A military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures

Abstract

The present application belongs to the technical field of aircraft structure design, and particularly relates to a military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures, the floor panel comprising a honeycomb panel (1), an edge wrapping piece (2), a sealing strip (3) and a noise reduction foam (4); the edge wrapping piece (2) is wrapped around the edges of the honeycomb panel (1); the sealing strip (3) is located at the connection between the lower panel surface of the honeycomb panel (1) and the frame (12); the noise reduction foam (4) is adhered to the lower panel surface of the honeycomb panel (1); wherein the honeycomb panel (1) has a flat head inlay (5) penetrating the upper and lower panels of the panel near the edges, and a countersunk inlay (6) is penetrated in the middle, and the countersunk bolt (9) of the equipment is connected to the frame (12) below the sealing piece (3) after passing through the two inlays. The floor panel of the present application has a simple structure, is easy to install, has good maintainability, and is highly adaptable.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure design, and in particular relates to a military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures. Background Art

[0002] The floor panel of the mission cabin of a military aircraft is located in the operator's work area and must meet the connection and load-bearing requirements of the workbench and equipment cabinets above it, as well as the requirements of sound insulation and noise reduction of the mission cabin. The lower equipment compartment under the mission cabin floor of a military aircraft is equipped with a large number of equipment, which is the source of noise and vibration, which puts higher requirements on the vibration reduction and noise reduction of the floor panel. Summary of the invention

[0003] In order to solve the above problems, the present application provides a military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures, mainly including:

[0004] Honeycomb panels, multiple honeycomb panels are spliced ​​together to form the floor panels of the military aircraft mission cabin;

[0005] Edge wrapping parts, covering the edges of the honeycomb panel;

[0006] A sealing strip, located at the connection between the lower plate surface of the honeycomb panel and the frame, the sealing strip includes a quadrilateral frame strip and a plurality of middle strips located inside the quadrilateral frame strip and parallel to the two side edges;

[0007] Noise reduction foam, adhered to the lower surface of the honeycomb panel;

[0008] Among them, the honeycomb panel has a flat head inlay penetrating the upper and lower panels of the panel near the edges. The countersunk bolts used to fix the equipment pass through the flat head inlay, and then pass through the quadrilateral frame strip of the sealing belt and the frame below the sealing belt, and then connect with the spring clamp nut;

[0009] The interior of the honeycomb panel has a countersunk inlay that penetrates the upper and lower surfaces of the panel. The countersunk bolts used to fix the equipment pass through the countersunk inlay, further through the middle strip of the sealing belt and the frame below the sealing belt, and then are connected to the spring clamp nuts.

[0010] Preferably, the honeycomb panel is a rectangular structure formed by secondary segmentation of a finished carbon fiber or glass fiber honeycomb sandwich panel.

[0011] Preferably, adhesive is filled between the four edges of the honeycomb panel and the edging member.

[0012] Preferably, the filling width of the adhesive is 3-5 mm, and the single-side edging width of the edging piece is not less than 25 mm.

[0013] Preferably, the edging piece is made of polytetrafluoroethylene raw material through an expansion process to form fibers, which are then woven.

[0014] Preferably, the flat head insert and the countersunk head insert are both of a configuration with a thin middle and flanges at both ends, the upper flange has a tapered hole, the middle is a through hole, and the lower flange has two adhesive injection holes.

[0015] Preferably, the middle parts of the flat head insert and the countersunk head insert have a gear groove or a hexagonal column structure on the outer cylinder surface.

[0016] Preferably, a U-shaped vibration-damping pad covering the mounting edge of the frame is provided between the frame and the spring clip nut.

[0017] Preferably, the sealing tape is made of expanded polytetrafluoroethylene material, has its own adhesive backing, and is directly adhered to the floor panel overlapped with the frame.

[0018] Preferably, the noise reduction foam is made of self-extinguishing flexible polyurethane foam.

[0019] The present application can meet the requirements of sound insulation, noise reduction and corrosion resistance, and can also meet the connection requirements of workbenches or equipment tables, has strong cargo carrying capacity and structural rigidity, can be quickly installed and disassembled, and has strong versatility. The floor panel of the present application has a simple structure, is easy to install, has good maintainability, and is highly adaptable. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the structural composition of a floor panel of a preferred embodiment of the military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures of the present application.

[0021] Figure 2 This application Figure 1 Schematic diagram of the connection between two floor panels and a frame in the illustrated embodiment.

[0022] Figure 3 This application Figure 1 Top view of the floor panel of the illustrated embodiment.

[0023] Figure 4 This application Figure 3 An enlarged schematic diagram of the structure at location Ⅰ of the illustrated embodiment.

[0024] Figure 5 This application Figure 4 AA cross-sectional structural schematic diagram of the embodiment shown.

[0025] Figure 6 This application Figure 3 An enlarged schematic diagram of the structure at location II of the illustrated embodiment.

[0026] Figure 7 This application Figure 6 BB cross-sectional structural schematic diagram of the embodiment shown.

[0027] Figure 8 This application Figure 1 The illustrated embodiment is a schematic structural diagram of a preferred embodiment of a flat head inlay or a countersunk head inlay.

[0028] Fig. 9 This application Figure 1 A schematic structural diagram of another preferred embodiment of the flat head insert or countersunk head insert of the illustrated embodiment.

[0029] Among them, 1-honeycomb panel, 2-edging piece, 3-sealing tape, 31-quadrilateral frame strip, 32-middle strip, 4-noise reduction foam, 5-flat head inlay, 6-countersunk head inlay, 7-spring clip nut, 8-U-shaped vibration damping pad, 9-countersunk bolt, 10-flat sealing pad, 11-adhesive, 12-skeleton. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0031] The present application provides a military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures, such as Figure 1-Figure 7 As shown, it mainly includes:

[0032] Honeycomb panel 1, multiple honeycomb panels 1 are spliced ​​together to form a military aircraft mission cabin floor panel;

[0033] The edge wrapping member 2 is wrapped around the edges of the honeycomb panel 1;

[0034] The sealing strip 3 is located at the connection between the lower plate surface of the honeycomb panel 1 and the frame 12, and the sealing strip 3 includes a quadrilateral frame strip 31 and a plurality of middle strips 32 located inside the quadrilateral frame strip and parallel to two side edges;

[0035] Noise reduction foam 4, adhered to the lower surface of the honeycomb panel 1;

[0036] The honeycomb panel 1 has a flat-head inlay 5 passing through the upper and lower surfaces of the panel near the edges. The countersunk bolt 9 for fixing the equipment passes through the flat-head inlay 5, and then passes through the quadrilateral frame strip 31 of the sealing belt 3 and the frame 12 below the sealing belt 3, and then is connected with the spring clamp nut 7.

[0037] The interior of the honeycomb panel 1 has a countersunk inlay 6 that passes through the upper and lower surfaces of the panel. The countersunk bolt 9 used to fix the equipment passes through the countersunk inlay 6, further passes through the middle strip 32 of the sealing belt 3 and the frame 12 below the sealing belt 3, and then is connected to the spring clamp nut 7.

[0038] In this embodiment, reference Figure 1 The flat-head inlay 5 is mainly installed near the edges of the honeycomb panel 1. Figure 2 A structural schematic diagram of the joint of two honeycomb panels 1 is given, wherein the sides of the two honeycomb panels 1 are provided with flat-head inlays 5, which are then fixed to a frame 12 below by countersunk bolts 9. With the help of the flat-head inlays 5, the equipment in the mission cabin that is relatively light in weight or relatively less disassembled can be directly connected to the floor panel and the frame through its countersunk bolts 9. At the equipment connection hole, with the help of the flat-head inlays 5, a detachable connection structure is formed between the honeycomb sandwich structure and other structures, which is convenient for structural maintenance. In addition, the floor panel of the present application, i.e., the honeycomb panel 1, is divided into rectangular blocks, and the honeycomb panel is provided with corresponding equipment base through grooves where the equipment in the cabin is directly connected to the floor frame. Figure 1 The open grooves around the honeycomb panel are where the seat rail base and the floor frame are connected.

[0039] Similar reference Figure 1 , a countersunk inlay 6 is installed inside the honeycomb panel 1, and two countersunk inlays 6 are arranged at each installation position, which also provides installation space for countersunk bolts 9 so as to be connected with the frame 12 below. In addition, the center of the hole of the countersunk inlay 6 is not less than 2D+1mm from the edge of the floor, where D is the diameter of the countersunk inlay 6. The number of bushings is determined according to the size of the floor. Generally, a single floor has no less than 8 bushings, which are distributed at the four corners of the floor and are evenly arranged at 400-600mm in the longitudinal direction.

[0040] In some optional embodiments, the honeycomb panel 1 is a rectangular structure formed by secondary segmentation of a finished carbon fiber or glass fiber honeycomb sandwich panel.

[0041] In this embodiment, the honeycomb panel 1 is formed by secondary segmentation of mature carbon fiber or glass fiber honeycomb sandwich panel products according to the load requirements. The floor panel is divided into rectangular blocks. The size of the panel blocks is limited by the supply size of the panel products (the size of domestic composite floor is not more than 1.2m×2.4m at present), and mainly considers the disassembly requirements and the layout requirements of the system workbench interface. Considering that one person can easily complete the handling and installation, the weight of a single block is controlled below 5kg as much as possible.

[0042] In some optional embodiments, adhesive 11 is filled between the four edges of the honeycomb panel 1 and the edging member 2 .

[0043] In some optional implementations, the filling width of the adhesive 11 is 3-5 mm, and the single-side edging width of the edging piece 2 is not less than 25 mm.

[0044] In some optional embodiments, the edging piece 2 is made of polytetrafluoroethylene raw material through an expansion process to form fibers, which are then woven.

[0045] In the above embodiment, after the honeycomb panel 1 is formed by secondary segmentation, the sharp corner is beveled at 45°, and the edges of the panel are sealed with honeycomb edge filling adhesive, and the filling width is 3mm~5mm. In addition to filling with adhesive, the panel is edged with expanded polytetrafluoroethylene woven tape (with self-adhesive backing), i.e., the edge wrapping piece 2, and the width of the single side edge wrapping is not less than 25mm. In this embodiment, the edge wrapping piece 2 can be formed by splicing.

[0046] The braided tape used for the edge wrapping 2 is made of polytetrafluoroethylene raw materials through an expansion process into fibers, and then braided. The double edge sealing using adhesive and expanded polytetrafluoroethylene braided tape can seal the cut of the floor panel to the maximum extent, preventing moisture from entering the honeycomb.

[0047] In some optional embodiments, such as Figure 8 and Fig. 9 As shown, the flat head insert 5 and the countersunk head insert 6 are both thin in the middle and have flanges at both ends. The upper flange has a tapered hole and a through hole in the middle, and the lower flange has two adhesive injection holes.

[0048] In some optional embodiments, the middle parts of the flat head insert 5 and the countersunk head insert 6 have a gear groove or a hexagonal prism structure on the outer cylinder surface. Figure 8 and Fig. 9 These two structural forms are respectively given, and the bonding area with the honeycomb floor is increased and the torsional bearing capacity of the honeycomb inlay is ensured by the gear groove or the protruding hexagonal prism structure. In this embodiment, the flat head inlay 5 and the countersunk head inlay 6 are both made of stainless steel, and the surface is passivated.

[0049] In some optional embodiments, a U-shaped vibration-damping pad 8 covering the mounting edge of the frame is provided between the frame 12 and the spring clamp nut 7 .

[0050] refer to Figure 2 A spring clamp nut 7 is provided at the connection hole of the floor frame, and a countersunk bolt passes through the floor panel inlay (referring to the flat head inlay 5 and the countersunk head inlay 6) and the frame and is fixed at the spring clamp nut 7. A flat sealing gasket 10 is provided in the tapered hole of the floor panel inlay, and a U-shaped vibration-damping gasket 8 is provided between the U-shaped slot of the spring clamp nut and the frame. Both gaskets are made of expanded polytetrafluoroethylene and play the role of vibration and noise reduction and sealing and corrosion prevention between structures.

[0051] In some optional embodiments, the sealing tape 3 is made of expanded polytetrafluoroethylene material, has its own adhesive backing, and is directly adhered to the floor panel overlapped with the frame.

[0052] In some optional embodiments, the noise reduction foam 4 is made of self-extinguishing soft polyurethane foam. In this embodiment, 30mm thick soft polyurethane foam (HB5404-1988) is laid on the lower surface of the floor of the equipment cabin, working cabin, and rest cabin. The foam needs to avoid the crossbeams, longitudinal beams and supports under the floor. At the same time, the foam is not laid on the openings on the floor, and the openings of the same size as the floor are retained. Through this vibration reduction and noise reduction measure, the comfort of the mission cabin is further improved.

[0053] The present application has a simple structure, is easy to install, has good sound insulation, noise reduction and anti-corrosion measures, meets the installation requirements of workbenches and equipment tables, has good maintainability and strong adaptability.

[0054] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures, characterized in that: include: Honeycomb panel (1), a plurality of honeycomb panels (1) are spliced ​​together to form a floor panel for a military aircraft mission cabin; An edge wrapping member (2) wrapping around the edges of the honeycomb panel (1); A sealing strip (3) located at the connection between the lower plate surface of the honeycomb panel (1) and the frame (12), the sealing strip (3) comprising a quadrilateral frame strip (31) and a plurality of middle strips (32) located inside the quadrilateral frame strip and parallel to two side edges; Noise reduction foam (4), adhered to the lower surface of the honeycomb panel (1); The honeycomb panel (1) has a flat-head inlay (5) passing through the upper and lower surfaces of the panel near the edges thereof, and the countersunk bolt (9) for fixing the device passes through the flat-head inlay (5), and then passes through the quadrilateral frame strip (31) of the sealing strip (3) and the frame (12) below the sealing strip (3), and is connected to the spring clamp nut (7); The honeycomb panel (1) has a countersunk inlay (6) penetrating the upper and lower surfaces of the panel. The countersunk bolt (9) for fixing the device passes through the countersunk inlay (6), further passes through the middle strip (32) of the sealing strip (3) and the frame (12) below the sealing strip (3), and is connected to the spring clamp nut (7).

2. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: The honeycomb panel (1) is a rectangular structure formed by secondary segmentation of a finished carbon fiber or glass fiber honeycomb sandwich panel.

3. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: Adhesive (11) is filled between the four edges of the honeycomb panel (1) and the edge wrapping piece (2).

4. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 3, characterized in that: The filling width of the adhesive (11) is 3-5 mm, and the single-side hemming width of the hemming piece (2) is not less than 25 mm.

5. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: The edging piece (2) is made from polytetrafluoroethylene raw material through an expansion process to form fibers, which are then woven.

6. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: The flat head inlay (5) and the countersunk head inlay (6) are both of a configuration with a thin middle and flanges at both ends, the upper flange having a tapered hole and a through hole in the middle, and the lower flange having two adhesive injection holes.

7. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 6, characterized in that: The middle parts of the flat head insert (5) and the countersunk head insert (6) have a gear groove or a hexagonal column structure on the outer cylinder surface.

8. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: A U-shaped vibration-damping pad (8) covering the mounting edge of the frame is provided between the frame (12) and the spring clamp nut (7).

9. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: The sealing tape (3) is made of expanded polytetrafluoroethylene material, has its own adhesive backing, and is directly adhered to the floor panel overlapped with the frame.

10. The military aircraft mission cabin floor panel with multiple noise reduction and anti-corrosion measures as claimed in claim 1, characterized in that: The noise reduction foam (4) is made of self-extinguishing soft polyurethane foam plastic.

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