown in the figure. As can be seen from the figure, the antenna has a -10dB impedance bandwidth of 7.95GHz-11.30GHz, with a relative impedance bandwidth of 34.8%. The maximum gain of the antenna is 20.06dBi, and the gain is greater than 17dBi across the entire frequency band. Compared with traditional substrate integrated cavity antennas, this invention shows a significant improvement in gain and bandwidth. Therefore, this invention has broad application prospects in satellite communication, radar, radio frequency identification, and other fields.

[0079] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A spacecraft solar panel integrated metasurface array antenna, characterized in that, include: The stacked unit array dielectric substrate, the I-shaped feed network dielectric substrate, the bottom feed network dielectric substrate, and the solar panel; The unit array dielectric substrate serves as the front side of the array antenna, and includes multiple substrate integrated cavity units arranged in an array. Each substrate integrated cavity unit includes a substrate integrated cavity surrounded by metal through holes and a metasurface structure located at the center of the aperture surface of the substrate integrated cavity. The metasurface structure includes several rectangular metal patches arranged at periodic intervals. At low frequencies, the metasurface structure acts as the main radiator and operates in the fundamental mode; at high frequencies, the substrate integrated cavity acts as the main radiator and operates in the higher-order mode. The metasurface structure is used to change the higher-order mode distribution of the substrate integrated cavity so that its maximum radiation direction is along the normal direction of the substrate integrated cavity. The resonant frequencies corresponding to the two operating modes do not coincide. The I-shaped feed network dielectric substrate includes multiple I-shaped feed network units, each of which is surrounded by a first substrate integrated waveguide formed by metal vias. The first substrate integrated waveguide is used to feed the substrate integrated cavity unit. The underlying feed network dielectric substrate includes a second substrate integrated waveguide surrounded by metal vias, the second substrate integrated waveguide being used to feed energy into a plurality of the I-shaped feed network units; The solar panel and the array antenna are isolated by a metal floor of the underlying feed network dielectric substrate. The solar panel is responsible for collecting the illumination energy on the back of the array antenna and powering the spacecraft connected to the array antenna. The unit array dielectric substrate, the I-shaped power supply network dielectric substrate, and the bottom power supply network dielectric substrate all include an upper metal layer on the upper surface and a lower metal layer on the lower surface. The lower metal layer of the substrate integrated cavity unit and the upper metal layer of the I-shaped power supply network unit are respectively provided with a first power supply gap that fits together. The first power supply gap is used to feed the energy of the I-shaped power supply network unit into the substrate integrated cavity unit. The lower metal layer of the I-shaped feed network unit and the upper metal layer of the second substrate integrated waveguide are respectively provided with a second feed gap that fits into each other. The second feed gap is used to feed the energy of the second substrate integrated waveguide into the I-shaped feed network unit. The lower metal layer of the underlying feed network dielectric substrate includes a coplanar waveguide transition structure for feeding external energy into the second substrate integrated waveguide. The lower metal layer of the underlying power supply network dielectric substrate serves as a metal floor, which is bonded to the solar panel.

2. The spacecraft solar panel integrated metasurface array antenna as described in claim 1, characterized in that, The solar panel has solar cells arranged periodically. The energy harvesting direction of the solar panel is opposite to the radiation direction of the array antenna.

3. The spacecraft solar panel integrated metasurface array antenna as described in claim 1, characterized in that, The diagonal of the rectangular metal patch in the metasurface structure forms a 45° angle with the diagonal of the aperture face of the substrate integrated cavity.

4. The spacecraft solar panel integrated metasurface array antenna as described in claim 1, characterized in that, The adjacent substrate integrated cavities on the unit array dielectric substrate share a row of metal through holes.

5. The spacecraft solar panel integrated metasurface array antenna as described in claim 4, characterized in that, A first feed slot is provided at the center of the lower metal layer of the substrate integrated cavity unit; four longitudinal waveguide slots are opened at the end of the I-shaped waveguide of the I-shaped feed network unit as the first feed slots, and four first feed slots are provided on the upper metal layer of the I-shaped feed network unit.

6. The spacecraft solar panel integrated metasurface array antenna as described in claim 4, characterized in that, A second feed slot is provided on the lower metal layer of one of the I-shaped feed network units; a waveguide longitudinal slot is opened at the end of the power divider structure of the bottom feed network dielectric substrate, which serves as a second feed slot; and four second feed slots are provided on the upper metal layer of one of the second substrate integrated waveguides.

7. The spacecraft solar panel integrated metasurface array antenna as described in claim 4, characterized in that, The second feed slot in the I-shaped feed network unit has its long side parallel to the propagation direction of the adjacent waveguide; the first feed slot in the I-shaped feed network unit has its long side parallel to the propagation direction of the adjacent waveguide; by adjusting the distance between the first feed slot and the second feed slot and the waveguide wall, the antenna achieves impedance matching.

8. The spacecraft solar panel integrated metasurface array antenna as described in claim 4, characterized in that, The first substrate integrated waveguide and the second substrate integrated waveguide also include multiple impedance adjustment vias and multiple offset waveguides; The impedance adjustment via and offset waveguide are used to adjust impedance matching.

9. The spacecraft solar panel integrated metasurface array antenna as described in claim 1, characterized in that, The substrate integrated cavity is a rectangular cavity.

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