Multi-array-plane device at top of fuselage and cooperative working method of multiple array planes
By designing a multi-faceted array device on the top of the aircraft fuselage and employing a collaborative working strategy, the problems of multi-directional radiation and reception of the arrays were solved, thereby improving the overall performance of the aircraft and the effectiveness of the mission system.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-26
- Publication Date
- 2026-04-07
AI Technical Summary
The existing single-sided array cannot meet the requirements of modern mission systems for multi-directional radiation and reception, and the traditional fuselage outer surface mounting technology is difficult to balance the functional performance of the array with the structural shielding problem.
Design a multi-array device on the top of an aircraft fuselage, including internal and external components. Through the coordinated work of the external frame support elements and array fairing components, multi-directional radiation and reception can be achieved. The working mode and beam resources of the array are dynamically allocated through a coordinated working strategy.
It fulfills the requirements for multi-directional radiation and reception of the array, improves the overall performance of the aircraft, solves the limitation of the array beam emission angle, and enhances the situational awareness, survivability and strike capability of the carrier aircraft.
Smart Images
Figure CN121799602A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of aircraft avionics, in particular to a multi-array device on the top of an aircraft fuselage and a cooperative working method of multiple arrays. BACKGROUND
[0002] The outer surface of an aircraft carries multiple arrays to complete various tasks such as reconnaissance, identification, search, and surveillance. The arrays are usually installed on the front, back, left, and right outer surfaces of the fuselage. The task arrays usually have radiation installation angles and viewing angle requirements, and the aircraft structure is required to have small shielding to the arrays to maximize the function of the task system. The existing single-sided single array can only radiate or receive in a certain direction. Therefore, the conventional array installation technology on the outer surface of the fuselage cannot meet the use requirements of modern task systems. SUMMARY
[0003] Therefore, the embodiments of the present application provide a multi-array device on the top of an aircraft fuselage and a cooperative working method of multiple arrays to solve the limitation of array beam emission angle, achieve the use requirements of array multi-directional radiation and reception, and improve the overall use performance of the aircraft.
[0004] The embodiments of the present application provide the following technical solutions: A multi-array device on the top of an aircraft fuselage, comprising: an in-cabin assembly and an out-of-cabin assembly, the bottom of the out-of-cabin assembly is fixedly connected to the in-cabin assembly, and the in-cabin assembly is used to transmit the load generated by the out-of-cabin assembly to the fuselage skin, the reinforcement pad, the longeron, the floor beam, and the floor lower frame of the aircraft; the out-of-cabin assembly comprises an out-of-cabin frame support element and an array fairing assembly; the out-of-cabin frame support element comprises an out-of-cabin lower end butt joint reinforcement, and the bottom of the out-of-cabin frame support element is fixed to the fuselage skin and the frame of the top of the aircraft fuselage through the out-of-cabin lower end butt joint reinforcement; the array fairing assembly is fixed on the out-of-cabin frame support element, and the array fairing assembly is used to generate and receive electromagnetic waves for performing reconnaissance, identification, search, and surveillance tasks.
[0005] Further, the out-of-cabin frame support element comprises an out-of-cabin left and right side lower end right-angle profile, an out-of-cabin left and right side lower end T-shaped profile, an out-of-cabin left and right side upper end right-angle profile, an out-of-cabin left and right side upper lower right-angle profile, an out-of-cabin left and right side upper end T-shaped profile, an out-of-cabin top right-angle profile, an out-of-cabin left and right side face T-shaped profile, an out-of-cabin left and right side face web plate, an out-of-cabin top web plate, an out-of-cabin front and rear upper end obtuse angle arc profile, an out-of-cabin front and rear upper lower right-angle arc profile, an out-of-cabin front and rear web plate, and an out-of-cabin four-corner right-angle profile. One side of the lower docking reinforcement of the cabin is fitted to the fuselage skin and frame edge of the top of the aircraft fuselage, and the other side of the lower docking reinforcement of the cabin is fixedly connected to the right-angle profiles and T-shaped profiles of the lower left and right sides of the cabin. The upper right-angle profiles on the left and right sides of the cabin are symmetrically arranged with the lower right-angle profiles on the left and right sides of the cabin. The upper T-shaped profiles on the left and right sides of the cabin are symmetrically arranged vertically with the lower T-shaped profiles on the left and right sides of the cabin. The right-angle profile of the outer top is fixedly connected to the outer top web plate; The T-shaped profiles on the left and right sides of the cabin and the web plates on the left and right sides of the cabin are both located between the lower T-shaped profiles on the left and right sides of the cabin and the upper T-shaped profiles on the left and right sides of the cabin. The upper part of one end of the top web plate of the cabin is fixedly connected to the upper right-angle profile of the left and right sides of the cabin, and the lower part of the other end is fixedly connected to the lower right-angle profile of the upper left and right sides of the cabin. The lower part of the other end of the top web plate of the cabin is fixedly connected to the upper T-shaped profile of the left and right sides of the cabin and the upper right-angle profile of the cabin, respectively. The fairing assembly is connected to the upper side of the outer top web plate via obtuse-angled arc profiles at the front and rear ends of the outer side, and to the lower side of the outer top web plate via right-angled arc profiles at the front and rear ends of the outer side. Right-angle profiles at the four corners of the cabin are set at the four corners of the cavity formed by the left and right side webs and the front and rear webs of the cabin. The left and right side webs and the front and rear webs of the cabin are all fixed by the right-angle profiles at the four corners of the cabin.
[0006] Furthermore, the external frame support elements also include a first external inclined right-angle profile, a second external inclined right-angle profile, an external top joint, and an external bottom joint; Both the first and second external inclined right-angle profiles are installed between the left and right side web plates of the cabin. The tops of the first and second external inclined right-angle profiles are fixedly connected to the external top web plate via external top joints. The bottom of the first and second external inclined right-angle profiles are fixedly connected to the lower end of the external structure via the external bottom joint and the external lower end reinforcement.
[0007] Furthermore, the array fairing assembly includes: External front and rear arrays, external left and right side arrays, external top array or satellite communication equipment, top composite fairing, front and rear composite fairings and left and right side composite fairings; The fore and aft arrays are set on the fore and aft webs of the external cabin, and the fore and aft arrays include the fore array and the aft array. The external left and right side arrays are located on the external left and right side webs of the cabin; The external top array or satellite communication equipment is mounted on the external top web plate; The top composite material fairing is connected to the upper side of the top web of the cabin via obtuse-angled arc profiles at the front and rear ends of the cabin. The front and rear composite material fairings are respectively installed on the front and rear sides of the front and rear webs outside the cabin; The left and right composite material fairings are connected to the lower side of the top web plate of the cabin via right-angled arc profiles at the front and rear of the cabin.
[0008] Furthermore, the internal components include a first reinforcing frame, a second reinforcing frame, a third reinforcing frame, a fourth reinforcing frame, a docking joint, and an upper docking reinforcement within the internal compartment; The upper docking reinforcement inside the cabin is fixedly connected to the external components. The tops of the first, second, third, and fourth reinforcing frames are all fixedly connected to the upper internal reinforcement components after being inserted into each other. The bottoms of the first reinforcing frame, the second reinforcing frame, the third reinforcing frame, and the fourth reinforcing frame are fixedly connected to the floor beam or the lower edge of the floor frame via butt joints (5); The first, second, third, and fourth reinforcing frames are fixedly connected to the fuselage skin or reinforcing pad on one side and to the stringer on the other side.
[0009] A multi-array cooperative working method for performing reconnaissance, identification, search, or surveillance tasks based on array fairing assemblies, comprising the following steps: Receive mission instructions from the aircraft control system; Based on mission instructions, generate a collaborative working strategy for at least two arrays in the array fairing assembly, including the front and rear arrays, left and right arrays, and top array, or satellite communication equipment. The collaborative working strategy is used to dynamically allocate the working modes and beam resources of different arrays. Based on the collaborative work strategy, control at least two fronts to perform corresponding reconnaissance, identification, search, or surveillance tasks.
[0010] Furthermore, a collaborative working strategy is generated for at least two arrays in the array fairing assembly, including the fore-and-aft arrays, left and right side arrays, and top array, or satellite communication equipment. The task instruction is parsed into multiple perception subtasks; At least one array surface is assigned as an execution unit for each sensing subtask; Time resources are allocated for each assigned array face, and a working mode and beam pointing are set for each assigned array face through a collaborative working strategy. The collaborative working strategy includes a beam focusing mode and a beam diversity mode. The beam focusing mode controls the transmit or receive beams of at least two array faces to simultaneously point to the same spatial area. The beam diversity mode controls the beams of each array face to point to different preset spatial sectors in order to achieve panoramic coverage.
[0011] Furthermore, the steps for setting time resources for each assigned array face include: Define a scan cycle; The scanning period is divided into multiple non-overlapping or partially overlapping time slices; Within different time slices, control the same array to execute different subtasks, and / or control different arrays to work in parallel or sequentially.
[0012] Furthermore, collaborative work methods also include: Acquire sensing data from the front and rear arrays, left and right side arrays, and top array or satellite communication equipment outside the cabin; The acquired perception data is fused and processed to generate unified battlefield situation information; Based on battlefield situation information, assess the effectiveness of the current collaborative work strategy and dynamically adjust the collaborative work strategy when the effectiveness does not meet the preset conditions.
[0013] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least: It solves the limitation of the array beam emission angle, realizes the application requirements of multi-directional radiation and reception of the array, and improves the overall performance of the aircraft. Attached Figure Description
[0014] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0015] Figure 1 This is a schematic diagram of a multi-faceted device on the top of an aircraft fuselage according to an embodiment of the present invention; Figure 2 yes Figure 1 A schematic cross-sectional view along the AA direction; Figure 3 yes Figure 1 A schematic cross-sectional view along direction B; Figure 4 yes Figure 2 Detailed schematic diagram of Part I; Figure 5 yes Figure 2 Detailed schematic diagram of Part II; Figure 6 yes Figure 3 Detailed schematic diagram of Part III; Figure 7 yesFigure 3 Detailed diagram of part IV; Figure 8 yes Figure 2 A cross-sectional view along direction C; Figure 9 yes Figure 8 A cross-sectional view along direction D; Figure 10 yes Figure 9 A schematic cross-sectional view along the FF direction; Figure 11 yes Figure 8 A cross-sectional view along direction E; Figure 12 yes Figure 11 A cross-sectional schematic diagram along the GG direction.
[0016] Figure reference numerals: 1. First reinforcing frame; 2. Second reinforcing frame; 3. Third reinforcing frame; 4. Fourth reinforcing frame; 5. Butt joint; 6. Upper butt reinforcing member inside the cabin; 7. Lower butt reinforcing member outside the cabin; 8. Lower right-angle profile on the left and right sides outside the cabin; 9. Lower T-shaped profile on the left and right sides outside the cabin; 10. Upper right-angle profile on the left and right sides outside the cabin; 11. Lower right-angle profile on the upper left and right sides outside the cabin; 12. Upper T-shaped profile on the left and right sides outside the cabin; 13. Upper right-angle profile on the top of the cabin; 14. T-shaped profile on the left and right sides outside the cabin; 15. Web plate on the left and right sides outside the cabin; 16. Cabin 17. Obtuse-angled arc profile at the upper front and rear of the cabin; 18. Right-angled arc profile at the upper front and rear of the cabin; 19. Front and rear web plates of the cabin; 20. Front and rear arrays of the cabin; 21. Left and right side arrays of the cabin; 22. Top array or satellite communication equipment of the cabin; 23. Top joint of the cabin; 24. Bottom joint of the cabin; 25. Top composite material fairing; 26. Front and rear composite material fairings; 27. Left and right side composite material fairings; 28. First oblique right-angle profile of the cabin; 29. Second oblique right-angle profile of the cabin; 30. Right-angle profiles at the four corners of the cabin. Detailed Implementation
[0017] The embodiments of this application will now be described in detail with reference to the accompanying drawings.
[0018] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.
[0019] like Figures 1-12 As shown, a multi-faceted device on the top of an aircraft fuselage includes: The cabin components and the external components are fixedly connected at the bottom to the cabin components. The cabin components are used to transfer the loads generated by the external components to the aircraft fuselage skin, reinforcing pads, stringers, floor beams, and lower floor frame edges. The external components include external frame support elements and array fairing assemblies; The external frame support element includes an external lower end docking reinforcement 7, and the bottom of the external frame support element is fixed to the fuselage skin and frame edge of the top of the aircraft fuselage through the external lower end docking reinforcement 7. The array fairing assembly is fixed to the external frame support elements and is used to generate and receive electromagnetic waves for reconnaissance, identification, search and surveillance missions.
[0020] Specifically, the external frame support elements include: right-angle profiles 8 at the lower ends of the left and right sides of the external cabin; T-shaped profiles 9 at the lower ends of the left and right sides of the external cabin; right-angle profiles 10 at the upper ends of the left and right sides of the external cabin; lower right-angle profiles 11 at the upper part of the left and right sides of the external cabin; T-shaped profiles 12 at the upper ends of the left and right sides of the external cabin; right-angle profiles 13 at the top of the external cabin; T-shaped profiles 14 on the left and right sides of the external cabin; web plates on the left and right sides of the external cabin; top web plate of the external cabin; obtuse-angled arc profiles at the upper front and rear ends of the external cabin; lower right-angled arc profiles at the upper front and rear ends of the external cabin; front and rear web plates of the external cabin; and right-angle profiles at the four corners of the external cabin. One side of the lower docking reinforcement 7 outside the cabin is fitted to the fuselage skin and frame edge of the top of the aircraft fuselage, and the other side of the lower docking reinforcement 7 outside the cabin is fixedly connected to the right angle profile 8 and the T-shaped profile 9 on the lower left and right sides of the cabin. The upper right-angle profile 11 on the left and right sides of the cabin and the lower right-angle profile 8 on the left and right sides of the cabin are symmetrically arranged vertically. The upper T-shaped profiles 12 on the left and right sides of the cabin and the lower T-shaped profiles 9 on the left and right sides of the cabin are symmetrically arranged vertically. The right-angle profile 13 on the top of the cabin is fixedly connected to the top web plate 16 on the top of the cabin. The T-shaped profiles 14 on the left and right sides of the cabin and the web plates 15 on the left and right sides of the cabin are both located between the lower T-shaped profiles 9 on the left and right sides of the cabin and the upper T-shaped profiles 12 on the left and right sides of the cabin. The upper part of one end of the top web plate 16 outside the cabin is fixedly connected to the upper right-angle profile 10 of the left and right sides outside the cabin, and the lower part of the other end is fixedly connected to the lower right-angle profile 11 of the upper left and right sides outside the cabin. The lower part of the other end of the top web plate 16 outside the cabin is fixedly connected to the upper T-shaped profile 12 of the left and right sides outside the cabin and the upper right-angle profile 13 of the cabin outside the cabin, respectively. The fairing assembly is connected to the upper side of the outer top web plate 16 via obtuse-angled arc profiles 17 at the front and rear ends of the outer side of the cabin, and to the lower side of the outer top web plate 16 via right-angled arc profiles 18 at the front and rear ends of the outer side of the cabin. Right-angle profiles 30 are installed at the four corners of the cavity formed by the left and right side webs 15 and the front and rear webs 19 outside the cabin. The left and right side webs 15 and the front and rear webs 19 outside the cabin are all fixed by the right-angle profiles 30 outside the cabin.
[0021] Specifically, the external frame support elements also include a first external inclined right-angle profile 28, a second external inclined right-angle profile 29, an external top joint 23, and an external bottom joint 24; The first external inclined right-angle profile 28 and the second external inclined right-angle profile 29 are both installed between the left and right side web plates 15 outside the cabin; The tops of the first external inclined right-angle profile 28 and the second external inclined right-angle profile 29 are fixedly connected to the external top web plate 16 via external top joint 23. The bottom of the first external inclined right-angle profile 28 and the second external inclined right-angle profile 29 are fixedly connected to the external lower end docking reinforcement 7 through the external bottom joint 24.
[0022] Specifically, the array fairing assembly includes: External front and rear arrays 20, external left and right side arrays 21, external top array or satellite communication equipment 22, top composite material fairing 25, front and rear composite material fairings 26 and left and right side composite material fairings 27.
[0023] The fore and aft arrays 20 are mounted on the fore and aft webs 19, including a fore array and an aft array. The left and right side arrays 21 are mounted on the left and right side webs 15. The top array or satellite communication equipment 22 is mounted on the top web 16. The top composite material fairing 25 is connected to the upper side of the top web 16 via obtuse-angled arc profiles 17 at the fore and aft ends. The fore and aft composite material fairings 26 are mounted on the fore and aft sides of the fore and aft webs 19, respectively. The left and right side composite material fairings 27 are connected to the lower side of the top web 16 via right-angled arc profiles 18 at the fore and aft ends.
[0024] Specifically, the internal components include a first reinforcing frame 1, a second reinforcing frame 2, a third reinforcing frame 3, a fourth reinforcing frame 4, a docking joint 5, and an upper docking reinforcement 6.
[0025] The upper docking reinforcement 6 inside the cabin is fixedly connected to the external components; the tops of the first reinforcement frame 1, the second reinforcement frame 2, the third reinforcement frame 3 and the fourth reinforcement frame 4 are all fixedly connected to the upper docking reinforcement 6 inside the cabin after being inserted; the bottoms of the first reinforcement frame 1, the second reinforcement frame 2, the third reinforcement frame 3 and the fourth reinforcement frame 4 are fixedly connected to the floor beam or the lower edge of the floor frame through the docking joint 5; one side of the first reinforcement frame 1, the second reinforcement frame 2, the third reinforcement frame 3 and the fourth reinforcement frame 4 is fixedly connected to the fuselage skin or the reinforcing pad, and the other side is fixedly connected to the stringer.
[0026] In one embodiment of the present invention, such as Figures 1-12As shown, the array device on the outer top of the aircraft includes: a first reinforcing frame 1, a second reinforcing frame 2, a third reinforcing frame 3, a fourth reinforcing frame 4, a docking joint 5 (8 pieces in total), an upper docking reinforcement 6 inside the cabin (4 pieces in total), a lower docking reinforcement 7 outside the cabin (1 piece), right-angle profiles 8 on the lower ends of the left and right sides outside the cabin (2 pieces in total), T-shaped profiles 9 on the lower ends of the left and right sides outside the cabin (2 pieces in total), right-angle profiles 10 on the upper ends of the left and right sides outside the cabin (2 pieces in total), lower right-angle profiles 11 on the upper parts of the left and right sides outside the cabin (2 pieces in total), T-shaped profiles 12 on the upper ends of the left and right sides outside the cabin (2 pieces in total), right-angle profiles 13 on the top of the cabin outside the cabin (17 pieces in total), T-shaped profiles 14 on the left and right sides outside the cabin (30 pieces in total), web plates on the left and right sides outside the cabin (2 pieces in total), and a top web plate outside the cabin. 16 (1 piece), obtuse-angled arc profile at the upper front and rear of the cabin 17 (2 pieces in total), right-angled arc profile at the upper front and rear of the cabin 18 (4 pieces in total), front and rear web plates of the cabin 19 (2 pieces in total), front and rear array surfaces of the cabin 20 (2 pieces in total), left and right side array surfaces of the cabin 21 (2 pieces in total), top array surface or satellite communication of the cabin 22 (1 piece in total), top connector of the cabin 23 (2 pieces in total), bottom connector of the cabin 24 (2 pieces in total), top composite material fairing 25 (1 piece), front and rear composite material fairing 26 (2 pieces in total), left and right side composite material fairing 27 (2 pieces in total), right-angled angled profile of the cabin 28 (2 pieces in total), right-angled angled profile of the cabin 29 (2 pieces in total), right-angled profile at the four corners of the cabin 30 (4 pieces in total).
[0027] The multi-faceted structure on the top of the aircraft fuselage mainly consists of two parts: internal assembly and external assembly.
[0028] The internal assembly mainly consists of the first reinforcing frame 1, the second reinforcing frame 2, the third reinforcing frame 3, the fourth reinforcing frame 4, the docking joint 5 (a total of 8 pieces), and the upper docking reinforcing component 6 (a total of 4 pieces).
[0029] like Figure 1 , Figure 2 , Figure 3 As shown, all internal components are integral aluminum alloy reinforcing parts, CNC machined. The positioning dimension of the first reinforcing frame 1 and the fourth reinforcing frame 4 is f. The first reinforcing frame 1, the second reinforcing frame 2, the third reinforcing frame 3, the fourth reinforcing frame 4, and the docking joint 5 are connected to the aircraft floor and floor beams by bolts. The first reinforcing frame 1, the second reinforcing frame 2, the third reinforcing frame 3, the fourth reinforcing frame 4, and the upper internal docking reinforcing component 6 are connected by bolts after mating. The lateral connections of the first reinforcing frame 1, the second reinforcing frame 2, the third reinforcing frame 3, and the fourth reinforcing frame 4 are bolted to the fuselage skin and reinforcing pads. The lateral connections of the first reinforcing frame 1, the second reinforcing frame 2, the third reinforcing frame 3, and the fourth reinforcing frame 4 are connected to the stringers by bolts through stringer joints. These components form the internal assembly, distributing external loads to the fuselage skin, stringers, floor beams, and lower floor frame edge. The force transmission path is continuous, direct, and reliable, achieving force transmission and balance.
[0030] The external assembly mainly consists of: 7 (1 piece) of lower external docking reinforcement, 8 (2 pieces) of lower right-angle profiles on the left and right sides of the external assembly, 9 (2 pieces) of lower T-shaped profiles on the left and right sides of the external assembly, 10 (2 pieces) of upper right-angle profiles on the left and right sides of the external assembly, 11 (2 pieces) of lower right-angle profiles on the upper part of the left and right sides of the external assembly, 12 (2 pieces) of upper T-shaped profiles on the left and right sides of the external assembly, 13 (17 pieces) of upper right-angle profiles on the top of the external assembly, 14 (30 pieces) of T-shaped profiles on the left and right sides of the external assembly, 15 (2 pieces) of web plates on the left and right sides of the external assembly, 16 (1 piece) of top web plate on the external assembly, 17 (2 pieces) of obtuse-angled arc profiles at the front and rear of the external assembly, and the upper front and rear of the external assembly. It consists of: lower right-angled arc profile 18 (4 pieces in total), external front and rear web plates 19 (2 pieces in total), external front and rear array surfaces 20 (2 pieces in total), external left and right side array surfaces 21 (2 pieces in total), external top array surface or satellite communication 22 (1 piece in total), external top connector 23 (2 pieces in total), external bottom connector 24 (2 pieces in total), top composite material fairing 25 (1 piece), front and rear composite material fairings 26 (2 pieces in total), left and right side composite material fairings 27 (2 pieces in total), external inclined right-angle profile 28 (2 pieces in total), external inclined right-angle profile 29 (2 pieces in total), external four corner right-angle profiles 30 (4 pieces in total), etc.
[0031] Among them, the lower external docking reinforcement 7, the top external connector 23, and the bottom external connector 24 are integral aluminum alloy reinforcements, machined. The lower external docking reinforcement 7 (1 piece) is located outside the aircraft skin. One side of the lower external docking reinforcement 7 is attached to the fuselage skin, and the other side of the lower external docking reinforcement 7 is a horizontal plane. It is bolted to the lower right-angle profiles 8 (2 pieces in total) on the left and right sides of the external cabin, the lower T-shaped profiles 9 (2 pieces in total) on the left and right sides of the external cabin, the aircraft skin, and the frame edge.
[0032] like Figure 11 As shown, the lower docking reinforcement 7 outside the cabin has through holes for cables, liquid cooling, etc. The hole positioning dimensions are jmm (typical size), Φk mm, Φw mm, to facilitate the passage of cables, liquid cooling, and other equipment.
[0033] The upper T-shaped profiles 12 on the left and right sides of the cabin (2 pieces in total) are symmetrical to the lower T-shaped profiles 9 on the left and right sides of the cabin, and use the same profile number.
[0034] Between the lower T-shaped profiles 9 on the left and right sides of the upper and lower compartments, and the upper T-shaped profiles 12 on the left and right sides of the compartments, there are T-shaped profiles 14 on the left and right sides of the compartments and web plates 15 on the left and right sides of the compartments. The positioning dimension of the T-shaped profiles 14 on the left and right sides of the compartments is g mm (typical dimension). Figure 2 As shown, the left and right side web plates 15 outside the cabin are spaced apart by e mm, and the spaced area is the installation and maintenance passage.
[0035] likeFigure 8 , Figure 9 As shown, the four right-angle profiles 30 (4 pieces in total) are arranged at the front and rear corners of the external assembly.
[0036] Two external inclined right-angle profiles 28 and 29 are diagonally arranged inside the external assembly and are connected and fixed to surrounding structural components using external top joints 23 and external bottom joints 24. Figure 3 , Figure 6 , Figure 7 As shown, the positioning dimensions t mm, u mm, and y mm provide an effective passage for installation and maintenance.
[0037] Two right-angled profiles 8 (total of 2) are arranged symmetrically with two lower right-angled profiles 11 (total of 2) on the upper part of the left and right sides of the cabin. Two upper right-angled profiles 10 (total of 2) are arranged above the lower right-angled profiles 11 on the upper part of the left and right sides of the cabin. Figure 4 , Figure 5 As shown. The right-angle profiles 10 on the upper left and right sides of the cabin are connected and fixed to the top composite material fairing 25 (1 piece) using standard parts. The external dimensions of the top composite material fairing 25 (1 piece) are Rd mm.
[0038] Two composite material fairings 27 are arranged between the lower right-angle profiles 8 on the left and right sides of the cabin and the upper lower right-angle profiles 11 on the left and right sides of the cabin. The lower right-angle profiles 8 on the left and right sides of the cabin, the upper lower right-angle profiles 11 on the left and right sides of the cabin, and the composite material fairings 27 on the left and right sides of the cabin are connected and fixed using standard parts.
[0039] The outer top web plate 16 (1 piece) is arranged on the upper part of the outer side of the cabin. The outer top right angle profile 13 (17 pieces in total) is arranged on the outer top web plate 16. The outer top right angle profile 13 is fixed to the outer top web plate 16 by standard parts.
[0040] The front and rear ends of the cabin are equipped with four right-angled arc profiles (18 pieces in total) at the upper and lower parts of the front and rear ends, and two obtuse-angled arc profiles (17 pieces in total) at the upper and lower ends of the front and rear ends. Figure 10 As shown, the obtuse-angled arc profile 17 at the front and rear upper ends of the cabin, the right-angled arc profile 18 at the front and rear upper parts of the cabin, the top composite material fairing 25, and the front and rear composite material fairings 26 are connected and fixed with standard parts.
[0041] The front and rear web plates 19 (2 pieces) are installed on the flat surfaces of the four right-angle profiles 30 (4 pieces) outside the cabin. The front and rear arrays 20 (2 pieces) are installed on the flat surfaces of the front and rear web plates 19 outside the cabin. The left and right side arrays 21 (2 pieces) are installed on the flat surfaces of the left and right side web plates 15 (2 pieces) outside the cabin. The top array or satellite communication 22 (1 piece) is installed on the flat surface of the top web plate 16 (1 piece) outside the cabin.
[0042] The external components have dimensions of a mm, b mm, and c mm, and transfer the load to the internal components to achieve force balance.
[0043] To ensure the normal operation of various air defense arrays, power and liquid cooling functions are provided, while also meeting the requirements for installation, maintenance, and personnel access space for the mission system's power and liquid cooling systems. The power and liquid cooling systems can be installed and maintained through the aircraft skin and external assembly space. The power and liquid cooling systems pass through the aircraft's airtight lines (skin) and employ conventional airtight devices to ensure the aircraft's airtightness.
[0044] A multi-array cooperative working method for performing reconnaissance, identification, search, or surveillance tasks based on array fairing assemblies, comprising the following steps: Step 1: Receive mission instructions from the aircraft control system; Step 2: Based on the mission instructions, generate a collaborative working strategy for at least two arrays in the array fairing assembly, including the front and rear arrays 20, the left and right side arrays 21, and the top array or satellite communication equipment 22. The collaborative working strategy is used to dynamically allocate the working modes and beam resources of different arrays. Step 2.1: Parse the task instruction into multiple perception subtasks; Step 2.2: Assign at least one array as an execution unit for each of the aforementioned sensing subtasks; Step 2.3: Set time resources for each assigned array face, and set working mode and beam pointing for each assigned array face through a collaborative working strategy. The collaborative working strategy includes beam focusing mode and beam diversity mode. The beam focusing mode controls the transmit beams or receive beams of at least two array faces to simultaneously point to the same spatial area. The beam diversity mode controls the beams of each array face to point to different preset spatial sectors to achieve panoramic coverage.
[0045] Step 2.3.1: Define a scan cycle; Step 2.3.2: Divide the scanning period into multiple non-overlapping or partially overlapping time slices; Step 2.3.3: Within different time slices, control the same array surface to execute different sub-tasks, and / or control different array surfaces to work in parallel or sequentially.
[0046] Step 3: According to the cooperative working strategy, control at least two arrays to perform corresponding reconnaissance, identification, search or surveillance tasks.
[0047] Step 4.1: Acquire sensing data from the front and rear arrays 20, the left and right side arrays 21, and the top array or satellite communication equipment 22 outside the cabin; Step 4.2: Perform fusion processing on the acquired sensing data to generate unified battlefield situation information; Step 4.3: Based on the battlefield situation information, evaluate the execution effectiveness of the current collaborative work strategy, and dynamically adjust the collaborative work strategy when the effectiveness does not meet the preset conditions.
[0048] In one embodiment of the present invention, the specific implementation process is as follows: 1. Receive task instructions.
[0049] The central processing computer receives high-level mission instructions from the pilot's operating interface or a higher-level flight mission management system. These mission instructions may, for example, be: Wide-area search: requires indiscriminate and wide-range reconnaissance of the airspace surrounding the aircraft.
[0050] Multi-target tracking: requires continuous and accurate tracking of multiple specific targets that have been detected.
[0051] Specific sector surveillance: requires focused monitoring of a specific direction.
[0052] Communication relay: requires the establishment of a stable communication link with satellites or other platforms.
[0053] Electronic countermeasures: This requires jamming enemy radar or missile guidance systems.
[0054] 2. Generate collaborative work strategies.
[0055] Based on the received task instructions, the central processing unit generates a dynamic collaborative work strategy. The core of this strategy is to virtualize multiple physical arrays as a unified resource pool for scheduling.
[0056] Taking the "multi-target tracking" instruction as an example, the system parses it into the following sub-tasks: Subtask A: Continuously track locked high-priority targets.
[0057] Subtask B: Maintain a search of the entire airspace in preparation for new threats.
[0058] Subtask C: Maintain satellite communication link with command center.
[0059] Resource allocation and beam coordination.
[0060] The system allocates the most suitable array resources based on the needs of the sub-tasks: Subtask A (Precision Tracking) is assigned to the outer frontal array with the highest detection accuracy.
[0061] Subtask B (wide-area search) is assigned to the external top array or satellite communication device 22 with the widest field of view, and it is instructed to perform an airspace scan.
[0062] Subtask C (communication relay) is assigned to a top array or satellite communication device 22 with satellite communication capabilities (in this embodiment, the top array is a multi-functional integrated design).
[0063] When faced with sudden, high-intensity missions, the system will activate beam focusing mode. For example, when a highly stealthy target is detected, the system can control the beams of the external forward array and the external left array to simultaneously point at the target, forming a beam with stronger equivalent power through coherent synthesis, which greatly improves the detection and tracking range and accuracy of the target.
[0064] 3. Resource scheduling based on time-division multiplexing.
[0065] To address the issue of a single array needing to perform multiple tasks or system resource constraints, this embodiment employs time-division multiplexing technology for micro-scheduling.
[0066] The system defines a fixed-duration scan period and divides this period into multiple time slices: During the first time period of a fixed duration, the top surface performs a wide-area search (subtask B).
[0067] During the second time period of fixed duration, the front plane performs precision tracking (subtask A).
[0068] During the third time period of a fixed duration, the top array switches to satellite communication mode and performs "communication relay" (sub-task C) to conduct a high-speed data burst.
[0069] During the fourth period of the fixed time interval, all arrays switch to passive receiving mode to conduct electronic reconnaissance.
[0070] This rapid switching at the nanosecond / microsecond level enables multiple tasks to be performed simultaneously, significantly improving the overall task efficiency and resource utilization of the system.
[0071] 4. Data fusion and feedback optimization.
[0072] The central processing computer continuously receives perception data such as points and images from various fronts, and uses Kalman filtering and trajectory association algorithms to fuse these data to generate a unified, non-redundant, and high-precision comprehensive battlefield situation map, which is then displayed on the pilot's screen.
[0073] The system monitors performance metrics in real time, such as the tracking accuracy of Target A. If tracking accuracy degrades due to aircraft maneuvers, the system dynamically adjusts its collaborative working strategy. For example, it can automatically shorten the search time slice of the top array (e.g., from A ms to B ms) and allocate the saved AB ms to the front array to increase its tracking data update rate, thereby restoring tracking accuracy. This closed-loop control mechanism ensures that the system maintains optimal performance under various dynamic environments.
[0074] Beneficial effects of the embodiments of the present invention: This invention overcomes the shortcomings of existing array mounting technologies and provides a multi-array device on the top of an aircraft fuselage. It meets the requirements for multi-directional radiation and reception of airborne and mission systems. By elevating the array, it reduces obstruction of the array by aircraft structures such as the fuselage, wings, and tail. By raising the array to form five arrays (front, rear, left, right, and upper), it solves the limitation of the array beam emission angle, achieving multi-directional radiation and reception requirements and improving the overall performance of the aircraft. Furthermore, by mounting the array high outside the fuselage, it reduces obstruction of the array by aircraft structures such as the fuselage, wings, and tail. By forming five arrays, it solves the limitation of the array beam emission angle, achieving 360° use of the array by mission systems and improving the overall performance of the aircraft. By combining mission-driven dynamic resource allocation with beam coordination control, this method effectively solves the problems of resource conflicts, single-task focus, and blind spots in traditional multi-array systems, maximizing system efficiency and significantly improving the aircraft's situational awareness, survivability, and strike capabilities.
[0075] The above are merely specific embodiments of the present invention and should not be construed as limiting the scope of the invention. Therefore, substitutions of equivalent components, or equivalent changes and modifications made within the scope of protection of this patent, should still fall within the scope of this patent. Furthermore, the technical features, technical features and technical solutions, and technical solutions in this invention can be freely combined and used.
Claims
1. A multi-faceted device on the top of an aircraft fuselage, characterized in that, include: The cabin includes an internal component and an external component, the bottom of which is fixedly connected to the internal component. The internal component is used to transfer the load generated by the external component to the aircraft's fuselage skin, reinforcing pads, stringers, floor beams, and lower floor frame. The external components include external frame support elements and array fairing assemblies; The external frame support element includes an external lower end docking reinforcement (7), and the bottom of the external frame support element is fixed to the fuselage skin and frame edge of the top of the aircraft fuselage through the external lower end docking reinforcement (7). The array fairing assembly is fixed to the external frame support element, and the array fairing assembly is used to generate and receive electromagnetic waves for performing reconnaissance, identification, search and surveillance missions.
2. The multi-faceted device on the top of the aircraft fuselage according to claim 1, characterized in that, The external frame support elements include right-angle profiles (8) at the lower ends of the left and right sides of the cabin, T-shaped profiles (9) at the lower ends of the left and right sides of the cabin, right-angle profiles (10) at the upper ends of the left and right sides of the cabin, lower right-angle profiles (11) at the upper part of the left and right sides of the cabin, T-shaped profiles (12) at the upper end of the left and right sides of the cabin, right-angle profiles (13) at the top of the cabin, T-shaped profiles (14) on the left and right sides of the cabin, web plates (15) on the left and right sides of the cabin, top web plates (16) at the top of the cabin, obtuse-angled arc profiles (17) at the upper front and rear ends of the cabin, lower right-angled arc profiles (18) at the upper front and rear ends of the cabin, front and rear web plates (19) and right-angle profiles (30) at the four corners of the cabin. One side of the lower docking reinforcement (7) of the cabin is attached to the fuselage skin and frame edge of the top of the aircraft fuselage, and the other side of the lower docking reinforcement (7) of the cabin is fixedly connected to the right angle profile (8) of the lower left and right sides of the cabin and the T-shaped profile (9) of the lower left and right sides of the cabin. The upper right-angle profile (11) on the left and right sides outside the cabin and the lower right-angle profile (8) on the left and right sides outside the cabin are symmetrically arranged vertically. The upper T-shaped profiles (12) on the left and right sides outside the cabin and the lower T-shaped profiles (9) on the left and right sides outside the cabin are symmetrically arranged vertically. The right-angle profile (13) on the top of the cabin is fixedly connected to the top web plate (16) of the cabin. The T-shaped profiles (14) on the left and right sides of the cabin and the web plates (15) on the left and right sides of the cabin are both located between the lower T-shaped profiles (9) on the left and right sides of the cabin and the upper T-shaped profiles (12) on the left and right sides of the cabin. The upper part of one end of the top web plate (16) of the cabin is fixedly connected to the upper right-angle profile (10) of the left and right sides of the cabin, and the lower part of one end is fixedly connected to the lower right-angle profile (11) of the upper left and right sides of the cabin. The lower part of the other end of the top web plate (16) of the cabin is fixedly connected to the upper T-shaped profile (12) of the left and right sides of the cabin and the upper right-angle profile (13) of the cabin respectively. The fairing assembly is connected to the upper side of the top web plate (16) of the cabin via obtuse-angled arc profiles (17) at the front and rear ends of the cabin, and to the lower side of the top web plate (16) of the cabin via right-angled arc profiles (18) at the front and rear ends of the cabin. The right-angle profiles (30) at the four corners of the cabin are set at the four corners of the cavity formed by the left and right side webs (15) and the front and rear webs (19) of the cabin. The left and right side webs (15) and the front and rear webs (19) of the cabin are fixed by the right-angle profiles (30).
3. The multi-faceted device on the top of the aircraft fuselage according to claim 2, characterized in that, The external frame support elements also include a first external inclined right-angle profile (28), a second external inclined right-angle profile (29), an external top connector (23), and an external bottom connector (24). The first external inclined right-angle profile (28) and the second external inclined right-angle profile (29) are both located between the left and right side web plates (15) of the cabin. The tops of the first external inclined right-angle profile (28) and the second external inclined right-angle profile (29) are fixedly connected to the external top web plate (16) through the external top joint (23); The bottoms of the first external inclined right-angle profile (28) and the second external inclined right-angle profile (29) are fixedly connected to the external lower end docking reinforcement (7) through the external bottom joint (24).
4. The multi-faceted device on the top of the aircraft fuselage according to claim 2, characterized in that, The array fairing assembly includes: External front and rear arrays (20), external left and right side arrays (21), external top array or satellite communication equipment (22), top composite fairing (25), front and rear composite fairings (26) and left and right side composite fairings (27); The external front and rear arrays (20) are disposed on the external front and rear webs (19), wherein the external front and rear arrays (20) include an external front array and an external rear array; The left and right side arrays (21) outside the cabin are set on the left and right side webs (15) outside the cabin; The external top array or satellite communication equipment (22) is mounted on the external top web (16); The top composite material fairing (25) is connected to the upper side of the top web plate (16) of the cabin via obtuse-angled arc profiles (17) at the front and rear ends of the cabin. The front and rear composite material fairings (26) are respectively disposed on the front and rear sides of the front and rear webs (19) outside the cabin; The left and right composite material fairings (27) are connected to the lower side of the top web plate (16) of the cabin via the upper right-angled arc profile (18) at the front and rear of the cabin.
5. The multi-faceted device on the top of the aircraft fuselage according to claim 1, characterized in that, The internal components include a first reinforcing frame (1), a second reinforcing frame (2), a third reinforcing frame (3), a fourth reinforcing frame (4), a docking joint (5), and an upper docking reinforcement (6) inside the cabin. The upper docking reinforcement (6) inside the cabin is fixedly connected to the external assembly; The tops of the first reinforcing frame (1), the second reinforcing frame (2), the third reinforcing frame (3) and the fourth reinforcing frame (4) are all fixedly connected to the upper docking reinforcing member (6) inside the cabin after being inserted into each other; The bottoms of the first reinforcing frame (1), the second reinforcing frame (2), the third reinforcing frame (3), and the fourth reinforcing frame (4) are fixedly connected to the floor beam or the lower edge of the floor frame through the butt joint (5); One side of the first reinforcing frame (1), the second reinforcing frame (2), the third reinforcing frame (3) and the fourth reinforcing frame (4) are fixedly connected to the fuselage skin or the reinforcing pad, and the other side is fixedly connected to the stringer.
6. A multi-array cooperative working method for performing reconnaissance, identification, search, or surveillance tasks based on the array fairing assembly according to any one of claims 1 to 5, characterized in that, Includes the following steps: Receive mission instructions from the aircraft control system; Based on the mission instructions, a collaborative working strategy is generated for at least two of the following arrays in the array fairing assembly: the front and rear arrays (20), the left and right side arrays (21), and the top array or satellite communication equipment (22). The collaborative working strategy is used to dynamically allocate the working modes and beam resources of different arrays. According to the aforementioned collaborative working strategy, at least two arrays are controlled to perform corresponding reconnaissance, identification, search, or surveillance tasks.
7. The collaborative working method according to claim 6, characterized in that, Generate a cooperative working strategy for at least two of the following arrays in the array fairing assembly: the fore-and-aft arrays (20), the left and right side arrays (21), and the top array or satellite communication equipment (22). The task instruction is parsed into multiple perception subtasks; At least one array surface is assigned as an execution unit for each of the aforementioned sensing subtasks; Time resources are allocated for each assigned array face, and a working mode and beam pointing are set for each assigned array face through a collaborative working strategy. The collaborative working strategy includes a beam focusing mode and a beam diversity mode. The beam focusing mode controls the transmit or receive beams of at least two array faces to simultaneously point to the same spatial region. The beam diversity mode controls the beams of each array face to point to different preset spatial sectors to achieve panoramic coverage.
8. The collaborative working method according to claim 7, characterized in that, The steps for setting time resources for each assigned array face include: Define a scan cycle; The scanning period is divided into multiple non-overlapping or partially overlapping time slices; Within different time slices, different sub-tasks are executed on the same array surface, and / or different array surfaces are controlled to work in parallel or sequentially.
9. The collaborative working method according to claim 7, characterized in that, The collaborative work method also includes: Acquire sensing data from the front and rear arrays (20) outside the cabin, the left and right side arrays (21) outside the cabin, and the top array or satellite communication equipment (22) outside the cabin; The acquired perception data is fused and processed to generate unified battlefield situation information; Based on the battlefield situation information, the effectiveness of the current collaborative work strategy is evaluated, and the collaborative work strategy is dynamically adjusted when the effectiveness does not meet the preset conditions.