Multi-section separable and modular composite material aircraft pod

Abstract

This invention discloses a multi-segment detachable and combinable composite material aviation pod, comprising a central pod, side pod A, and side pod B. Side pod A is detachably connected to one end of the central pod, and side pod B is detachably connected to the other end of the central pod. The beneficial effects of this invention are: the pod has relatively independent side pods and a central pod, enabling a standardized design of the pod; under the same type of mission load, different size series of pods can be formed by combining independent pods according to functional capacity and specific requirements, which to a certain extent reduces the product development cycle and also reduces production costs; the use of carbon fiber combined with PMI reduces the weight of the pod and lightens the burden on the main load-bearing components; at the same time, the carbon fiber and PMI composite structure increases the stiffness of the pod while also increasing system damping, thereby optimizing the mechanical properties of the pod and enabling it to have vibration reduction and amplitude limiting functions; the shear structure at the connection between the side pod and the central pod compensates for the decrease in strength and stiffness at the connection end frame after the pod is segmented, ensuring the strength of the segmented pod.

Description

Technical Field

[0001] This invention pertains to airborne mission pods in the aviation field, specifically relating to a multi-section separable and combinable composite material aviation pod. Background Technology

[0002] Airborne pods, as airborne electronic mission platforms, expand the mission capabilities of aircraft without significantly altering their internal structure and external aerodynamic characteristics. They can be widely used on various aircraft platforms, including transport aircraft, fighter jets, helicopters, and unmanned aerial vehicles. Various mission payloads can be installed in the pods, expanding the aircraft's communication, navigation, reconnaissance, countermeasures, observation, and remote sensing functions.

[0003] Currently known pod types include frame type, beam end frame type, and top-load integrated pod.

[0004] Frame-type pods are derived from the structural design of aircraft skeletons and skins. The main structure consists of structural trusses of various cross-sectional shapes, with a high proportion of openwork. Its advantages include lighter weight, relatively easy machining, and the ability to be flexibly modified to meet specific needs, making it suitable for various applications. Furthermore, its streamlined shape makes it a common choice for supersonic pods. Its disadvantages include a relatively complex structure, numerous sealing elements, low space utilization, complex assembly, poor equipment maintainability, and a lower overall modal frequency and weaker stiffness. This type of pod can be made with a large diameter, reaching 700mm, allowing for the installation of a large amount of equipment, making it suitable for use on large, multi-functional platforms.

[0005] The main beam end-frame type pod is the most common type of pod found in domestic literature. It mainly consists of upper and lower main beams and a bulkhead (end frame), generally with a rectangular cross-section. The advantages of this type of pod are its relatively simple structure, fewer sealing elements, relatively compact structure, high rigidity, relatively simple assembly, high space utilization, and good equipment maintainability. However, because its upper and lower main beams are milled from a single piece of material, its machinability is relatively poor, and its weight is heavier than that of aircraft frame pods. The cross-sectional dimensions of this type of pod cannot be too large, thus limiting the equipment that can be installed inside. However, it has a certain degree of versatility, making it suitable for projects with a single function and a moderate amount of internal equipment. Because this type of pod usually has a non-streamlined interface, it is mostly used in subsonic flight environments.

[0006] Top-mounted pods typically consist of a top plate and an underbody enclosure. This type of pod is commonly used when there are few load-bearing devices, the equipment is lightweight, and internal antenna beamwidth coverage exceeds 90°. Its advantages include simple structure, easy assembly, wide beamwidth coverage, and light weight. Disadvantages include limited internal space and restrictions on the amount and weight of equipment that can be carried. Patents related to pod structure design include:

[0007] In known embodiments of the art, Chinese patent application CN105691626A discloses an aircraft fuselage bottom pod, which relates to an aircraft bottom pod that can serve as a test flight and usage platform for airborne products such as large antennas, radars, and cameras. The aircraft bottom pod is located on a straight section directly beneath the aircraft's belly and is a closed test pod composed of a fuselage bottom structure, an adapter flange, and an antenna radome. A lifting beam, serving as the installation interface for the tested equipment, is arranged inside the pod and rigidly connected to the original fuselage bottom structure, but it does not involve segmented design or universal design.

[0008] In known embodiments in the art, Chinese patent application CN114313205A discloses a composite material single-layer wall panel structure manned airship pod without mechanical connection. This invention discloses a composite material single-layer wall panel structure manned airship pod, which is a single-wall panel structure arranged in the middle of the hull, but does not involve segmented design or universal design.

[0009] In known embodiments in this field, Chinese patent application CN103728140A discloses a small turbojet engine flight test pod. This invention belongs to the field of aviation power flight test technology and relates to a pod for flight testing of small turbojet engines. Its features include a front section, a middle section, and a rear section, but it does not involve segmented design or universal design.

[0010] In known embodiments in the art, Chinese patent application CN113879549A discloses a rotor aerial refueling pod, including an outer shell, a ramjet air turbine at the front end of the outer shell, a fuel supply port, a control interface, and a connection port at the top of the outer shell, a pod camera base at the lower rear end of the outer shell, and a pod camera mounted on the pod camera base. The interior of the outer shell includes a fuel delivery system, a refueling system, a refueling cone, a rotor, a refueling pod controller, and a power assembly, but does not involve segmented design or universal design. Summary of the Invention

[0011] Based on the mission requirements of communication, reconnaissance, telemetry and control, this invention develops a multi-segment separable and combinable composite material aviation pod through a series of pod size type analysis. This pod is designed to adapt to different mission payload types, payload quantities, pod size and weight restrictions. It also features a standardized and universal design based on traditional pods, which reduces costs to a certain extent and solves the problems of poor versatility and functionality of existing pods.

[0012] The objective of this invention is achieved through the following technical solution:

[0013] A multi-segment detachable and combinable composite material aircraft pod includes a central pod, and also includes side pod A and side pod B. Side pod A is detachably connected to one end of the central pod, and side pod B is detachably connected to the other end of the central pod.

[0014] Furthermore, the middle compartment includes an upper middle beam, a lower middle beam, a middle compartment end frame A, and a middle compartment end frame B. One end of the upper middle beam is connected to one end of the lower middle beam, and the other end of the upper middle beam is connected to the other end of the lower middle beam, with the middle compartment end frame A detachably connected to the side compartment A, and the middle compartment end frame B detachably connected to the side compartment B.

[0015] Furthermore, the side compartment armor includes an upper side beam armor, a lower side beam armor, a side end frame armor, and a middle end frame armor. One end of the upper side beam armor is connected to one end of the lower side beam armor, and the other end of the upper side beam armor is connected to the other end of the lower side beam armor. The middle end frame armor is detachably connected to the middle compartment.

[0016] Furthermore, the side compartment B includes an upper side beam B, a lower side beam B, a middle frame B, and a side frame B. One end of the upper side beam B is connected to one end of the lower side beam B, and the other end of the upper side beam B is connected to the other end of the lower side beam B. The middle frame B is detachably connected to the middle compartment.

[0017] Furthermore, the end frame and the beam are connected by transition corner pieces, which are fixed to the end frame or beam by bolts and rivets.

[0018] Furthermore, the side compartment A and the middle compartment, as well as the side compartment B and the middle compartment, are all connected by bolts.

[0019] Furthermore, docking pins are provided between side compartment A and the middle compartment, and between side compartment B and the middle compartment.

[0020] Furthermore, the upper part of the middle compartment is equipped with a hoisting and positioning structure.

[0021] Furthermore, a shear support A connects the side compartment A and the middle compartment, and a shear support B connects the side compartment B and the middle compartment.

[0022] Furthermore, both the middle frame of the side compartment a and the middle end frame of the middle compartment a are provided with support mounting holes A that are positioned opposite each other. The shear support A is located inside the support mounting hole A and is connected to the edge of the support mounting hole A by bolts.

[0023] Furthermore, both the middle end frame B of the middle compartment and the middle end frame B of the side compartment B are provided with support mounting holes B in opposite positions. The shear support B is located inside the support mounting hole B and is connected to the edge of the support mounting hole B by bolts.

[0024] The beneficial effects of this invention are:

[0025] 1. This pod has relatively independent side compartments and a central compartment, which allows for a standardized design of the pod. Under the same type of mission payload, such as communication pods and reconnaissance pods, different sizes of pods can be formed by combining independent compartments according to functional capacity and specific requirements. This reduces the product development cycle and production costs to a certain extent.

[0026] 2. By combining carbon fiber with PMI (Polymerized Insulation Mixing), the weight of the pod is reduced, thus lessening the burden on its main load-bearing components. Simultaneously, the carbon fiber and PMI composite structure increases both the pod's stiffness and system damping, thereby optimizing the pod's mechanical properties and enabling it to perform vibration reduction and amplitude limiting functions.

[0027] 3. The shear-resistant structure at the connection between the side cabin and the middle cabin compensates for the decrease in strength and stiffness at the connection end frame after the pod is segmented, ensuring the strength of the pod segment after segmentation.

[0028] The aforementioned main solution of the present invention and its various further alternative solutions can be freely combined to form multiple solutions, all of which are solutions that can be adopted and are claimed by the present invention; furthermore, the (non-conflicting alternatives) can also be freely combined with each other and with other alternatives. Those skilled in the art, after understanding the solution of the present invention, will realize from the prior art and common general knowledge that there are many combinations, all of which are technical solutions to be protected by the present invention, and will not be exhaustively listed here. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the structure of the present invention.

[0030] Figure 2 This is a schematic diagram of the side compartment armor of the present invention.

[0031] Figure 3 This is a schematic diagram of the structure of the cabin in this invention.

[0032] Figure 4 This is a schematic diagram of the structure of side compartment B of the present invention.

[0033] Figure 5 This is a schematic diagram of the beam-slab structure of the present invention.

[0034] Figure 6 This is a structural breakdown diagram of the beam and slab of the present invention.

[0035] In the diagram: 1-Side compartment A, 2-Side compartment B, 3-Middle compartment, 4-Upper middle beam, 5-Lower middle beam, 6-Upper side beam A, 7-Lower side beam A, 8-Upper side beam B, 9-Lower side beam B, 10-Side end frame A, 11-Middle end frame A, 12-Middle compartment end frame A, 13-Middle compartment end frame B, 14-Middle end frame B, 15-Side end frame B, 16-Shear support A, 17-Shear support B, 18-Carbon fiber skin and PMI sandwich structure, 19-Carbon fiber skin, 20-Sandwich main beam, 21-Intermediate structure. Detailed Implementation

[0036] The following non-limiting examples are used to illustrate the present invention.

[0037] Example 1:

[0038] refer to Figures 1-4 As shown, a multi-section separable and modular composite material aircraft pod includes three sections: side pod A1, side pod B2, and center pod 3. These three sections are designed to be separable, with each section assembled independently. Side pod A1 is detachably connected to center pod 3 at one end, and side pod B2 is detachably connected to center pod 3 at the other end. Based on mission payload requirements, the dimensions of the center and side pods are determined. A special end-frame connection method enables the separation of the three sections. After independent assembly, the three sections are then combined into a complete pod using assembly tooling.

[0039] The mid-cabin 3 includes an upper mid-beam 4, a lower mid-beam 5, a mid-cabin end frame A 12, and a mid-cabin end frame B 13. One end of the upper mid-beam 4 is connected to one end of the lower mid-beam 5 via the mid-cabin end frame A 12, and the other end of the upper mid-beam 4 is connected to the other end of the lower mid-beam 5 via the mid-cabin end frame B 13. The mid-cabin end frame A 12 is detachably connected to the mid-end frame A 11 of the side cabin A 1 by bolts, and the mid-cabin end frame B 13 is detachably connected to the mid-end frame B 14 of the side cabin B 2 by bolts. The upper part of the upper mid-beam 4 of the mid-cabin 3 is equipped with a hoisting and positioning structure to realize the hoisting connection of the aircraft to the mid-cabin 3.

[0040] Side compartment A1 includes upper side beam A6, lower side beam A7, side end frame A10 and middle end frame A11. One end of upper side beam A6 is connected to one end of lower side beam A7 via side end frame A10, and the other end of upper side beam A6 is connected to the other end of lower side beam A7 via middle end frame A11. Middle end frame A11 is detachably connected to middle end frame A12 of middle compartment 3 via bolts.

[0041] Side compartment B2 includes upper side beam B8, lower side beam B9, middle end frame B14 and side end frame B15. One end of upper side beam B8 is connected to one end of lower side beam B9 via middle end frame B14, and the other end of upper side beam B8 is connected to the other end of lower side beam B9 via side end frame B15. Middle end frame B14 is detachably connected to middle end frame B13 of middle compartment 3 via bolts.

[0042] The end frames of the three pods are connected to the beams (i.e., beams) by transition corner fittings. The transition corner fittings are fixed to the end frames or beams by bolts and rivets. The transition corner fittings are connected to the end frames and beams in multiple directions by bolts and rivets, which provides a certain degree of reinforcement to the pods.

[0043] Side compartment A1 and middle compartment 3, and side compartment B2 and middle compartment 3 are all connected by bolts. In the process of assembling the three compartments into a whole compartment, the compartments are connected by bolts between middle end frame A11 and middle compartment end frame A12, and between middle compartment end frame B13 and middle end frame B14, to achieve basic connection and tensile strength between the compartments.

[0044] The end frames that need to be connected are machined with high precision at the connection point to ensure the flatness, perpendicularity and surface roughness of the connection point. At the same time, pins are designed at the connection point, that is, there are docking pins between side compartment A1 and middle compartment 3, and between side compartment B2 and middle compartment 3. When the compartments are docked, the pins are used to guide the alignment first, and then the end faces are fixed by connecting bolts.

[0045] Shear bracing A16 connects side compartment A1 to middle compartment 3, and shear bracing B17 connects side compartment B2 to middle compartment 3. These shear bracings enhance the shear and torsional resistance at the pod section connections. After the sections are connected, the shear bracing is installed last, with appropriate adjustments made during installation to ensure precision. The shear bracing is connected to the end frame support mounting holes using plate nuts and bolts, thus bearing the shear and torsional forces at the pod connections.

[0046] Both the middle frame A11 of the side compartment A1 and the middle end frame A12 of the middle compartment 3 are provided with support mounting holes A in opposite positions. The shear support A16 is located in the support mounting hole A and is connected to the edge of the support mounting hole A by bolts to ensure that the shear support A16 is fixed between the side compartment A1 and the middle compartment 3.

[0047] Both the middle end frame B13 of the middle compartment 3 and the middle end frame B14 of the side compartment B2 are provided with support mounting holes B in opposite positions. The shear support B17 is located in the support mounting hole B and is connected to the edge of the support mounting hole B by bolts to ensure that the shear support B17 is fixed between the side compartment B2 and the middle compartment 3.

[0048] refer to Figure 5 and Figure 6 As shown, since the pod is divided into three sections, the rigidity of the connection is reduced compared to an integrated pod. Therefore, carbon fiber composite materials are used for each component of the pod. In the main load-bearing components (i.e. beams and plates), carbon fiber skin and PMI sandwich structure 18 are used. This achieves weight reduction while ensuring the rigidity of the pod structure and increasing the damping of the system.

[0049] The main carbon fiber structural components are the six beams of the pod. The beams consist of a carbon fiber skin 19, a sandwich main beam 20, and an intermediate structure 21. The intermediate structure 21 includes a plate structure and plate beams. The plate structure and plate beams are connected and fixed by adhesive riveting. First, the plate beams are fixed to the corresponding positions of the plate structure using tooling. Adhesive is applied to the contact surfaces. Before the adhesive cures, rivets are pulled at the corresponding positions (the rivet surfaces are coated with adhesive to prevent electrochemical corrosion), which serves to strengthen the connection.

[0050] The slab structure adopts a partial A-layer method, with foam placed in the middle section on both sides of the inner wall of the slab and carbon fiber embedded parts placed at both ends, which can effectively improve the stiffness of the upper beam slab in the length direction. The solid embedded parts can hold pins and threaded sleeves for connecting other components (installing wire threaded sleeves to connect with transition plates and transition T-shaped parts).

[0051] The panel structure is formed in an autoclave using a single-sided mold. The mold surface is the aerodynamically oriented side of the product. An A-layer structure is employed, with a 2mm thick layer of carbon fiber prepreg applied to the mold surface. Then, carbon fiber and foam embeddings are placed in corresponding positions (the outer surfaces of the carbon fiber and foam embeddings are wrapped with adhesive film to improve the structural bonding strength during curing). Finally, another 2mm thick layer of carbon fiber prepreg is applied. The panels are then bagged, vacuum-sealed, and placed in an autoclave for curing.

[0052] Similarly, depending on the functional requirements, the middle cabin 3 can be further expanded into sections, and can be divided into two, three or more sections. The connection structure is similar to that of the three-section cabin, and the connection between the additional two adjacent middle cabins 3 can also adopt the above connection structure.

[0053] The foregoing basic examples and their further alternative examples of the present invention can be freely combined to form multiple embodiments, all of which are embodiments that can be adopted and claimed by the present invention. In the present invention, each alternative example can be arbitrarily combined with any other basic example and alternative example.

[0054] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multi-segment separable and combinable composite material aircraft pod, comprising a mid-section (3), characterized in that: It also includes side compartment A (1) and side compartment B (2), with side compartment A (1) being detachably connected to one end of the middle compartment (3), and side compartment B (2) being detachably connected to the other end of the middle compartment (3); The middle compartment (3) includes an upper middle beam (4), a lower middle beam (5), a middle compartment end frame A (12) and a middle compartment end frame B (13). One end of the upper middle beam (4) is connected to one end of the lower middle beam (5) via the middle compartment end frame A (12), and the other end of the upper middle beam (4) is connected to the other end of the lower middle beam (5) via the middle compartment end frame B (13). The middle compartment end frame A (12) is detachably connected to the side compartment A (1), and the middle compartment end frame B (13) is detachably connected to the side compartment B (2). The side compartment A (1) includes an upper side beam A (6), a lower side beam A (7), a side end frame A (10), and a middle end frame A (11). One end of the upper side beam A (6) is connected to one end of the lower side beam A (7) via the side end frame A (10), and the other end of the upper side beam A (6) is connected to the other end of the lower side beam A (7) via the middle end frame A (11). The middle end frame A (11) is detachably connected to the middle compartment (3). The side compartment B (2) includes an upper side beam B (8), a lower side beam B (9), a middle frame B (14), and a side frame B (15). One end of the upper side beam B (8) is connected to one end of the lower side beam B (9) via the middle frame B (14), and the other end of the upper side beam B (8) is connected to the other end of the lower side beam B (9) via the side frame B (15). The middle frame B (14) is detachably connected to the middle compartment (3). Shear support A (16) connects the side compartment A (1) and the middle compartment (3), and shear support B (17) connects the side compartment B (2) and the middle compartment (3). The middle frame A (11) of the side compartment A (1) and the middle compartment end frame A (12) of the middle compartment (3) are provided with support mounting holes A in opposite positions. The shear support A (16) is located inside the support mounting hole A and is connected to the edge of the support mounting hole A by bolts. The middle cabin (3) and the middle end frame (13) of the side cabin (2) are provided with support mounting holes (14) with opposite positions. The shear support (17) is located in the support mounting hole (17) and is connected to the edge of the support mounting hole (17) by bolts.

2. The multi-segment separable and combinable composite material aircraft pod according to claim 1, characterized in that: The end frame and the beam are connected by transition corner pieces, which are fixed to the end frame or beam by bolts and rivets.

3. The multi-segment separable and combinable composite material aircraft pod according to claim 1, characterized in that: The side compartment A (1) and the middle compartment (3) are connected by bolts, and the side compartment B (2) and the middle compartment (3) are connected by bolts. The side compartment A (1) and the middle compartment (3) and the side compartment B (2) and the middle compartment (3) are provided with connecting pins.

4. The multi-segment separable and combinable composite material aircraft pod according to claim 1, characterized in that: The upper part of the middle compartment (3) is equipped with a hoisting and positioning structure.

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