A method for designing a cambered array surface device for an aircraft side

Abstract

The application provides a curved-surface array device and a design method for the side of an airplane, which comprises a plurality of curved-surface arrays, an out-of-cabin array rotating platform, a flow-rectifying wave-transparent cover, an array rotating platform and fuselage connecting assembly, a flow-rectifying wave-transparent cover and fuselage connecting assembly and an array and rotating platform connecting assembly; the out-of-cabin array rotating platform is arranged outside the airplane fuselage skin, the plurality of curved-surface arrays are all fixed outside the out-of-cabin array rotating platform, and the flow-rectifying wave-transparent cover covers outside the curved-surface arrays; the out-of-cabin array rotating platform is connected to the airplane fuselage skin through the array rotating platform and fuselage connecting assembly, the curved-surface arrays are connected to the airplane fuselage skin through the array and rotating platform connecting assembly, and the flow-rectifying wave-transparent cover is connected to the outside of the airplane fuselage skin through the flow-rectifying wave-transparent cover and fuselage connecting assembly. Through the design of the lateral stepped curved-surface array, the convexity of the array and the external flow-rectifying wave-transparent cover is reduced, the limitation of the array beam emission angle is solved, and the normal power of external radiation in each direction is ensured.

Description

Technical Field

[0001] This invention relates to the field of aircraft avionics design technology, specifically to an arc-shaped array device and design method for the side of an aircraft. Background Technology

[0002] Antenna arrays are typically mounted on the outer surfaces of the aircraft's fuselage, usually consisting of an array structure mounting platform on the fuselage exterior, the array itself, and an external fairing. The array is generally designed as a flat panel to ensure adequate normal power radiation and ease of manufacturing. However, in practice, some arrays are large and require specific pitch angles. Designing the array as a curved surface directly would reduce the normal power radiation in all directions, increasing manufacturing difficulty and cost. These antenna arrays located on the outer side of the aircraft not only affect aerodynamic performance but also increase the aircraft's reflective area, structural weight, and negatively impact range and handling. To address these adverse effects, a stepped curved surface design method for the aircraft's sides can be adopted to ensure the array meets operational requirements. Summary of the Invention

[0003] In view of this, the embodiments of this specification provide an arc-shaped array device and design method for the side of an aircraft, so as to reduce flight aerodynamic drag and structural weight, and solve the limitation of the array beam emission angle.

[0004] The embodiments in this specification provide the following technical solutions:

[0005] A curved surface array device on the side of an aircraft, comprising: Multiple curved arrays, external array mounting platform, rectifier radome, mounting platform and fuselage connection assembly, rectifier radome and fuselage connection assembly, and array and mounting platform connection assembly; The external array mounting platform is located on the outside of the aircraft fuselage skin, and multiple arc-shaped arrays are fixed on the outside of the external array mounting platform. The rectifier wave shield covers the outside of the arc-shaped arrays. The external array mounting platform is connected to the aircraft fuselage skin via the mounting platform and fuselage connection assembly. The arc-shaped array is connected to the aircraft fuselage skin via the array and mounting platform connection assembly. The rectifier radar dome is connected to the outside of the aircraft fuselage skin via the rectifier radar dome and fuselage connection assembly.

[0006] Furthermore, the inner contour of the external array mounting platform fits the outer contour of the aircraft fuselage skin, and the outer contour of the external array mounting platform includes multiple stepped planes, which fit one by one with the arc-shaped array.

[0007] Furthermore, the external array mounting platform includes a surface treatment layer and a conductive adhesive layer covering the surface of the surface treatment layer.

[0008] Furthermore, the rectifier shield is made of multi-layer fiberglass.

[0009] Furthermore, the material of the external array mounting platform is a pre-stretched plate, which is formed by bending after being processed by CNC machine tools or mechanical processing.

[0010] A design method for designing curved surface array devices on the side of an aircraft, comprising: Based on the mission requirements to be performed by the aircraft, the performance parameters of the arc-shaped array are determined, including the array aperture, array power, operating frequency band, and radiation angle. The mission requirements include detection missions, jamming missions, and early warning missions. Based on the performance parameters, the overall length, overall width, and overall height of the arc-shaped array are determined, and the thickness of the arc-shaped array is determined according to the array power. Based on the overall length, overall width, and overall height of the arc surface array, the arc surface array is decomposed into multiple sub-flat surface arrays, and the number of sub-flat surface arrays and the individual length, individual width, individual height, and preset normal direction of each sub-flat surface array are determined. Based on the overall length, overall width, overall height of the arc-shaped array and the shape of the aircraft fuselage skin, the inner contour of the external array mounting platform is determined so that the inner contour fits the outer contour of the aircraft fuselage skin. Determine the number of stepped planes on the external array mounting platform, so that the number of stepped planes is consistent with the number of sub-flat arrays, and determine the outer contour of the stepped planes so that the installed arc-shaped array is tangent to the arc-shaped surface on the side of the aircraft. Based on the physical interface locations of the cables, plugs, and liquid cooling equipment of the avionics equipment, the location coordinates and aperture dimensions of the installation and maintenance openings are determined within the outer contour dimensions of the external array mounting platform. Based on the overall length, overall width, overall height and radiation requirements of the arc surface, the external dimensions of the rectifier radome are determined, and the minimum gap is determined according to the wave transmission performance requirements of the rectifier radome, so that the inner shape of the rectifier radome and the arc surface maintain the minimum gap.

[0011] Further, based on the overall length, overall width, and overall height of the arc-shaped array, the arc-shaped array is decomposed into multiple sub-flat arrays, and the number of sub-flat arrays and the individual length, individual width, individual height, and preset normal direction of each sub-flat array are determined, including: The electromagnetic wavelength λ is determined by the operating frequency band, and the target coverage arc surface on the side of the aircraft is determined by the radiation angle. Based on the electromagnetic wavelength λ and the target coverage arc surface, a decomposition rule is established; Using the overall length, width, and height of the arc surface as boundaries and the decomposition rules as constraints, the number of sub-flat surfaces, the individual length, width, and height of each sub-flat surface, and the preset normal direction are determined through iterative optimization, thus completing the decomposition of the arc surface.

[0012] Furthermore, based on the electromagnetic wavelength λ and the target coverage arc surface, decomposition rules are established, including: The first decomposition rule is that the maximum value of the length and width of each sub-flat surface is no greater than 2λ. The second decomposition rule is that the angle between the preset normal direction of each sub-flat surface and the theoretical normal direction of the target covering arc surface at the corresponding projection center is no greater than 5°. The third decomposition rule is that the height difference between the stepped planes of two adjacent sub-flat plate arrays is less than λ / 4 on the external array platform. The decomposition rule is defined as one that simultaneously satisfies the first decomposition rule, the second decomposition rule, and the third decomposition rule.

[0013] Further, the outer contour of the stepped plane is determined so that the installed arcuate surface is tangent to the arcuate surface of the aircraft side, including: Based on the fit between the inner contour of the external array mounting platform and the aircraft fuselage skin, the installation reference position coordinates corresponding to each sub-flat array are determined. For each of the sub-plate arrays, a corresponding stepped plane space equation is established at the coordinates of the installation reference position according to the preset normal direction corresponding to the sub-plate array, wherein the normal direction of the stepped plane is consistent with the preset normal direction of the corresponding sub-plate array. Based on the spatial equation of each stepped plane and the individual dimensions of the sub-flat surface, calculate the coordinates of the boundary points of each stepped plane; The outer contour of the stepped plane of the external array mounting platform is generated based on the coordinates of the boundary points of all the stepped planes.

[0014] Further, determining the minimum gap based on the wave transmission performance requirements of the rectifier radome includes: Obtain the electromagnetic wavelength λ corresponding to the operating frequency band; Based on the electromagnetic wavelength λ and the preset wave transmission performance index, the minimum theoretical gap value that meets the wave transmission requirements is determined. Obtain the overall height of the arc-shaped surface and the thickness of the rectifier radome; Based on the minimum theoretical gap value, the overall height of the arc-shaped array, and the thickness of the rectifier radome, the minimum gap between the rectifier radome and the arc-shaped array is calculated.

[0015] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least: The design of the lateral stepped arc surface reduces the outward bulge of the array and the external rectifier radome, thereby reducing aerodynamic drag and structural weight, solving the limitation of the array beam emission angle, and ensuring the normal power radiated outward in all directions. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the location of the arc-shaped array device on the side of the aircraft according to an embodiment of the present invention. Figure 2 yes Figure 1 A cross-sectional view along the AA direction; Figure 3 yes Figure 1 A cross-sectional view along the BB direction; Figure 4 This is a cross-sectional view of the external array mounting platform according to an embodiment of the present invention.

[0018] The attached figures are labeled as follows: 1. Curved radar array; 2. External radar array mounting platform; 3. Rectifier radome; 4. Mounting platform and fuselage connection assembly; 5. Rectifier radome and fuselage connection assembly; 6. Radome and mounting platform connection assembly. Detailed Implementation

[0019] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0020] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] A curved surface array device on the side of an aircraft, comprising: 1. Multiple curved arrays, 2. External array mounting platform, 3. Rectifier radome, 4. Rectifier radome and fuselage connection assembly, 5. Array and mounting platform connection assembly; The external array mounting platform 2 is set on the outside of the aircraft fuselage skin, and multiple curved arrays 1 are fixed on the outside of the external array mounting platform 2. The fairing 3 covers the outside of the curved arrays 1. The external array mounting platform 2 is connected to the aircraft fuselage skin via the mounting platform and fuselage connection assembly 4. The curved array 1 is connected to the aircraft fuselage skin via the array and mounting platform connection assembly 6. The fairing 3 is connected to the outside of the aircraft fuselage skin via the fairing and fuselage connection assembly 5.

[0022] The inner contour of the external array mounting platform 2 fits the outer contour of the aircraft fuselage skin. The outer contour of the external array mounting platform 2 includes multiple stepped planes, which fit one by one with the curved array 1.

[0023] The external array mounting platform 2 includes a surface treatment layer and a conductive adhesive layer covering the surface of the surface treatment layer.

[0024] The rectifier shield 3 is made of multi-layer fiberglass.

[0025] The material of the external array mounting platform 2 is a pre-stretched plate, which is formed by bending after being processed by CNC machine tools or mechanical processing.

[0026] In one embodiment of the present invention, according to Figures 1 to 4 As shown, a type of aircraft lateral stepped arc surface array mainly includes: arc surface array 1 (9 pieces symmetrically arranged on the left and right), external array mounting platform 2 (1 piece symmetrically arranged on the left and right), fairing 3 (2 pieces), mounting platform and fuselage connection assembly 4 (several pieces), fairing and fuselage connection assembly 5 (several pieces), and multiple array pieces and mounting platform connection assembly 6 (several pieces).

[0027] The external array mounting platform 2 is made of pre-stretched plate material 7075-T7451-δ, and is formed by CNC machine tool processing (or mechanical processing followed by bending). The internal shape of the external array mounting platform 2 is consistent with the shape of the aircraft skin. The outer surface of the external array mounting platform 2 has 9 stepped planes for installing the arc surface array 1, so that after the arc surface array 1 is installed, the arc surface array 1 is tangent to each arc surface segment and radiates outward in the normal direction.

[0028] The external array mounting platform 2, after machining, has dimensions of a×k×j mm (length×height×thickness). Simultaneously, the external array mounting platform 2 and the fuselage skin have corresponding openings for the installation and maintenance of equipment such as cables, plugs, and liquid cooling systems, facilitating equipment installation and maintenance. The external array mounting platform 2 is connected and fixed to the aircraft skin and surrounding structures using mounting platform and fuselage connection components 4 (several pieces), forming a mounting and fixing platform for the arc-shaped array 1, such as... Figure 2 , Figure 4 .

[0029] Installation of the finished arc-shaped array 1. After removing the metal protective coating from the outer surface of the external array mounting platform 2, a layer of conductive adhesive is applied to the outer surface of the external array mounting platform 2 to ensure the conductivity requirements between the arc-shaped array 1 and the external array mounting platform 2. The external dimensions of a single arc-shaped array 1 are a×b×cmm (length×width×height). Nine arc-shaped arrays 1 are spliced ​​together to form an array with dimensions a×dmm (length×width). The finished arc-shaped array 1 is connected and fixed to the mounting platform connecting assembly 6 (several pieces) using multiple array pieces. At the same time, the power supply cables, plugs, liquid cooling equipment, and other equipment of the arc-shaped array 1 are installed.

[0030] The rectifier radome 3 serves both rectification and wave transmission functions. It is right-symmetrical about the aircraft's centerline of symmetry, with external dimensions of e×f×g mm (length×width×height). The minimum internal dimension of the rectifier radome 3 compared to the curved surface 1 is h mm, where h is greater than or equal to 70 mm, ensuring sufficient internal space for installation. The rectifier radome 3 is a multi-layered fiberglass structure, using a specialized mold, vacuum-laid bonding, and high-temperature curing for one-time molding. The design of the rectifier radome 3 meets its own strength and rigidity requirements, as well as the wave transmission and burn-resistance performance requirements of the curved surface 1. During installation, after removing the surface treatment (removing the metal protective treatment) from the contact area between the fuselage skin and the rectifier radome 3, a layer of conductive adhesive is applied to the treated area to ensure conductivity between the rectifier radome 3 and the fuselage skin. The rectifier radome 3 and the fuselage skin are connected and fixed using the rectifier radome-fuselage connection assembly 5 (several pieces). This technical solution realizes a design method for a side-mounted stepped curved surface array for aircraft.

[0031] The design method for the curved surface array device on the side of an aircraft includes the following steps: Step 1: Determine the performance parameters of the arc-shaped array based on the mission requirements to be performed by the aircraft. The performance parameters include array aperture, array power, operating frequency band and radiation angle. The mission requirements include detection mission, jamming mission and early warning mission. Step 2: Based on performance parameters, determine the overall length, overall width, and overall height of the arc-shaped array 1, and determine the thickness of the arc-shaped array 1 according to the array power; Step 3: Based on the overall length, overall width and overall height of the arc surface array 1, decompose the arc surface array 1 into multiple sub-flat surface arrays, and determine the number of sub-flat surface arrays and the individual length, individual width, individual height and preset normal direction of each sub-flat surface array; Step 4: Based on the overall length, width, and height of the curved surface 1 and the shape of the aircraft fuselage skin, determine the inner contour of the external surface mounting platform 2 so that the inner contour fits the outer contour of the aircraft fuselage skin. Step 5: Determine the number of stepped planes on the external array mounting platform 2, so that the number of stepped planes is consistent with the number of sub-flat arrays, and determine the outer contour of the stepped planes so that the installed arc array 1 is tangent to the arc surface on the side of the aircraft. Step 6: Based on the physical interface locations of the cables, plugs, and liquid cooling equipment of the avionics equipment, determine the location coordinates and aperture dimensions of the installation and maintenance openings within the outer contour dimensions of the external array mounting platform 2. Step 7: Based on the overall length, overall width, overall height and radiation requirements of the arc surface 1, determine the external dimensions of the rectifier radome 3, and determine the minimum gap according to the wave transmission performance requirements of the rectifier radome 3, and keep the minimum gap between the inner shape of the rectifier radome 3 and the arc surface 1.

[0032] Starting with the top-level missions (detection, jamming, early warning), the core electromagnetic parameters (aperture, power, frequency band, radiation angle) that determine the array's performance are defined. Then, these electromagnetic parameters are transformed into the initial physical concept of the array (overall dimensions). Finally, the array is decomposed and mapped.

[0033] The concept of a large array surface is broken down into multiple smaller, more easily implemented sub-flat array surfaces, and their geometric properties and key "preset normal directions" are determined.

[0034] The properties of the decomposed electromagnetic units (sub-plate arrays) are precisely mapped onto the mechanical structure. That is, based on the normal direction of the sub-plate arrays, the stepped plane of the external array mounting platform is designed to ensure that an approximate curved surface radiation effect can be achieved after installation.

[0035] Complete the design of the platform openings and fairing to form a complete, manufacturable, and installable device solution.

[0036] The design method of this invention provides a standardized and repeatable design process, avoiding the trial-and-error process that relies on experience in traditional design, thus improving design efficiency and success rate. Through a rigorous chain of steps, it ensures that the final manufactured physical device meets the initially set electromagnetic performance requirements, achieving "design is correct." The input-output relationships between design parameters are clearly defined, laying the foundation for subsequent optimization and computer-aided design (CAD / CAE).

[0037] Specifically, based on the overall length, width, and height of the arc surface array 1, the arc surface array 1 is decomposed into multiple sub-flat surface arrays. The number of sub-flat surface arrays and the individual length, width, height, and preset normal direction of each sub-flat surface array are determined, including: The electromagnetic wavelength λ is determined by the operating frequency band, and the target coverage arc on the side of the aircraft is determined by the radiation angle. Decomposition rules are established based on the electromagnetic wavelength λ and the target coverage arc surface; Using the overall length, width, and height of the arc surface array 1 as boundaries and the decomposition rules as constraints, the number of sub-flat surfaces, the individual length, width, and height of each sub-flat surface array, and the preset normal direction are determined through iterative optimization, thus completing the decomposition of the arc surface array 1.

[0038] Specifically, based on the electromagnetic wavelength λ and the target coverage arc, decomposition rules are established, including: The first decomposition rule is that the maximum length and width of each sub-plate surface are no greater than 2λ. The second decomposition rule is that the angle between the preset normal direction of each sub-flat surface and the theoretical normal direction of the target covering arc surface at the corresponding projection center is no greater than 5°. The third decomposition rule is that the height difference between the stepped planes of two adjacent sub-flat plate arrays is less than λ / 4 on the external array platform 2. The decomposition rule is defined as one that simultaneously satisfies the first decomposition rule, the second decomposition rule, and the third decomposition rule.

[0039] Specifically, rule one (individual size ≤ 2λ): Based on antenna theory, when the size of a radiating element is much larger than the wavelength, its beam narrows, and the mutual coupling effect between elements becomes complex and difficult to control. Limiting the subarray size to within 2λ ensures that each subarray maintains good radiation characteristics within the operating frequency band and simplifies the overall array's feed network and beam control design.

[0040] Decomposition Rule 2 (normal angle ≤ 5°): This is key to achieving the "arc surface" radiation effect. By forcibly requiring the normal of each sub-array to closely adhere to the theoretical normal of the target arc surface, it ensures that the principal direction of the radiation beam from each sub-array points to the expected spatial angle. After all sub-array beams are combined, a wide-angle, uniformly covered radiation field can be formed in space, approximating the effect of a real arc surface array.

[0041] Decomposition Rule 3 (Step Height Difference < λ / 4): The step height difference between adjacent arrays introduces a path difference in electromagnetic wave propagation, which is converted into a phase difference. According to electromagnetic field theory, when the phase error is controlled within 90 degrees (i.e., the phase corresponding to the λ / 4 path difference), the impact on the antenna pattern (especially the main beam and sidelobes) is acceptable. This rule limits the electromagnetic performance degradation introduced by the mechanical steps.

[0042] By achieving an optimal balance between electrical performance and manufacturing feasibility through three decomposition rules, and through the combined constraints of these three rules, a high-performance electromagnetic arc surface was successfully approximated using a series of easily manufactured mechanical planes. This effectively solved the core contradiction of narrow viewing angle of flat panel arrays and difficult manufacturing of real arc surface arrays, achieving wide-angle, high-normal-power radiation.

[0043] Specifically, the outer contour of the stepped plane is determined so that the installed arc surface 1 is tangent to the arc surface of the aircraft side, including: Based on the fit between the inner contour of the external array mounting platform 2 and the aircraft fuselage skin, the coordinates of the installation reference position corresponding to each sub-flat panel are determined. For each sub-panel array, based on the preset normal direction corresponding to the sub-panel array, a corresponding stepped plane space equation is established at the coordinates of the installation reference position, wherein the normal direction of the stepped plane is consistent with the preset normal direction of the corresponding sub-panel array. Based on the spatial equation of each stepped plane and the individual dimensions of the sub-plate surface, the coordinates of the boundary points of each stepped plane are calculated. Based on the coordinates of the boundary points of all stepped planes, the outer contour of the stepped plane of the external array mounting platform 2 is generated.

[0044] The electromagnetic design (preset normal direction) is precisely translated into the mechanical structure (platform outer contour). Using the preset normal direction and installation reference position as input, an infinitely extending plane is uniquely determined in three-dimensional space. The infinite plane is trimmed using the individual dimensions of the sub-plate arrays to obtain a closed boundary representing the actual size and shape of the stepped plane. Combining the boundaries of all stepped planes forms a complete and accurate three-dimensional model of the installation platform.

[0045] Seamless digital integration from electromagnetic design to structural design was achieved, reducing human error and significantly improving design accuracy and efficiency. Rigorous mathematical calculations ensured that the stepped plane of the manufactured platform perfectly aligned with the sub-array surface, ultimately maintaining tangency between the array surface and the aircraft target's curved surface, guaranteeing that electromagnetic performance met requirements. The generated boundary point coordinates and 3D model can be directly used for CNC machine tool programming and to guide production.

[0046] Specifically, the minimum gap is determined based on the wave transmission performance requirements of the rectifier radome 3, including: Obtain the electromagnetic wavelength λ corresponding to the operating frequency band; Based on the electromagnetic wavelength λ and the preset wave transmission performance index, the minimum theoretical gap value that meets the wave transmission requirements is determined. Obtain the overall height of the curved surface 1 and the thickness of the rectifier radome 3; Based on the minimum theoretical gap value, the overall height of the arc surface 1, and the thickness of the rectifier radome 3, the minimum gap between the rectifier radome 3 and the arc surface 1 is calculated.

[0047] When the thickness of the air layer is an integer multiple of half the wavelength, a standing wave is formed, causing resonance. This results in a large amount of electromagnetic waves being reflected back, leading to a sharp decrease in wave transmission performance. The determination of the minimum theoretical gap value is precisely to avoid these resonance points and ensure stable wave transmission within the operating frequency band.

[0048] Based on theoretical calculations, and combined with the array height and cover thickness, the final minimum gap is calculated. In one embodiment of the invention, the minimum gap can be set to 70mm. A minimum gap ≥70mm ensures that resonance can be effectively avoided and transmission parameters (such as insertion loss and VSWR) can be met under all operating conditions and manufacturing tolerances.

[0049] Minimal gaps ensure that the energy emitted by the antenna can be effectively radiated and that external signals can be received without loss. By designing this feature, system performance degradation caused by improper gaps is avoided at the source. Such problems are difficult to detect in later testing and are extremely costly to correct.

[0050] The arc-shaped array device of this invention meets the requirements for airborne and mission system array use. Under the condition of arrays in the same frequency band, a large flat panel array is decomposed into multiple identical (or similar) small flat panel arrays. These multiple identical (or similar) small flat panel arrays are spliced ​​onto an array stepped mounting platform on the outer surface of the aircraft (the mounting area is flat), forming an arc-like array. This achieves outward arc-shaped radiation with the same frequency band, the same area aperture, and the same power. It reduces the outward convexity of the array and the external fairing, reduces aerodynamic drag and structural weight, solves the limitation of the array beam emission angle, ensures the normal power of outward radiation in all directions, meets the requirements for array use, and improves the overall performance of the aircraft.

[0051] Beneficial effects of the embodiments of the present invention: This invention provides a lateral stepped arc array for aircraft. By arranging a large array on the sidewall of a medium-sized or large aircraft within the available space, it meets the requirements for large-scale installation, viewing angle, and functionality. This invention overcomes the increased impact on aircraft weight and aerodynamic drag caused by installing a large array. It decomposes the large array into multiple identical (or similar) small flat panel arrays, which are then spliced ​​together to form a similar arc-shaped array, achieving external arc-shaped radiation with the same frequency band, area, and power. The design of the lateral stepped arc array reduces the outward protrusion of the array and the external fairing, decreasing aerodynamic drag and structural weight, and overcoming the limitation of the array beam emission angle, ensuring normal power radiated outward in all directions. Through reasonable arrangement, optimized weight reduction, and aerodynamic drag reduction design, the array function is achieved, the impact on the overall aircraft performance is reduced, and the overall aircraft performance is improved. It also has good manufacturability and maintainability.

[0052] The above description is merely a specific embodiment of the present invention and should not be construed as limiting the scope of the invention. Therefore, any substitution of equivalent components or equivalent changes and modifications made within the scope of protection of this patent should still fall within the scope of this patent. Furthermore, the technical features, technical features and technical solutions, and technical solutions in this invention can be freely combined and used.

Claims

1. A design method for an arc-shaped array device on the side of an aircraft, used to design an arc-shaped array device on the side of an aircraft, characterized in that, The curved surface array device on the side of the aircraft includes: Multiple curved surface arrays (1), external array mounting platform (2), rectifier radome (3), mounting platform and fuselage connection assembly (4), rectifier radome and fuselage connection assembly (5), and array and mounting platform connection assembly (6). The external array mounting platform (2) is set on the outside of the aircraft fuselage skin. Multiple arc-shaped arrays (1) are fixed on the outside of the external array mounting platform (2). The rectifier radome (3) covers the outside of the arc-shaped arrays (1). The external array mounting platform (2) is connected to the fuselage skin of the aircraft via the mounting platform and fuselage connection assembly (4), the arc surface array (1) is connected to the fuselage skin of the aircraft via the array and mounting platform connection assembly (6), and the rectifier radome (3) is connected to the outside of the fuselage skin of the aircraft via the rectifier radome and fuselage connection assembly (5). Design methods include: Based on the mission requirements to be performed by the aircraft, the performance parameters of the arc-shaped array are determined, including the array aperture, array power, operating frequency band, and radiation angle. The mission requirements include detection missions, jamming missions, and early warning missions. Based on the performance parameters, the overall length, overall width and overall height of the arc surface array (1) are determined, and the thickness of the arc surface array (1) is determined according to the array power; Based on the overall length, overall width and overall height of the arc surface array (1), the arc surface array (1) is decomposed into multiple sub-flat surface arrays, and the number of sub-flat surface arrays and the individual length, individual width, individual height and preset normal direction of each sub-flat surface array are determined. Based on the overall length, overall width, overall height of the arc surface (1) and the shape of the aircraft fuselage skin, the inner contour of the external surface mounting platform (2) is determined so that the inner contour fits the outer contour of the aircraft fuselage skin. Determine the number of stepped planes of the external array mounting platform (2) so that the number of stepped planes is consistent with the number of sub-flat arrays. Determine the outer contour of the stepped planes so that the installed arc array (1) is tangent to the arc surface on the side of the aircraft. Based on the physical interface locations of the cables, plugs, and liquid cooling equipment of the avionics equipment, the location coordinates and aperture size of the installation and maintenance openings are determined within the outer contour dimensions of the external array mounting platform (2). Based on the overall length, overall width, overall height and radiation requirements of the arc surface (1), the external dimensions of the rectifier shield (3) are determined, and the minimum gap is determined according to the wave transmission performance requirements of the rectifier shield (3), so that the inner shape of the rectifier shield (3) and the arc surface (1) maintain the minimum gap.

2. The design method according to claim 1, characterized in that, Based on the overall length, overall width, and overall height of the arc surface array (1), the arc surface array (1) is decomposed into multiple sub-flat surface arrays. The number of sub-flat surface arrays and the individual length, individual width, individual height, and preset normal direction of each sub-flat surface array are determined, including: The electromagnetic wavelength λ is determined by the operating frequency band, and the target coverage arc surface on the side of the aircraft is determined by the radiation angle. Based on the electromagnetic wavelength λ and the target coverage arc surface, a decomposition rule is established; Using the overall length, overall width, and overall height of the arc surface array (1) as boundaries and the decomposition rules as constraints, the number of sub-flat surfaces, the individual length, individual width, and individual height of each sub-flat surface array, and the preset normal direction are determined through iterative optimization, thereby completing the decomposition of the arc surface array (1).

3. The design method according to claim 2, characterized in that, Based on the electromagnetic wavelength λ and the target coverage arc surface, decomposition rules are established, including: The first decomposition rule is that the maximum value of the length and width of each sub-flat surface is no greater than 2λ. The second decomposition rule is that the angle between the preset normal direction of each sub-flat surface and the theoretical normal direction of the target covering arc surface at the corresponding projection center is no greater than 5°. The third decomposition rule is that the height difference between the stepped planes of two adjacent sub-flat plate arrays on the external array platform (2) is less than λ / 4. The decomposition rule is defined as one that simultaneously satisfies the first decomposition rule, the second decomposition rule, and the third decomposition rule.

4. The design method according to claim 1, characterized in that, Determine the outer contour of the stepped plane so that the installed arc surface (1) is tangent to the arc surface on the side of the aircraft, including: Based on the fit relationship between the inner contour of the external array mounting platform (2) and the aircraft fuselage skin, the installation reference position coordinates corresponding to each sub-flat array are determined; For each of the sub-plate arrays, a corresponding stepped plane space equation is established at the coordinates of the installation reference position according to the preset normal direction corresponding to the sub-plate array, wherein the normal direction of the stepped plane is consistent with the preset normal direction of the corresponding sub-plate array. Based on the spatial equation of each stepped plane and the individual dimensions of the sub-flat surface, calculate the coordinates of the boundary points of each stepped plane; The outer contour of the stepped plane of the external array platform (2) is generated based on the coordinates of the boundary points of all the stepped planes.

5. The design method according to claim 1, characterized in that, The minimum clearance is determined according to the wave transmission performance requirements of the rectifier shield (3), including: Obtain the electromagnetic wavelength λ corresponding to the operating frequency band; Based on the electromagnetic wavelength λ and the preset wave transmission performance index, the minimum theoretical gap value that meets the wave transmission requirements is determined. Obtain the overall height of the arc surface (1) and the thickness of the rectifier shield (3); Based on the minimum theoretical gap value, the overall height of the arc surface (1) and the thickness of the rectifier shield (3), the minimum gap between the rectifier shield (3) and the arc surface (1) is calculated.

6. The design method according to claim 1, characterized in that, The inner contour of the external array mounting platform (2) fits the outer contour of the aircraft fuselage skin. The outer contour of the external array mounting platform (2) includes multiple stepped planes, which fit one by one with the arc surface array (1).

7. The design method according to claim 1, characterized in that, The external array mounting platform (2) includes a surface treatment layer and a conductive adhesive layer covering the surface of the surface treatment layer.

8. The design method according to claim 1, characterized in that, The rectifier shield (3) is made of multi-layer fiberglass.

9. The design method according to claim 1, characterized in that, The material of the external array mounting platform (2) is a pre-stretched plate, which is formed by bending after being processed by CNC machine tool or mechanical processing.

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