An aircraft fuselage high rack electronic array configuration device
By installing a ship-shaped electronic array configuration device high on the outside of the aircraft fuselage, the limitations of traditional electronic arrays in terms of radiation installation angle and viewing angle are solved, enabling 360° use of the electronic array and increasing the number of electronic arrays installed on the aircraft and its overall performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHAANXI AIRCRAFT CORPORATION
- Filing Date
- 2023-10-25
- Publication Date
- 2026-07-14
AI Technical Summary
Traditional fuselage surface-mounted electronic arrays are difficult to meet the requirements of modern aircraft electronic warfare mission systems, especially due to limitations in the radiation installation angle and viewing angle, which restricts the functionality of the electronic arrays.
The system employs an elevated electronic array configuration on the aircraft fuselage, mounting the electronic array high above the fuselage in a boat-shaped layout to form an all-around electronic array, including six electronic arrays on the front, rear, top, bottom, left, and right sides. Through the design of internal components, external components, and boat-shaped components, the system achieves the 360° operational requirements of the electronic array.
It expands the installation methods of electronic arrays, increases the number of electronic arrays on the aircraft, enhances the overall performance of the aircraft, and meets the requirements of modern aircraft electronic warfare mission systems.
Smart Images
Figure CN117508618B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aviation technology and relates to the layout design of an aircraft electronic array, specifically to an aircraft airborne electronic array configuration device. Background Technology
[0002] With the development of modern electronic warfare, aircraft surfaces need to carry an increasing variety of electronic arrays to perform various tasks such as electronic reconnaissance, identification, search, surveillance, communication jamming, radar jamming, and early warning. This makes conventional electronic arrays increasingly inadequate for most aircraft. Electronic arrays are typically mounted on the front, rear, left, and right sides of the fuselage. Mission-specific electronic arrays usually have specific radiation angle and viewing angle requirements, necessitating minimal obstruction from the aircraft's fuselage, wings, and tail to maximize the functionality of the mission system.
[0003] Traditional fuselage surface mounting technology is difficult to meet the requirements of modern mission systems. Under the inherent aircraft structural layout, the traditional electronic array design is difficult to adapt to the needs of modern aircraft combat modes and functions. Therefore, it is necessary to adopt the form of elevated electronic array, which extends the electronic array to a high position outside the fuselage to meet the requirements of mission system electronic array use.
[0004] Traditional elevated electronic arrays are single-array or two-array arrays, with relatively small radiation installation angles and visual angles. Summary of the Invention
[0005] To address the aforementioned issues, this invention proposes an elevated electronic array configuration device for aircraft fuselages. By mounting the electronic array high above the fuselage and employing a boat-shaped layout, it forms an all-around electronic array covering the front, rear, top, bottom, left, and right sides. This overcomes the limitation of the electronic array's beam emission angle, achieving 360° operation of the electronic array, expanding the range of electronic array mounting options, increasing the number of electronic arrays installed on the aircraft, and ultimately improving the overall performance of the aircraft.
[0006] The technical solution of the present invention is as follows:
[0007] An overhead electronic array configuration device for an aircraft fuselage includes an internal assembly, an external assembly, and a boat-shaped assembly. The internal assembly is arranged within the fuselage skin of the aircraft, and it transmits the structural forces above it to the floor beams and the bottom of the aircraft. The external assembly is connected to the upper part of the internal assembly. The external assembly is a rectangular structure with a directional layout, and it has leading and trailing edges at its front and rear ends. The upper end of the external assembly is connected to the boat-shaped assembly, which is boat-shaped and symmetrical in all directions. Electronic arrays are arranged in the front, rear, left, right, and top of the boat-shaped assembly. Electronic arrays are also arranged in the left and right sides of the external assembly.
[0008] Furthermore, the cabin assembly includes reinforcing frames, docking joints, and upper cabin docking reinforcements. The reinforcing frames are near-circular frame structures with the same curvature as the fuselage surface. Four reinforcing frames are respectively located at the front two positions and the rear two positions of the aircraft fuselage and fit snugly inside the fuselage. The bottom of each reinforcing frame is connected to the aircraft floor and floor beams through its own docking joint. The reinforcing frames at the front two positions are connected to the upper cabin docking reinforcements at the front, and the reinforcing frames at the rear two positions are connected to the upper cabin docking reinforcements at the rear.
[0009] Furthermore, the upper docking reinforcement inside the cabin is a reinforced structural component with the same curvature as the top of the fuselage; the upper docking reinforcement inside the cabin, the reinforcing frame and the docking joint distribute the load transmitted from the top to the fuselage skin, stringers and floor beams, achieving force transmission and balance.
[0010] Furthermore, the external assembly includes an external lower end docking reinforcement, an external vertical beam assembly, and an external upper end docking reinforcement. The two external lower end docking reinforcements are respectively connected to the front and rear ends of the internal assembly, and the external upper end docking reinforcements are respectively connected to the front and rear ends of the hull assembly. The external vertical beam assembly is supported between the external lower end docking reinforcement and the external upper end docking reinforcement. The external vertical beam assembly has an external elevated leading edge at its front end and an external elevated trailing edge at its rear end.
[0011] Furthermore, there are eight external beam assemblies, which are respectively located on the left and right sides of the four reinforcing frames. A horizontal beam between the external elevated beams is provided between two external beam assemblies that are opposite each other on the left and right sides.
[0012] Furthermore, the left and right sides of the external assembly are respectively provided with external elevated frame rectifiers. The external elevated frame rectifiers are specifically located between the front and rear external beam assemblies. Electronic arrays are installed in the internal space of the eight external beam assemblies and transmit and receive signals to the outside through the external elevated frame rectifiers. The space between the front edge of the external elevated frame and the front external beam assembly, as well as the space between the rear edge of the external elevated frame and the front external beam assembly, are the installation space for cables and liquid cooling systems.
[0013] Furthermore, the hull-shaped assembly includes a lower hull-shaped docking reinforcement, a hull-shaped vertical beam assembly, a upper hull-shaped docking reinforcement, a forward hull-shaped fairing, a rear hull-shaped fairing, port and starboard side fairings, and a top hull-shaped fairing. The lower hull-shaped docking reinforcement is connected to the top of the external assembly. The lower hull-shaped docking reinforcement is connected to the upper hull-shaped docking reinforcement through the hull-shaped vertical beam assembly to form a roughly square-shaped reinforced frame. The forward hull-shaped fairing, a rear hull-shaped fairing, two port and starboard side fairings, and the top hull-shaped fairing are respectively located at the front, rear, left, right, and top of the reinforced frame to form a hull-shaped structure. An electronic array is arranged inside the hull-shaped assembly, and the electronic array transmits and receives signals through the five fairings of the hull-shaped assembly.
[0014] Furthermore, the loads of the hull assembly are distributed to the fuselage skin, girder, and floor beams through the external and internal assemblies, achieving force transmission and balance.
[0015] The beneficial effects of this invention are as follows:
[0016] 1. This invention provides an elevated electronic array configuration device for aircraft. By installing the electronic array at a high position outside the fuselage, the electronic array is raised, reducing the obstruction of the electronic array by aircraft structures such as the fuselage, wings, and tail.
[0017] 2. This invention proposes a ship-shaped electronic array configuration device, forming six electronic arrays in the front, rear, top, bottom, left, and right directions. It solves the limitation of the electronic array beam emission angle, realizes the 360° use requirement of the electronic array, meets the requirements of the mission system, expands and increases the electronic array installation methods, increases the number of electronic arrays installed on the aircraft, and improves the overall comprehensive performance of the aircraft. Attached Figure Description
[0018] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this invention and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.
[0019] Figure 1 This is a schematic diagram of an aircraft elevated electronic array configuration device.
[0020] Figure 2 for Figure 1 A schematic diagram of direction B;
[0021] Figure 3 for Figure 1 A schematic diagram of the AA cross-section;
[0022] Wherein: 1—Reinforcing frame, 2—Docking joint, 3—Upper docking reinforcement inside the cabin, 4—Lower docking reinforcement outside the cabin, 5—Upper beam assembly outside the cabin, 6—Upper docking reinforcement outside the cabin, 7—Lower docking reinforcement of the hull shape, 8—Hall beam assembly of the hull shape, 9—Upper docking reinforcement of the hull shape, 10—Leading edge of the elevated structure outside the cabin, 11—Rearing edge of the elevated structure outside the cabin, 12—Forward fairing of the hull shape, 13—Rear fairing of the hull shape, 14—Positive and negative fairings of the hull shape, 15—Top fairing of the hull shape, 16—Positive and negative fairings of the elevated structure outside the cabin, 17—Horizontal beam between the vertical beams of the elevated structure outside the cabin. Detailed Implementation
[0023] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.
[0024] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are based on the orientation or positional relationships in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or case referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.
[0025] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.
[0026] Example 1:
[0027] An overhead electronic array configuration device for an aircraft fuselage includes an internal assembly, an external assembly, and a boat-shaped assembly. The internal assembly is arranged within the fuselage skin of the aircraft, and it transmits the structural forces above it to the floor beams and the bottom of the aircraft. The external assembly is connected to the upper part of the internal assembly. The external assembly is a rectangular structure with a directional layout, and it has leading and trailing edges at its front and rear ends. The upper end of the external assembly is connected to the boat-shaped assembly, which is boat-shaped and symmetrical in all directions. Electronic arrays are arranged in the front, rear, left, right, and top of the boat-shaped assembly. Electronic arrays are also arranged in the left and right sides of the external assembly.
[0028] The cabin assembly includes a reinforcing frame 1, a docking joint 2, and an upper cabin docking reinforcement 3. The reinforcing frame 1 is a near-circular frame structure with the same curvature as the fuselage surface. Four reinforcing frames 1 are respectively located at the front two positions and the rear two positions of the aircraft fuselage and fit into the interior of the fuselage. The bottom of each reinforcing frame 1 is connected to the aircraft floor and floor beam through its respective docking joint 2. The reinforcing frames 1 at the front two positions are connected to the upper cabin docking reinforcement 3 at the front, and the reinforcing frames 1 at the rear two positions are connected to the upper cabin docking reinforcement 3 at the rear.
[0029] The upper docking reinforcement 3 inside the cabin is a reinforced structural component with the same curvature as the top of the fuselage; the upper docking reinforcement 3 inside the cabin, the reinforcement frame 1 and the docking joint 2 distribute the load transmitted from the top to the fuselage skin, stringers and floor beams, so as to achieve force transmission and balance.
[0030] The external assembly includes an external lower end docking reinforcement 4, an external vertical beam assembly 5, and an external upper end docking reinforcement 6. The two external lower end docking reinforcements 4 are respectively connected to the front and rear ends of the internal assembly. The external upper end docking reinforcements 6 are respectively connected to the front and rear ends of the ship assembly. The external vertical beam assembly 5 is supported between the external lower end docking reinforcements 4 and the external upper end docking reinforcements 6. The front end of the external vertical beam assembly 5 is provided with an external elevated front edge 10, and the rear end of the external vertical beam assembly 5 is provided with an external elevated rear edge 11.
[0031] There are eight external beam assemblies 5, which are respectively located on the left and right sides of the four reinforcing frames 1. A horizontal beam 17 is provided between two external beam assemblies 5 that are opposite each other on the left and right sides.
[0032] The left and right sides of the external assembly are respectively provided with external elevated frame left and right side rectifiers 16. The external elevated frame left and right side rectifiers 16 are specifically located between the front and rear two external vertical beam assemblies. Electronic arrays are installed in the internal space of the eight external vertical beam assemblies 5 and transmit and receive signals to the outside through the external elevated frame left and right side rectifiers 16. The space between the front edge 10 of the external elevated frame and the front external vertical beam assembly 5, and the space between the rear edge 11 of the external elevated frame and the front external vertical beam assembly 5 are the installation space for cables and liquid cooling systems.
[0033] The hull-shaped assembly includes a lower hull-shaped docking reinforcement 7, a hull-shaped vertical beam assembly 8, a upper hull-shaped docking reinforcement 9, a forward hull-shaped fairing 12, a rear hull-shaped fairing 13, port and starboard hull-shaped fairings 14, and a top hull-shaped fairing 15. The lower hull-shaped docking reinforcement 7 is connected to the top of the external assembly. The lower hull-shaped docking reinforcement 7 is connected to the upper hull-shaped docking reinforcement 9 through the port and starboard vertical beam assembly 8 to form a roughly square-shaped reinforced frame. The forward hull-shaped fairing 12, a rear hull-shaped fairing 13, the two port and starboard hull-shaped fairings 14, and the top hull-shaped fairing 15 are respectively located at the front, rear, left, right, and top of the reinforced frame to form a hull-shaped structure. An electronic array is arranged inside the hull-shaped assembly, and the electronic array transmits and receives signals through the five fairings of the hull-shaped assembly.
[0034] The loads of the hull assembly are distributed to the fuselage skin, stringers, and floor beams through the external and internal assemblies, achieving force transmission and balance.
[0035] Example 2:
[0036] like Figure 1 As shown, an elevated electronic array configuration device for an aircraft is provided. The device mainly includes: 4 reinforcing frames 1; 8 docking joints 2; 4 upper docking reinforcements inside the cabin 3; 2 lower docking reinforcements outside the cabin 4; 8 external vertical beam assemblies 5; 2 upper docking reinforcements outside the cabin 6; lower docking reinforcements of the boat-shaped structure 7; 8 vertical beam assemblies of the boat-shaped structure 8; upper docking reinforcements of the boat-shaped structure 9; leading edge of the elevated structure outside the cabin 10; trailing edge of the elevated structure outside the cabin 11; forward fairing of the boat-shaped structure 12; rear fairing of the boat-shaped structure 13; left and right side fairings of the boat-shaped structure 14; top fairing of the boat-shaped structure 15; left and right side fairings of the elevated structure outside the cabin 16; and horizontal beams between the vertical beams of the elevated structure outside the cabin 17.
[0037] An aircraft elevated electronic array configuration device mainly comprises three parts: an internal assembly, an external assembly, and a ship-shaped assembly.
[0038] Interior assembly design. The interior assembly consists of four main components: a reinforcing frame 1, eight docking joints 2, and four upper interior docking reinforcements 3. Reinforcing frame 1, docking joints 2, and upper interior docking reinforcements 3 are all integral aluminum alloy reinforcements, machined. Reinforcing frame 1 and docking joints 2 are bolted to the aircraft floor and floor beams; reinforcing frame 1 and upper interior docking reinforcements 3 are also bolted together. The reinforcing frame 1, docking joints 2, and upper interior docking reinforcements 3 form the interior assembly, distributing external loads to the fuselage skin, stringers, and floor beams, achieving force transmission and balance. See [link / reference]. Figure 1 Section AA and view from direction B.
[0039] Design of the external assemblies. The external assemblies mainly consist of two lower external assemblies (4), eight external vertical beam assemblies (5), two upper external assemblies (6), the leading edge of the external elevated structure (10), the trailing edge of the external elevated structure (11), two left and right side rectifier wave-transmitting domes of the external elevated structure (16), and two horizontal beams between the vertical beams of the external elevated structure (17). Among them, the lower external assemblies (4), the upper external assemblies (6), and the horizontal beams between the vertical beams of the external elevated structure (17) are integral aluminum alloy reinforcements, machined. The external vertical beam assemblies (5) are I-beam profiles, connected to the lower external assemblies (4) and the upper external assemblies (6) with bolts to form the main force transmission frame of the external structure. The leading edge 10 and trailing edge 11 of the external elevated structure are bent LY12-M-δ1.0 aluminum alloy plates, serving as front and rear straighteners. They are detachably connected to the external vertical beam assembly 5 using screws. The internal space of the leading edge 10 and trailing edge 11 provides installation and maintenance space for cable, liquid cooling, and other systems. A horizontal beam 17 with a positioning dimension of h (mm) is designed between the left and right external vertical beam assemblies 5 to ensure the stability of the external vertical beam assembly 5. The left and right side rectifier wave shields 16 of the external elevated structure are made of composite wave-transparent material and are detachably connected to the external vertical beam assembly 5 using screws. Electronic arrays are arranged inside, and the electronic arrays are externally mounted for maintenance. The following components form the external assembly: 4. Lower external docking reinforcement; 5. External vertical beam assembly; 6. Upper external docking reinforcement; 10. Leading edge of external elevated structure; 11. Aft edge of external elevated structure; 16. Left and right side fairings of external elevated structure; 17. Horizontal beam between external elevated structure vertical beams. The external assembly has external dimensions of d (length) × e (width) × f (height) (mm). The loads of the upper hull assembly are distributed to the fuselage skin, girder, and floor beams through the external assembly, achieving force transfer and balance. See [link / reference] Figure 1 AA section.
[0040] Ship-shaped assembly design. The ship-shaped assembly mainly consists of the lower end docking reinforcement 7, eight ship-shaped vertical beam assemblies 8, the upper end docking reinforcement 9, the forward fairing 12, the aft fairing 13, the port and starboard fairings 14, and the top fairing 15. Among them, the lower end docking reinforcement 7 and the upper end docking reinforcement 9 are integral aluminum alloy reinforcements, machined. The vertical beam assembly 8 is an "I" profile, connected to the lower end docking reinforcement 7 and the upper end docking reinforcement 9 with bolts, forming the main force transmission skeleton of the ship-shaped assembly. The forward turret 12, aft turret 13, port and starboard turret 14, and top turret 15 of the hull shape are made of composite wave-transparent material. They are detachably connected to the lower end reinforcement 7, a total of 8 hull-shaped vertical beam assemblies 8, and the upper end reinforcement 9 of the hull shape via screws. Internally, they house electronic arrays, cables, and a liquid cooling system. The electronic arrays are externally mounted for maintenance. The hull-shaped assembly is formed by the lower end reinforcement 7, the 8 hull-shaped vertical beam assemblies 8, the upper end reinforcement 9, the forward turret 12, the aft turret 13, the port and starboard turret 14, and the top turret 15. The positioning dimension of the hull-shaped assembly is g (mm), and the overall dimensions are a (length) × b (width) × c (height) (mm). The loads of the hull assembly are distributed to the fuselage skin, girder, and floor beams through the external and internal assemblies, achieving force transfer and balance. See Figure 1 Section AA and view from direction B.
[0041] Different electronic arrays can be arranged inside the forward fairing 12, aft fairing 13, port and starboard fairings 14, top fairing 15, and port and starboard fairings 16 on the external overhead structure. These fairings are designed to meet mission power, transmittance, and other specifications, enabling various electronic reconnaissance, surveillance, jamming, and early warning missions. All electronic arrays are externally installed and maintained.
[0042] To ensure the normal operation of various electronic arrays, power and liquid cooling functions are provided for them, and the installation and maintenance space for the mission system's power and liquid cooling systems is required. The power and liquid cooling systems can be installed and maintained through the space between the leading edge 10 and the trailing edge 11 of the external overhead frame, or between the external vertical beam assembly 5. The power and liquid cooling systems pass through the aircraft's airtight lines (skin) and use conventional airtight devices to ensure the aircraft's airtightness.
[0043] This invention belongs to the field of aviation technology and relates to an elevated electronic array configuration device for aircraft. The invention mainly comprises internal components, external components, and a boat-shaped component. This device elevates the electronic array high above the fuselage, reducing obstruction of the electronic array by the fuselage, wings, tail, and other aircraft structures. By elevating the electronic array, it forms six electronic arrays (front / rear, top / bottom, left / right), solving the limitation of the electronic array beam emission angle and achieving 360° operation. This meets the requirements of mission systems, expands the electronic array installation methods, increases the number of electronic arrays installed on the aircraft, and improves the overall performance of the aircraft. Its design and layout are reasonable, with direct force transmission, and good manufacturability and maintainability.
[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.
Claims
1. A device for mounting an electronic array on an aircraft fuselage, characterized in that, It includes an internal assembly, an external assembly, and a hull-shaped assembly. The internal assembly is located within the aircraft's fuselage skin. The internal assembly transmits the structural forces from above to the aircraft's floor beams and bottom. The external assembly is connected to the internal assembly. The external assembly is a rectangular structure with a directional layout. The front and rear ends of the external assembly have leading and trailing edges. The upper end of the external assembly is connected to the hull-shaped assembly. The hull-shaped assembly is hull-shaped and symmetrical from front to back and left to right. Electronic arrays are located in the front, back, left, right, and top of the hull-shaped assembly. Electronic arrays are also located in the left and right sides of the external assembly. The cabin assembly includes a reinforcing frame (1), a docking joint (2), and an upper docking reinforcement (3). The reinforcing frame (1) is a near-circular frame structure with the same curvature as the fuselage surface. The four reinforcing frames (1) are respectively located at the front two positions and the rear two positions of the aircraft fuselage and fit into the interior of the fuselage. The bottom of each reinforcing frame (1) is connected to the aircraft floor and floor beam through its respective docking joint (2). The reinforcing frames (1) at the front two positions are connected to the upper docking reinforcement (3) at the front of the cabin, and the reinforcing frames (1) at the rear two positions are connected to the upper docking reinforcement (3) at the rear of the cabin.
2. The aircraft airframe mounted electronic array configuration device according to claim 1, characterized in that, The upper docking reinforcement (3) inside the cabin is a reinforced structural component with the same curvature as the top of the fuselage; the upper docking reinforcement (3), the reinforcing frame (1) and the docking joint (2) inside the cabin spread the load transmitted from the top to the fuselage skin, stringers and floor beams to achieve force transmission and balance.
3. The aircraft airframe mounted electronic array configuration device according to claim 1, characterized in that, The external assembly includes an external lower end docking reinforcement (4), an external vertical beam assembly (5), and an external upper end docking reinforcement (6). The two external lower end docking reinforcements (4) are respectively connected to the front and rear ends of the internal assembly. The external upper end docking reinforcement (6) is respectively connected to the front and rear ends of the ship assembly. The external vertical beam assembly (5) is supported between the external lower end docking reinforcement (4) and the external upper end docking reinforcement (6). The front end of the external vertical beam assembly (5) is provided with an external elevated front edge (10), and the rear end of the external vertical beam assembly (5) is provided with an external elevated rear edge (11).
4. The aircraft airframe mounted electronic array configuration device according to claim 3, characterized in that, There are eight external beam assemblies (5). The eight external beam assemblies (5) are respectively located on the left and right sides of the four reinforcing frames (1). A horizontal beam (17) is provided between two external beam assemblies (5) that are opposite each other on the left and right sides.
5. The aircraft airframe mounted electronic array configuration device according to claim 4, characterized in that, The left and right sides of the external assembly are respectively provided with the left and right side rectifiers (16) of the external elevated structure. The left and right side rectifiers (16) of the external elevated structure are specifically located between the front and rear two external beam assemblies. The electronic array is installed in the internal space of the eight external beam assemblies (5) and transmits and receives signals to the outside through the left and right side rectifiers (16) of the external elevated structure. The space between the front edge (10) of the external elevated structure and the front external beam assembly (5) and the space between the rear edge (11) of the external elevated structure and the front external beam assembly (5) are the installation space for cables and liquid cooling systems.
6. The aircraft airframe mounted electronic array configuration device according to claim 1, characterized in that, The hull-shaped assembly includes a lower hull-shaped docking reinforcement (7), a hull-shaped vertical beam assembly (8), a upper hull-shaped docking reinforcement (9), a forward hull-shaped fairing (12), a rear hull-shaped fairing (13), left and right hull-shaped fairings (14), and a top hull-shaped fairing (15). The lower hull-shaped docking reinforcement (7) is connected to the top of the outer hull assembly. The lower hull-shaped docking reinforcement (7) is connected to the upper hull-shaped docking reinforcement (9) through the hull-shaped vertical beam assembly (8) to form a square-shaped reinforced frame. The forward hull-shaped fairing (12), the rear hull-shaped fairing (13), the two left and right hull-shaped fairings (14), and the top hull-shaped fairing (15) are respectively located at the front, rear, left, right, and top of the reinforced frame to form a hull-shaped structure. An electronic array is arranged inside the hull-shaped assembly. The electronic array transmits and receives signals through the five fairings of the hull-shaped assembly.
7. The aircraft airframe mounted electronic array configuration device according to claim 1, characterized in that, The loads of the hull assembly are distributed to the fuselage skin, stringers, and floor beams through the external and internal assemblies, achieving force transmission and balance.