Aircraft back large array plane mounting structure

Abstract

The invention belongs to the technical field of aviation, and relates to an aircraft back large array plane mounting structure. Comprising a wave-transparent radome (1), an array plane antenna mounting platform (2) and an array plane antenna (3), the array plane antenna mounting platform (2) is made of a pre-stretching plate 7075-T7451-delta material, the whole array plane antenna mounting platform (2) is machined and formed by a numerical control machine tool, the inner shape of the array plane antenna mounting platform (2) is attached to the outer shape of the upper portion of an aircraft skin, and the upper surface of the array plane antenna mounting platform (2) is a plane; the array antenna mounting platform (2) is fixedly connected with an aircraft skin through the platform connecting bolt supporting plate nut standard component (5); the array antenna (3) is mounted on the upper surface of the array antenna mounting platform (2); the shape of the rectification wave-transparent cover (1) is symmetrical to the symmetrical center line of the airplane.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to a large array surface installation structure on the back of an aircraft. Background Art

[0002] In modern aircraft use, large arrays are required to be installed to meet the requirements of large-size installation, viewing angle, function, etc. These requirements put forward higher requirements on the aircraft platform. Only large and medium-sized aircraft can meet the installation requirements of large arrays. At the same time, it causes the load of large and medium-sized aircraft to increase, and the aerodynamic resistance of the aircraft increases, which affects the comprehensive performance of the aircraft. Summary of the invention

[0003] Purpose of the invention: To provide a large array surface mounting structure on the back of an aircraft, which overcomes the problem of large array surface size, heavy weight and large aerodynamic resistance in the large array surface mounting structure.

[0004] Technical solution:

[0005] A large array surface mounting structure on the back of an aircraft comprises: a wave-transmitting radome 1, an array surface antenna mounting platform 2, and an array surface antenna 3, wherein the array surface antenna mounting platform 2 is made of a pre-stretched plate 7075-T7451-δ material and is formed as a whole by numerical control machine tools, the inner shape of the array surface antenna mounting platform 2 is in line with the outer shape of the upper part of the aircraft skin, and the upper surface of the array surface antenna mounting platform 2 is a plane; the array surface antenna mounting platform 2 is connected and fixed to the aircraft skin through a platform connecting bolt support plate nut standard part 5; the array surface antenna 3 is mounted on the upper surface of the array surface antenna mounting platform 2; the outer shape of the rectifying wave-transmitting radome 1 is symmetrical to the symmetric center line of the aircraft.

[0006] Furthermore, the minimum thickness g of the array antenna mounting platform 2 is less than 2 mm.

[0007] Furthermore, corresponding openings for installation and maintenance of equipment such as cables, plugs, and liquid cooling are provided on the array antenna installation platform 2 and the fuselage skin for installation and maintenance of equipment.

[0008] Furthermore, the upper plane of the array antenna installation platform 2 is subjected to a surface treatment.

[0009] Furthermore, the array antenna 3 is connected to the array antenna mounting platform 2 via the array connection bolt support plate nut standard parts 4.

[0010] Furthermore, the rectifying and wave-transmitting cover 1 is a multi-layer glass fiber reinforced plastic structure, and is formed in one step by using a special mold, vacuum ply bonding, and high-temperature curing.

[0011] Furthermore, a layer of conductive glue is coated between the upper surface of the array antenna mounting platform 2 and the array antenna 3 .

[0012] Furthermore, the fairing and wave-transmitting cover 1 and the fuselage skin are connected and fixed by fuselage connecting bolts, support plates and nuts standard parts 6 .

[0013] Beneficial effects:

[0014] The present invention provides a large array installation structure on the back of an aircraft. By arranging the large array on the back of a large or medium-sized aircraft where the space allows, the use requirements of large-size installation, viewing angle, function, etc. of the large array are met. The present invention overcomes the impact on the weight and aerodynamics of the aircraft caused by the installation of a large array, and adopts reasonable arrangement, optimized weight reduction, aerodynamic drag reduction and other means to realize the array function, reduce the impact on the comprehensive performance of the aircraft, and meet the use requirements of the airborne and mission systems. It has a reasonable layout and good processability and maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the installation structure layout of a large array on the back of an aircraft;

[0016] Figure 2 It is a schematic diagram of direction A;

[0017] Figure 3 It is the BB view;

[0018] Figure 4 This is a detailed drawing of FIG.

[0019] Among them: 1. Wave-transmitting antenna cover; 2. Array antenna mounting platform; 3. Array antenna; 4. Array connecting bolts, support plate and nut standard parts; 5. Platform connecting bolts, support plate and nut standard parts; 6. Cover body connecting bolts, support plate and nut standard parts. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0021] In the description of the present invention, it is necessary to understand that the terms "center", "axial", "vertical", "up", "down", "upper end", "bottom end", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present invention.

[0022] The present application provides a large array installation structure on the back of an aircraft. By arranging the large array in the open area at the rear of the aircraft back, the array can meet the requirements of several meters of large-scale installation, viewing angle, function, etc. The present invention overcomes the shortcomings of the large array installation structure, such as large array size, heavy weight, and large aerodynamic resistance. Through optimized design, the problem of large array installation is solved, weight is reduced, aerodynamic drag is reduced, and the requirements of airborne and mission systems are met.

[0023] like Figure 1 , Figure 2 As shown, a large array mounting structure on the back of an aircraft is provided. The device mainly comprises: a wave-transmitting radome 1; an array antenna mounting platform 2; an array antenna 3; an array connection bolt, support plate, and nut standard part 4; a platform connection bolt, support plate, and nut standard part 5; and a cover body connection bolt, support plate, and nut standard part 6.

[0024] Design of array antenna mounting platform 2. The structural material of array antenna mounting platform 2 is pre-stretched plate 7075-T7451-δ material, which is processed and formed by CNC machine tools. The inner shape of array antenna mounting platform 2 fits the outer shape of the upper part of the aircraft skin. The upper surface of array antenna mounting platform 2 is flat and is used to install array antenna 3. The size of array antenna mounting platform 2 after processing is a×b×emm (length×width×thickness), where the minimum thickness is g, g is greater than or equal to 2mm, see Figure 2 Since the array antenna 3 is several meters long and wide, and the size is large, in order to reduce the weight of the array antenna installation platform 2 as a whole, the left and right sides of the array antenna installation platform 2 are processed by CNC machine tools to form inner grooves, one side is flat, and the other side is a skin shape, with dimensions j and h (typical), see Figure 3 At the same time, the array antenna installation platform 2 and the fuselage skin are provided with corresponding openings for installation and maintenance of cables, plugs, liquid cooling and other equipment, which facilitates the installation and maintenance of equipment. The array antenna installation platform 2 is connected and fixed to the surrounding structures such as the aircraft skin with 22 platform connection bolts, support plates and nuts standard parts 5 to form an installation and fixing platform for the array antenna 3.

[0025] The finished product of the array antenna 3 is installed. After the upper plane of the array antenna installation platform 2 is subjected to surface treatment (removing the metal protection treatment), a layer of conductive glue is applied to the upper plane of the array antenna installation platform 2 to ensure the conductivity requirements between the array antenna 3 and the array antenna installation platform 2. The finished product of the array antenna 3 is connected and fixed with 22 array connection bolts, support plates and nuts standard parts 4.

[0026] Design of the rectifying wave-transparent cover 1. The overall dimensions of the rectifying wave-transparent cover 1 are c×d×kmm (length×width×height). The shape of the rectifying wave-transparent cover 1 is symmetrical with the center line of symmetry of the aircraft. The minimum dimension of the inner shape and the array antenna 3 is fmm, and f is greater than or equal to 60mm. The transition length dimension between the front and rear ends of the rectifying wave-transparent cover 1 is tmm, and the ratio of t / c is less than or equal to 0.25. The angle between the upper plane of the rectifying wave-transparent cover 1 and the left and right sides is β°, 45°≤β°≤65°. The interior meets the requirements of the installation and maintenance space, and it plays the role of rectifying and transmitting waves. The rectifying wave-transparent cover 1 is a multi-layer fiberglass structure, using a special mold, vacuum ply bonding, and high-temperature curing for one-time molding. The design of the rectifying wave-transparent cover 1 meets its own strength and rigidity requirements, and meets the requirements of the array antenna 3 for wave transmission and anti-burning performance indicators. During installation, the surface of the contact area between the fuselage skin and the rectifying wave shield 1 is first treated (metal protection treatment is removed), and then a layer of conductive glue is applied to the treated area of ​​the fuselage skin to ensure the conductivity requirements between the rectifying wave shield 1 and the fuselage skin. The rectifying wave shield 1 and the fuselage skin are connected and fixed by 52 fuselage connection bolts, support plates and nuts standard parts 6. The above technical solution realizes a large-scale array installation structure on the back of an aircraft.

[0027] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A large array mounting structure on the back of an aircraft, characterized in that: include: A wave-transmitting radome (1), an array antenna mounting platform (2), and an array antenna (3), wherein the array antenna mounting platform (2) is made of a pre-stretched plate 7075-T7451-δ material and is formed as a whole by a numerical control machine tool; the inner shape of the array antenna mounting platform (2) fits the outer shape of the upper part of the aircraft skin, and the upper surface of the array antenna mounting platform (2) is a plane; the array antenna mounting platform (2) is connected and fixed to the aircraft skin through a platform connection bolt support plate nut standard part (5); the array antenna (3) is mounted on the upper surface of the array antenna mounting platform (2); and the outer shape of the rectifying wave-transmitting radome (1) is symmetrical to the symmetry center line of the aircraft.

2. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: The minimum thickness of the array antenna installation platform (2) is less than 2 mm.

3. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: The array antenna installation platform (2) and the fuselage skin are provided with corresponding openings for installation and maintenance of equipment such as cables, plugs, and liquid cooling, which are used for installation and maintenance of equipment.

4. The large array mounting structure on the back of an aircraft according to claim 1, characterized in that: The upper plane of the array antenna installation platform (2) is subjected to a surface treatment.

5. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: The array antenna (3) is connected to the array antenna installation platform (2) via an array connection bolt support plate nut standard part (4).

6. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: The rectifier wave-transmitting cover (1) is a multi-layer glass fiber reinforced plastic structure, adopts a special mold, vacuum ply bonding, and high-temperature curing to form it in one step.

7. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: A layer of conductive glue is coated between the upper surface of the array antenna installation platform (2) and the array antenna (3).

8. The large array installation structure on the back of an aircraft according to claim 1, characterized in that: The fairing wave-transmitting cover (1) and the fuselage skin are connected and fixed by fuselage connecting bolts, support plates and nut standard parts (6).

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