Airplane four-side array configuration device

Abstract

The invention belongs to the technical field of aviation, and relates to an aircraft four-side array configuration device. Comprising an in-cabin assembly, an out-cabin assembly and a disc assembly, the in-cabin assembly diffuses an out-cabin load to fuselage skin, a stringer, a floor cross beam and a floor lower frame edge, and force transmission and balance are achieved; the extra-cabin assembly diffuses the load of the upper disc assembly to the fuselage skin, the stringer and the floor cross beam through the extra-cabin assembly, so that force transmission and balance are achieved; the disc assembly diffuses loads to fuselage skins, stringers and floor cross beams through the outboard assembly, and force transmission and balance are achieved.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to an aircraft four-sided array configuration device. Background Art

[0002] Currently, arrays are mostly installed on the outer surface of the fuselage in front, behind, left and right. The existing single-sided single array can only radiate or receive in a certain direction. Therefore, the traditional technology of installing arrays on the outer surface of the fuselage is difficult to meet the requirements. Summary of the invention

[0003] Purpose of the invention: To provide an aircraft four-sided array configuration device, by installing the array surface at a high position outside the fuselage, the shielding of the array surface by aircraft structures such as the fuselage, wings and tail is reduced.

[0004] Technical solution:

[0005] An aircraft four-sided array configuration device comprises: an in-cabin assembly, an out-cabin assembly and a disc assembly, wherein:

[0006] The inboard assembly diffuses the extravehicular load to the fuselage skin, long stringers, floor beams and underfloor frame edge, achieving force transfer and balance; the outboard assembly diffuses the load of the upper disc assembly to the fuselage skin, long stringers and floor beams through the outboard assembly, achieving force transfer and balance; the disc assembly diffuses the load to the fuselage skin, long stringers and floor beams through the outboard assembly, achieving force transfer and balance.

[0007] Furthermore, the cabin assembly includes a reinforcement frame 1, a docking joint 2, and an upper cabin docking reinforcement 3, wherein the reinforcement frame 1 and the docking joint 2 are connected to the aircraft floor and the floor beam by bolts; the reinforcement frame 1 and the upper cabin docking reinforcement 3 are connected by bolts; the reinforcement frame 1 is laterally riveted to the fuselage skin and the long stringer.

[0008] Further, the outboard assembly includes: an outboard lower end docking reinforcement 4, an outboard beam assembly 5, an outboard upper end docking reinforcement 6, an outboard elevated horizontal beam 21, an outboard elevated front edge 22, an outboard elevated rear edge 23, and an outboard elevated skin 24 on both sides, wherein the outboard lower end docking reinforcement 4 is located outside the aircraft skin, and is connected to the inboard upper docking reinforcement 3, the outboard beam assembly 5, the aircraft skin and the frame edge with bolts; the outboard beam assembly 5 is a "work The outer upper end docking reinforcement 6 is located under the disc assembly and is connected to the outer beam assembly 5 and the lower end docking integral basin-shaped member 7 by bolts; the front edge 22 and the rear edge 23 of the outer elevated frame are connected to the outer beam assembly 5 by screws; the skins 24 on both sides of the outer elevated frame are detachably connected to the outer beam assembly 5 by screws, and cables are arranged inside.

[0009] Further, the disc assembly comprises: an integral basin-shaped member 7 butted against the lower end of the disc, an integral basin-shaped member 8 butted against the upper end of the disc, a longitudinal profile 9 on the integral basin-shaped member butted against the upper and lower ends of the disc, a longitudinal profile 10, a longitudinal profile 11, a transverse profile 12 on the integral basin-shaped member butted against the upper and lower ends of the disc, a transverse profile 13, a lateral web 14, a Z-shaped profile 15, a lateral inner right-angle profile 16, an array surface 17, and a rectifying and wave-transmitting cover 18, wherein the integral basin-shaped member 7 butted against the lower end of the disc is connected to the reinforcement member 6, the lateral web 14, the Z-shaped profile 15, and the lateral inner right-angle profile 16 at the upper end of the cabin by bolts; the lateral web 14, the Z-shaped profile 15, and the lateral inner right-angle profile 16 at the upper end of the disc are connected to the reinforcement member 6, the lateral web 14, the Z-shaped profile 15, and the lateral inner right-angle profile 16 at the upper end of the cabin by bolts; The plate 14 is connected to the integral basin-shaped part 7 at the lower end of the disk by rivets; the upper end of the disk is connected to the integral basin-shaped part 8, the Z-shaped profile 15, and the lateral inner right-angle profile 16; the Z-shaped profile 15 is connected to the integral basin-shaped part 7 at the lower end of the disk, the integral basin-shaped part 8 at the upper end of the disk, the lateral web 14, and the lateral inner right-angle profile 16 by rivets; a total of 4 array surfaces 17 are connected and fixed to the Z-shaped profile 15 through standard parts to form 4 array surfaces; a total of 4 rectifying and wave-transparent covers 18 are located outside the array surface 17, and the rectifying and wave-transparent covers 18 are connected to the integral basin-shaped part 7 at the lower end of the disk and the integral basin-shaped part 8 at the upper end of the disk.

[0010] Furthermore, the reinforcement frame 1, the docking joint 2, and the upper docking reinforcement 3 inside the cabin are integral aluminum alloy reinforcements that are machined, and the lower end docking reinforcement 4 outside the cabin, the upper end docking reinforcement 6 outside the cabin, and the horizontal beam 21 between the elevated beams outside the cabin are integral aluminum alloy reinforcements that are machined.

[0011] Furthermore, the front edge 22 of the external elevated frame, the rear edge 23 of the external elevated frame, and the skins 24 on both sides of the external elevated frame are LY12-M-δ1.0 aluminum alloy plate bent parts.

[0012] Furthermore, an external elevated inter-beam horizontal beam 21 is provided between the external beam assemblies 5 , and the external elevated inter-beam horizontal beam 21 is connected to the external beam assemblies 5 by bolts.

[0013] Furthermore, the material of the skin 24 on both sides of the cabin overhead frame is LY12-M-δ1.0 aluminum alloy plate bent parts.

[0014] Furthermore, the rectifying and wave-transmitting cover 18 is made of a glass fiber reinforced plastic composite material, which plays the role of rectifying and transmitting waves.

[0015] Furthermore, the disk is formed by combining a rectifying and wave-transmitting cover 18 .

[0016] Beneficial effects:

[0017] The present invention provides an aircraft four-sided array configuration device. By installing the array surface at a high position outside the fuselage, the array surface is raised high, and the problem of the aircraft structure such as the fuselage, wing, and tail shielding the array surface is reduced. By raising the array surface to form four array surfaces, the limitation of the array surface beam emission angle is solved, the requirement of 360° use of the system array surface is achieved, and the overall comprehensive use performance of the aircraft is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of a four-sided array configuration device for an aircraft;

[0019] Figure 2 It is a schematic diagram of the AA section;

[0020] Figure 3 It is a schematic diagram of direction B;

[0021] Figure 4 It is a schematic diagram of the C direction;

[0022] Figure 5 It is a schematic diagram of D direction;

[0023] Figure 6 It is a schematic diagram of E direction;

[0024] Figure 7 It is a schematic diagram of FF;

[0025] Figure 8 This is a schematic diagram of GG.

[0026] Among them: 1. Reinforcement frame (4 pieces in total); 2. Butt joint (8 pieces in total); 3. Upper butt reinforcement inside the cabin (4 pieces in total); 4. Lower butt reinforcement outside the cabin (1 piece); 5. Vertical beam assembly outside the cabin (8 pieces in total); 6. Upper butt reinforcement outside the cabin (1 piece in total); 7. Butt integral basin-shaped part at the lower end of the disc (1 piece); 8. Butt integral basin-shaped part at the upper end of the disc (1 piece); 9. Longitudinal profiles on the upper and lower ends of the disc butt integral basin-shaped part (20 pieces in total); 10. Longitudinal profiles (4 pieces in total); 11. Longitudinal profiles (4 pieces in total); 12. Horizontal profiles on the upper and lower ends of the disc butt integral basin-shaped part ( 5 pieces in total); 13. Transverse profiles (2 pieces in total); 14. Lateral webs (4 pieces in total); 15. Z-shaped profiles (40 pieces in total); 16. Lateral inner right-angle profiles (40 pieces in total); 17. Array surfaces (4 pieces in total); 18. Fairing shield (4 pieces in total); 19. Fairing shield support plate nut connection standard parts (several pieces); 20. Fairing shield overlap support plate nut connection standard parts (several pieces); 21. Horizontal beams between vertical beams of the external elevated structure (2 pieces in total); 22. External elevated leading edge (1 piece); 23. External elevated trailing edge (1 piece); 24. External elevated skins on both sides (2 pieces in total). DETAILED DESCRIPTION

[0027] The present invention overcomes the shortcomings of the existing array installation technology and provides an aircraft four-sided array configuration device. The present invention meets the 360° use requirements of the airborne and system arrays. By installing the arrays at a high place outside the fuselage, the problems of the aircraft structures such as the fuselage, wings and tail shielding the arrays are reduced. By raising the arrays to form four arrays in front, back, left and right, the limitation of the electronic array beam emission angle is solved, the 360° use requirements of the arrays are achieved, and the overall comprehensive performance of the aircraft is improved.

[0028] In conjunction with the accompanying drawings, a four-sided array configuration device of an aircraft of the present invention is described in detail:

[0029] According to the instructions Figures 1 to 8 , an aircraft four-sided array configuration device, including: a reinforcement frame (4 pieces in total) 1, a docking joint (8 pieces in total) 2, an upper docking reinforcement member in the cabin (4 pieces in total) 3, a lower end docking reinforcement member outside the cabin (1 piece) 4, an outer beam assembly (8 pieces in total) 5, an upper end docking reinforcement member outside the cabin (1 piece in total) 6, a lower end docking integral basin-shaped member of a circular disc (1 piece) 7, an upper end docking integral basin-shaped member of a circular disc (1 piece) 8, a longitudinal profile on the upper and lower ends of the circular disc butt joint integral basin-shaped member (20 pieces in total) 9, a longitudinal profile (4 pieces in total) 10, a longitudinal profile (4 pieces in total) 11, an upper and lower end docking integral basin-shaped member of a circular disc Transverse profiles (5 pieces in total) 12. Transverse profiles (2 pieces in total) 13. Lateral webs (4 pieces in total) 14. Z-shaped profiles (40 pieces in total) 15. Lateral inner right-angle profiles (40 pieces in total) 16. Array surfaces (4 pieces in total) 17. Fairing shield (4 pieces in total) 18. Fairing shield support plate nut connection standard parts (several pieces) 19. Fairing shield overlap support plate nut connection standard parts (several pieces) 20. Horizontal beams between vertical beams of the external elevated structure (2 pieces in total) 21. External elevated leading edge (1 piece) 22. External elevated trailing edge (1 piece) 23. External elevated skins on both sides (2 pieces in total) 24.

[0030] The aircraft four-sided array configuration device mainly comprises three parts: an in-cabin assembly, an out-cabin assembly and a disc assembly.

[0031] Manufacturing and assembly of cabin assemblies. The cabin assemblies are mainly composed of reinforcement frames (4 pieces in total) 1; butt joints (8 pieces in total) 2; and upper cabin butt reinforcements (4 pieces in total) 3. 1, 2, and 3 are integral aluminum alloy reinforcements, machined. The positioning size of the reinforcement frame is k. The reinforcement frame 1 and the butt joint 2 are connected to the aircraft floor and floor beams by bolts; the reinforcement frame 1 and the upper cabin butt reinforcement 3 are connected by bolts; the reinforcement frame 1 is laterally riveted to the fuselage skin, long stringers and other structural parts. 1, 2, and 3 form an in-cabin assembly, which diffuses the external load to the fuselage skin, long stringers, floor beams and the frame edge under the floor to achieve force transmission and balance. See Figure 1 , AA section.

[0032] Manufacturing and assembly of outboard assemblies. Outboard assemblies are mainly composed of outboard lower end docking reinforcement (1 piece) 4; outboard beam assembly (8 pieces in total) 5; outboard upper end docking reinforcement (1 piece in total) 6; outboard elevated horizontal beam between beams (2 pieces in total) 21; outboard elevated front edge (1 piece) 22; outboard elevated rear edge (1 piece) 23; outboard elevated skin on both sides (2 pieces in total) 24, etc. Among them, 4, 6, and 21 are integral aluminum alloy reinforcements, which are machined. Outboard lower end docking reinforcement (1 piece) 4 is located outside the aircraft skin and is connected to 3, 5, the aircraft skin and the frame edge with bolts. Outboard beam assembly (8 pieces in total) 5 is mainly an "I" shaped profile, which is connected to 4 and 6 with joints and bolts respectively. Outboard upper end docking reinforcement (1 piece in total) 6 is located under the disc assembly and is connected to 5 and 7 with bolts. It forms the main outboard force transmission skeleton. 22 and 23 are LY12-M-δ1.0 aluminum alloy plate bent parts, which play the role of front and rear rectification, and the positioning dimension is q. 22 and 23 are detachably connected to 5 by screws, and the space inside 22 and 23 is the installation and maintenance space for cables, liquid cooling and other systems. A horizontal beam 21 between the cabin external elevated beam assemblies 5 is designed, which is connected to 5 by bolts, and the positioning dimension is h (mm). Its function is to ensure the stability of the cabin external beam assembly 5. The skin 24 on both sides of the cabin external elevated is made of LY12-M-δ1.0 aluminum alloy plate bent parts, which are detachably connected to 5 by screws, and cables, equipment, etc. are arranged inside. The main space inside is the installation, maintenance, and upward climbing space (the passage to enter the disc assembly). 4, 5, 6, 21, 22, 23, 24 form an external cabin assembly, and the overall dimensions are m (length) × j (width) × f (height) (mm). It spreads the load of the upper disk assembly to the fuselage skin, long stringers and floor beams through the outer cabin assembly to achieve force transmission and balance. Figure 1 , AA section, B view.

[0033] Manufacturing and assembly of disc assembly. The disc assembly mainly consists of the lower end of the disc butt joint integral basin-shaped part (1 piece) 7; the upper end of the disc butt joint integral basin-shaped part (1 piece) 8; the upper and lower ends of the disc butt joint integral basin-shaped part on the longitudinal profile (20 pieces in total) 9; the longitudinal profile (4 pieces in total) 10; the longitudinal profile (4 pieces in total) 11; the upper and lower ends of the disc butt joint integral basin-shaped part on the transverse profile (5 pieces in total) 12; the transverse profile (2 pieces in total) 13; the lateral web (4 pieces in total) 14; the Z-shaped profile (40 pieces in total) 15; the lateral inner right-angle profile (40 pieces in total) 16; the array surface (4 pieces in total) 17; the rectifier (4 pieces in total) 18; the rectifier support plate nut connection standard parts (several pieces) 19; the rectifier overlap support plate nut connection standard parts (several pieces) 20, etc. Among them, 7 and 8 are integral aluminum alloy reinforcements, which are machined. The overall dimensions of the butt-jointed integral basin-shaped part 7 at the lower end of the disc are w (length) × w (width) (mm), and a φt installation and maintenance channel is provided in the center, which is connected to parts 6, 14, 15, and 16 by bolts. The overall dimensions of the butt-jointed integral basin-shaped part (1 piece) 8 at the upper end of the disc are w (length) × w (width) (mm), and are connected to parts 14, 15, and 16 by bolts. Parts 9, 10, 11, 12, and 13 are right-angle profiles, which are connected to parts 7 and 8 by bolts. The lateral web (4 pieces in total) 14 is made of LY12-M-δ1.5 aluminum alloy plate, which is connected to parts 7, 8, 15, and 16 by rivets. There are several lightening holes on the lateral web 14 to facilitate the installation of cables and equipment. The Z-shaped profile (40 pieces in total) 15 is a standard "Z"-shaped profile, which is connected to parts 7, 8, 14, and 16 by rivets. The lateral inner right-angle profile (40 pieces in total) 16 is a standard right-angle profile, which is connected with 7, 8, 14, and 15 by rivets to form the main force transmission framework of the square disc assembly.

[0034] The array surface (4 pieces in total) 17 is a finished product, which is connected and fixed with the Z-shaped profile 15 through standard parts to form 4 array surfaces, realizing 360° radiation or receiving functions, and completing various tasks such as reconnaissance, surveillance, interference, and early warning. The rectifying wave-transmitting cover (4 pieces in total) 18 is located outside the array surface 17. The rectifying wave-transmitting cover 18 is a finished product, made of fiberglass composite material, and plays the role of rectifying and transmitting waves. Its design meets the requirements of mission power, wave transmittance and other indicators. The rectifying wave-transmitting cover 18 is connected to the standard parts 19, 20 and 7, 8 with support nuts; the array surface 17 adopts external installation and maintenance. The positioning dimension of the disc assembly is g (mm), and the overall dimension is a (major axis) × b (minor axis) (mm). The disc assembly diffuses the load to the fuselage skin, long stringers and floor beams through the cabin outer assembly to achieve force transmission and balance. See Figure 1 , AA section, B view, C view, D view, E view, FF, GG.

[0035] In order to realize the normal operation of various arrays, power supply and liquid cooling functions are provided for various arrays to meet the requirements of system power supply and liquid cooling installation, maintenance, and personnel passage space. The power supply and liquid cooling system can be installed and maintained through the space between the front edge of the external cabin elevated frame (1 piece) 22; the rear edge of the external cabin elevated frame (1 piece) 23; and the skins on both sides of the external cabin elevated frame (2 pieces in total) 24. The power supply and liquid cooling system pass through the aircraft airtight line (skin) and use conventional airtight devices to ensure the airtightness of the aircraft.

Claims

1. An aircraft four-sided array configuration device, characterized in that: include: In-cabin assembly, out-cabin assembly and disc assembly, wherein: The inboard assembly diffuses the extravehicular load to the fuselage skin, long stringers, floor beams and underfloor frame edge, achieving force transfer and balance; the outboard assembly diffuses the load of the upper disc assembly to the fuselage skin, long stringers and floor beams through the outboard assembly, achieving force transfer and balance; the disc assembly diffuses the load to the fuselage skin, long stringers and floor beams through the outboard assembly, achieving force transfer and balance.

2. The aircraft four-sided array configuration device according to claim 1, characterized in that: The cabin assembly comprises a reinforcement frame (1), a docking joint (2), and an upper cabin docking reinforcement member (3), wherein the reinforcement frame (1) and the docking joint (2) are connected to the aircraft floor and the floor crossbeam by bolts; the reinforcement frame (1) and the upper cabin docking reinforcement member (3) are connected by bolts; and the reinforcement frame (1) is laterally connected to the fuselage skin and the long stringer by riveting.

3. The aircraft four-sided array configuration device according to claim 2, characterized in that: The outer cabin assembly comprises: an outer cabin lower end docking reinforcement (4), an outer cabin vertical beam assembly (5), an outer cabin upper end docking reinforcement (6), an outer cabin elevated vertical beam horizontal beam (21), an outer cabin elevated front edge (22), an outer cabin elevated rear edge (23), and outer cabin elevated side skins (24), wherein the outer cabin lower end docking reinforcement (4) is located outside the aircraft skin, and is connected to the cabin upper docking reinforcement (3), the outer cabin vertical beam assembly (5), the aircraft skin and the frame edge by bolts; the outer cabin vertical beam assembly (5) is in the shape of an "I" character. The profile is connected to the outer lower end docking reinforcement member (4) and the outer upper end docking reinforcement member (6) by joints and bolts respectively; the outer upper end docking reinforcement member (6) is located below the disc assembly and is connected to the outer beam assembly (5) and the disc lower end docking integral basin-shaped member (7) by bolts; the front edge (22) and the rear edge (23) of the outer elevated frame are connected to the outer beam assembly (5) by screws; the skins (24) on both sides of the outer elevated frame are detachably connected to the outer beam assembly (5) by screws, and cables are arranged inside.

4. The aircraft four-sided array configuration device according to claim 3, characterized in that: The disk assembly comprises: an integral basin-shaped member (7) butted against the lower end of the disk, an integral basin-shaped member (8) butted against the upper end of the disk, a longitudinal profile (9) on the integral basin-shaped member butted against the upper and lower ends of the disk, a longitudinal profile (10), a longitudinal profile (11), a transverse profile (12) on the integral basin-shaped member butted against the upper and lower ends of the disk, a transverse profile (13), a lateral web (14), a Z-shaped profile (15), a lateral inner right-angle profile (16), an array surface (17), and a rectifying wave-transmitting cover (18), wherein the integral basin-shaped member (7) butted against the lower end of the disk is connected to a reinforcement member (6) butted against the upper end of the cabin, the lateral web (14), the Z-shaped profile (15), and the lateral inner right-angle profile (16) by bolts; the lateral web (1 4) the integral basin-shaped part (7) is butt-jointed with the lower end of the disk by rivets; the upper end of the disk is butt-jointed with the integral basin-shaped part (8), the Z-shaped profile (15), and the lateral inner right-angle profile (16); the Z-shaped profile (15) is connected with the integral basin-shaped part (7) butt-jointed with the lower end of the disk, the integral basin-shaped part (8) butt-jointed with the upper end of the disk, the lateral web (14), and the lateral inner right-angle profile (16) by rivets; a total of four array surfaces (17) are respectively connected and fixed with the Z-shaped profile (15) by standard parts to form four array surfaces; a total of four rectifying and wave-transparent covers (18) are located outside the array surface (17), and the rectifying and wave-transparent covers (18) are connected with the integral basin-shaped part (7) butt-jointed with the lower end of the disk and the integral basin-shaped part (8) butt-jointed with the upper end of the disk.

5. The aircraft four-sided array configuration device according to claim 4, characterized in that: The reinforcement frame (1), the butt joint (2), and the upper butt reinforcement member (3) inside the cabin are integral aluminum alloy reinforcement members, which are machine-formed, and the lower butt reinforcement member (4) outside the cabin, the upper butt reinforcement member (6) outside the cabin, and the horizontal beam (21) between the elevated vertical beams outside the cabin are integral aluminum alloy reinforcement members, which are machine-formed.

6. The aircraft four-sided array configuration device according to claim 5, characterized in that: The front edge (22) of the external elevated frame, the rear edge (23) of the external elevated frame, and the skins (24) on both sides of the external elevated frame are LY12-M-δ1.0 aluminum alloy plate bent parts.

7. The aircraft four-sided array configuration device according to claim 6, characterized in that: An external elevated inter-beam horizontal beam (21) is arranged between the external beam assemblies (5), and the external elevated inter-beam horizontal beam (21) is connected to the external beam assemblies (5) by bolts.

8. The aircraft four-sided array configuration device according to claim 7, characterized in that: The material of the skins (24) on both sides of the cabin overhead frame is a LY12-M-δ1.0 aluminum alloy plate bent part.

9. The aircraft four-sided array configuration device according to claim 8, characterized in that: The rectifying and wave-transmitting cover (18) is made of a glass fiber reinforced plastic composite material and plays the role of rectifying and transmitting waves.

10. The aircraft four-sided array configuration device according to claim 9, characterized in that: The disk is formed by combining a rectifying and wave-transmitting cover (18).

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