Airtight structure device for embedded antenna array plane of airplane

Abstract

The invention belongs to the technical field of aviation, and relates to an aircraft embedded antenna array plane airtight structure device. Comprising an aircraft skin opening, a frame assembly, an airtight opening frame, an airtight box cover piece and an antenna array plane. According to the device, the array plane is arranged on the side wall plate of the aircraft, and an embedded antenna array plane airtight structure device is designed, so that the aircraft has the characteristics of airtightness, array plane shape preservation, invisibility, no conventional external wave-transparent fairing, direct outward radiation of the array plane and the like, the use requirements of a task system are met, and the comprehensive use performance of the aircraft is improved. The device is reasonable in design and arrangement, direct in force transmission and good in manufacturability and maintainability.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to an aircraft embedded antenna array airtight structure device. Background Art

[0002] The outer surface of the aircraft needs to carry a variety of arrays to complete various reconnaissance, identification, search, surveillance and other tasks. The arrays are mostly installed on the outer surface of the fuselage, mainly including structural parts, antennas, wave-transmitting fairings, etc. They usually protrude from the aircraft shape as a whole, are heavy, and increase aerodynamic resistance. Therefore, in order to solve the shortcomings brought about by the conventional arrangement, an embedded antenna array airtight structure device can be used to reduce the shortcomings of the installation of the array protruding from the aircraft shape, such as increased aerodynamic resistance, and meet the requirements for the installation and use of the mission system array. Summary of the invention

[0003] Purpose of the invention: To provide an airtight structure device for an aircraft embedded antenna array, so as to reduce aerodynamic drag, increase the stealth of the aircraft, and improve the comprehensive performance of the aircraft.

[0004] Technical solution:

[0005] An aircraft embedded antenna array airtight structure device, comprising: an aircraft frame assembly 2, an additional reinforcement frame assembly 3, an airtight opening frame 4, an airtight box cover 5, an external opening cover 6, an antenna array surface 8, an airtight standard component assembly 10, and an airtight standard component assembly 11, wherein the frame edge and the long stringer are segmented within the range of the aircraft skin opening 1 to form segmented aircraft frame assemblies 2 and segmented long stringers, and additional reinforcement frame assemblies 3 are provided at both ends of the long side of the airtight opening frame 4, and the segmented long stringers are respectively connected to the airtight opening frame 4 with joints and bolts, and the aircraft frame assembly 2 and the additional reinforcement frame assembly 3 are respectively riveted to the skin and the airtight opening frame 4 with rivets. The opening on the left side of the airtight frame 4 is the equipment installation and maintenance channel space, and an external cover 6 is designed on the left side. The external cover 6 is connected and fixed to the airtight frame 4 with an airtight standard parts assembly 11. The large opening on the right side of the airtight frame 4 is the antenna array 8 installation and maintenance channel space, and the antenna array 8 is connected and fixed to the airtight frame 4 with an airtight standard parts assembly 10. The airtight frame 4 is connected to the surrounding aircraft skin openings 1, aircraft frame assemblies 2, additional reinforcement frame assemblies 3 and aircraft long stringers with rivets and bolts to form a longitudinal and transverse frame-type airtight structure, and the airtight box cover 5 is connected to the airtight frame 4 with rivets to form an overall airtight device.

[0006] Furthermore, the aircraft skin opening 1 is located at a position on the aircraft side wall panel where an antenna array needs to be arranged.

[0007] Furthermore, the material of the airtight opening frame 4 is 7050-T7451-δ, has a hyperbolic shape, is an integral aluminum alloy reinforcement, and is formed by CNC machining.

[0008] Furthermore, the external cover 6 has a hyperbolic shape, which serves as a rectification, isolation, and installation maintenance channel.

[0009] Furthermore, a rubber plate 7 is provided between the airtight opening frame 4 and the external opening cover 6 .

[0010] Furthermore, the material of the airtight box cover 5 is 7050-T7451-δ, has a hyperbolic shape, is an integral aluminum alloy reinforcement, and is formed by CNC machining.

[0011] Furthermore, a conductive rubber plate 9 is provided between the antenna array surface 8 and the airtight opening frame 4 .

[0012] Furthermore, the conductive rubber plate 9 is made of 89-50182.

[0013] Beneficial effects:

[0014] The present invention provides an aircraft embedded antenna array airtight structure device. By arranging the array surface at the side wall plate of the aircraft and designing the embedded antenna array airtight structure device, the aircraft has the characteristics of airtightness, array surface conformal and stealth, no conventional external wave-transmitting fairing, and the array surface directly radiates outward, etc., which meets the requirements of mission system use and improves the comprehensive use performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the outer side of an aircraft embedded antenna array airtight structure device;

[0016] Figure 2 It is a schematic diagram of the AA section;

[0017] Figure 3 It is a schematic diagram of the BB section;

[0018] Figure 4 It is a schematic diagram of the CC section;

[0019] Figure 5 It is a schematic diagram of the DD section;

[0020] Figure 6 It is a schematic diagram of the airtight opening frame;

[0021] Figure 7 It is a schematic diagram of the airtight box cover;

[0022] Figure 8 It is a schematic diagram of the external cover;

[0023] Fig. 9 Schematic diagram of conductive rubber sheet.

[0024] Among them: 1. Aircraft skin opening; 2. Aircraft frame assembly; 3. Additional reinforcement frame assembly (2 pieces in total); 4. Airtight opening frame; 5. Airtight box cover; 6. External opening cover; 7. Rubber sheet; 8. Antenna array surface; 9. Conductive rubber sheet; 10. Airtight standard parts assembly; 11. Airtight standard parts assembly. DETAILED DESCRIPTION

[0025] The present invention overcomes the shortcomings of existing array surface installation technology and provides an aircraft embedded antenna array surface airtight structure device. The present invention meets the requirements for the use of airborne and mission system array surfaces. By opening holes in the aircraft skin, designing airtight opening frames, airtight box covers, etc., the array surface is installed on the embedded airtight opening frame. The array surface shape is conformal to the aircraft shape, and no conventional wave-transparent fairing design is required. The use requirements of the array surface are solved, which is more conducive to the power radiation of the array surface, reduces aerodynamic drag, increases the stealth of the aircraft, and improves the comprehensive performance of the aircraft.

[0026] like Figures 1 to 9 As shown, an aircraft embedded antenna array airtight structure device is provided. The device mainly includes: an aircraft skin opening 1, an aircraft frame assembly 2, an additional reinforcement frame assembly (2 pieces in total) 3, an airtight opening frame 4, an airtight box cover 5, an external opening cover 6, a rubber plate 7, an antenna array 8, a conductive rubber plate 9, an airtight standard component assembly 10, and an airtight standard component assembly 11.

[0027] like Figure 1 As shown, at the position where the antenna array needs to be arranged on the aircraft side wall panel, an opening 1 is opened in the aircraft skin, and the opening size is a (length) × b (height) (mm), and the positioning dimensions are c (mm) and d (mm) respectively. The frame edge and the long stringer are segmented within the range of the aircraft skin opening 1 to form a segmented aircraft frame assembly 2 and a segmented long stringer. Additional reinforcement frame assemblies (2 pieces in total) 3 are designed to be added at c (mm) and d (mm). The segmented long stringers are bolted to the airtight opening frame 4 with joints. The aircraft frame assembly 2 and the additional reinforcement frame assembly 3 are riveted to the skin, airtight opening frame 4 and other surrounding structural parts with rivets. See Figure 2 , Figure 3 , Figure 4 , Figure 5 .

[0028] Design the airtight opening frame 4. The airtight opening frame 4 is made of 7050-T7451-δ, has a hyperbolic shape, an integral aluminum alloy reinforcement, and is formed by CNC machining. Figure 6The maximum size of the airtight opening frame 4 is e (length) × f (height) (mm). The three openings on the left side of the airtight opening frame 4 are the installation and maintenance passage spaces for cables and other equipment. An external opening cover 6 is designed on the left side. The material of the external opening cover 6 is a LY12-M-δ2.5 aluminum alloy plate bending part. The size is j (length) × k (width) (mm). The external opening cover 6 has a hyperbolic shape and serves as a rectification, isolation, installation and maintenance passage. Figure 8 A rubber sheet 7 is designed between the airtight opening frame 4 and the external opening cover 6. The material is 1150δ1.5. The external opening cover 6 and the airtight opening frame 4 are connected and fixed by an airtight standard component assembly 11. The large opening on the right side is the installation and maintenance channel space for the antenna array 7. The antenna array 7 and the airtight opening frame 4 are connected and fixed by an airtight standard component assembly 10. Figure 5 The airtight opening frame 4 is connected with the surrounding aircraft skin opening 1, aircraft frame assembly 2, additional reinforcement frame assembly 3 and aircraft long stringers by rivets and bolts to form a longitudinal and transverse frame-type airtight structure, and the load generated by the airtight opening frame 4 and the antenna array 7 is transmitted through the fuselage skin, long stringers, aircraft frame assembly 2, and additional reinforcement frame assembly 3 to achieve force transmission and balance. Figure 2 , Figure 4 .

[0029] Design the airtight box cover 5. The material of the airtight box cover 5 is 7050-T7451-δ, with a hyperbolic shape, an integral aluminum alloy reinforcement, and a CNC machine forming process. Figure 7 The maximum size of the airtight box cover 5 is g (length) × h (height) (mm). The airtight box cover 5 is connected to the airtight opening frame 4 by rivets to form an integral airtight device. It plays the role of airtightness and isolation. Figure 3 .

[0030] The antenna array 7 is a finished product. The antenna array 7 and the airtight frame 4 are connected and fixed by an airtight standard component assembly 10. In order to increase the conductivity, a conductive rubber plate 9 is added between the antenna array 7 and the airtight frame 4. The material of the conductive rubber plate 8 is 89-50182, and the size of the conductive rubber plate 8 is m (length) × n (width) (mm), see Fig. 9 The antenna array surface 7 and the airtight opening frame 4 are sealed with a sealant (a small amount) on all sides.

[0031] The main supporting equipment of the antenna array 7, such as the transmitter, is arranged in the aircraft cabin. Figure 1 , from the inner side of the aircraft skin along the E direction, holes are opened on the additional reinforcement frame assembly 3 and the airtight opening frame 4, and the cable passes through the airtight guide sleeve into the airtight opening frame 4 to supply power to the antenna array 7.

[0032] The invention discloses an aircraft embedded antenna array airtight structure device, which has the performances of conformal, stealth and airtightness, and meets the requirements for the use of airborne and mission system arrays.

Claims

1. An aircraft embedded antenna array airtight structure device, characterized in that: include: An aircraft frame assembly (2), an additional reinforcement frame assembly (3), an airtight opening frame (4), an airtight box cover (5), an external opening cover (6), an antenna array surface (8), an airtight standard component assembly (10), and an airtight standard component assembly (11), wherein the frame edge and the long stringer are segmented within the range of the aircraft skin opening (1) to form a segmented aircraft frame assembly (2) and segmented long stringers, and additional reinforcement frame assemblies (3) are provided at both ends of the long side of the airtight opening frame (4), and the segmented long stringers are respectively connected to the airtight opening frame (4) by bolts using joints, and the aircraft frame assembly (2) and the additional reinforcement frame assembly (3) are respectively connected to the skin and the airtight opening frame (4) by riveting, and the left side of the airtight opening frame (4) is connected to the left side of the airtight opening frame (4) by rivets. The opening is a channel space for equipment installation and maintenance. An external cover (6) is designed on the left side. The external cover (6) is connected and fixed to the airtight frame (4) by an airtight standard component assembly (11). The large opening on the right side of the airtight frame (4) is a channel space for antenna array (8) installation and maintenance. The antenna array (8) is connected and fixed to the airtight frame (4) by an airtight standard component assembly (10). The airtight frame (4) is connected to the surrounding aircraft skin opening (1), aircraft frame assembly (2), additional reinforcement frame assembly (3) and aircraft long stringer by rivets and bolts to form a longitudinal and transverse frame-type airtight structure. The airtight box cover (5) is connected to the airtight frame (4) by rivets to form an integral airtight device.

2. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: The aircraft skin opening (1) is located at a position on the aircraft side wall panel where an antenna array needs to be arranged.

3. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: The material of the airtight opening frame (4) is 7050-T7451-δ, has a hyperbolic shape, is an integral aluminum alloy reinforcement, and is formed by CNC machining.

4. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: The external cover (6) has a hyperbolic shape and serves as a rectification, isolation, and installation maintenance channel.

5. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: A rubber plate (7) is provided between the airtight opening frame (4) and the external opening cover (6).

6. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: The material of the airtight box cover (5) is 7050-T7451-δ, has a hyperbolic shape, is an integral aluminum alloy reinforcement, and is formed by CNC machining.

7. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: A conductive rubber plate (9) is arranged between the antenna array surface (8) and the airtight opening frame (4).

8. The aircraft embedded antenna array airtight structure device according to claim 1, characterized in that: The material of the conductive rubber sheet (9) is 89-50182.

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