An aircraft top equipment compartment

Abstract

This application belongs to the field of aircraft top equipment compartment design technology, specifically relating to an aircraft top equipment compartment, including a front frame, a rear frame, a bottom panel, a cover, a front pad, and a rear pad; the front frame and the rear frame are arranged opposite each other, and their ends are connected to the left and right metal sidewalls inside the fuselage; the bottom panel is connected between the front frame and the rear frame, and is connected between the left and right metal sidewalls; the cover covers the front frame, the rear frame, and the left and right metal sidewalls, with its front and rear edges serrated to fit with the fuselage skin; the front pad and the rear pad are connected to the top outer side of the front frame and the rear frame, with their outer edges serrated, and are placed below the front and rear edges of the cover, extending into the underside of the fuselage skin; the overlapping areas of the front and rear pads and the front and rear edges of the cover are partially recessed to compensate for the thickness difference between the cover and the fuselage skin, so that the cover is flush with the outer side of the fuselage skin.

Description

Technical Field

[0001] This application belongs to the field of aircraft top equipment compartment design technology, and specifically relates to an aircraft top equipment compartment. Background Technology

[0002] The top equipment bay of an aircraft provides installation interfaces for airborne equipment such as electronics, fuel, environmental control, and liquid cooling systems, as well as maintains the normal operating environment for these systems.

[0003] With the increasing number of onboard equipment in modern aircraft, there is a requirement for the top equipment bay to have good volume ratio and maintainability, to facilitate the disassembly, assembly, and maintenance of onboard equipment, as well as good strength, rigidity, and waterproof performance. In view of this, this application is made. Summary of the Invention

[0004] The purpose of this application is to provide an aircraft top equipment bay to meet the needs of installing and maintaining airborne equipment in the aircraft top equipment bay.

[0005] The technical solution of this application is:

[0006] An aircraft top equipment compartment includes a front frame, a rear frame, a bottom panel, a cover, a front pad, and a rear pad.

[0007] The front and rear frames are positioned opposite each other, and the two ends are connected to the left and right metal sidewalls inside the body.

[0008] The bottom panel is connected between the front frame and the rear frame, as well as between the left and right metal side walls;

[0009] The cover is placed on the front frame, the rear frame, and above the left and right metal sidewalls, with the front and rear edges engaging with the serrated edges of the fuselage skin.

[0010] The projection lines of the serrated edges on the front and rear edges of the cover onto the horizontal plane of the aircraft structure are parallel to the projection lines of the leading and trailing edges of the wing or the leading edge of the fuselage.

[0011] The front and rear pads are connected to the top outer sides of the front and rear frames, with serrated outer edges. They are placed below the front and rear edges of the cover and extend under the fuselage skin.

[0012] The overlapping areas of the front and rear pads and the front and rear edges of the hatch are partially recessed to compensate for the thickness difference between the hatch and the fuselage skin, so that the hatch is flush with the outer surface of the fuselage skin.

[0013] The front and rear edges of the cap are connected to the front and rear pads by fasteners. One fastener is placed at the tip of the serration on the front and rear edges of the cap, and two fasteners are placed symmetrically on both sides of the peak and valley.

[0014] The outer edges of the front and rear pads have a straight structure at the serrated peaks and valleys, while the inner edges have an outward convex structure at the serrated peaks and valleys.

[0015] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the front frame and the rear frame are metal parts with ribs on one side, the ribs on the front frame are arranged in the forward direction, and the ribs on the rear frame are arranged in the aft direction.

[0016] Wiring holes and maintenance holes are provided on the front and rear frames to facilitate wiring and maintenance of airborne equipment inside the cabin.

[0017] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the bottom wall panel is a metal longitudinal and transverse stiffened sheet metal structure, the longitudinal and transverse stiffeners are respectively connected to the front frame, the rear frame and the left and right metal side walls, and L-shaped profiles are provided on the inner side of the front frame and the rear frame, and the bottom wall panel overlaps the L-shaped profiles at the front and rear.

[0018] Drainage holes are provided on the bottom panel.

[0019] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, adhesive tape is pasted at the gap between the front and rear edges of the access panel and the serrated edge of the fuselage skin.

[0020] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the cover is a honeycomb sandwich composite material.

[0021] The lid is divided into two parts, left and right.

[0022] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the fastener may specifically be a movable tray or a non-detachable cover lock.

[0023] According to at least one embodiment of this application, in the above-described aircraft top equipment compartment, a polytetrafluoroethylene sealing strip is provided between the cover and the front pad, the rear pad, and the left and right metal sidewalls.

[0024] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the front pad and the rear pad are metal parts;

[0025] The outer edges of the front and rear pads have a convex structure at the fastener connection points.

[0026] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, the front pad, the rear pad, and the fuselage skin are connected by a double-row staggered connection of high-strength bolts and nuts.

[0027] A bolt is placed at the tip of the serrated edge of the fuselage skin, and two bolts are placed symmetrically on both sides of the serration.

[0028] According to at least one embodiment of this application, the aforementioned aircraft top equipment compartment also includes supporting longitudinal beams;

[0029] Supporting longitudinal beams, such as Figure 5As shown, there are multiple detachable connections between the front and rear frames;

[0030] The supporting longitudinal beams at the joints of the flap sections have an I-shaped cross section, while the supporting longitudinal beams at other locations have a channel-shaped cross section.

[0031] According to at least one embodiment of this application, in the above-described aircraft top equipment compartment, the left and right side edges of the access cover are connected to the left and right metal sidewalls and the supporting longitudinal beams by fasteners.

[0032] According to at least one embodiment of this application, in the above-mentioned aircraft top equipment compartment, lug connectors are arranged on the front frame, rear frame, and support longitudinal beam, and the airborne equipment is connected and fixed by means of tie rod connection.

[0033] This application has at least the following beneficial technical effects:

[0034] An aircraft top equipment bay is provided. It has a simple overall structure, good strength, rigidity and waterproof performance, facilitates the disassembly and maintenance of airborne equipment, and has low detectability. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the structure of the aircraft top equipment compartment provided in the embodiments of this application;

[0036] Figure 2 This is a schematic diagram of the front-end frame and back-end frame provided in the embodiments of this application;

[0037] Figure 3 This is a cross-sectional view of the cover provided in an embodiment of this application;

[0038] Figure 4 This is a schematic diagram of the front pad and the rear pad provided in the embodiments of this application;

[0039] Figure 5 This is a schematic diagram of the supporting longitudinal beam provided in an embodiment of this application;

[0040] in:

[0041] 1-Front end frame; 2-Rear end frame; 3-Bottom panel; 4-Hand cover; 5-Front pad; 6-Rear pad; 7-Supporting longitudinal beam; 8-Fuselage skin.

[0042] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0043] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0044] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0045] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0046] An aircraft top equipment bay, such as Figure 1 As shown, it includes a front frame 1, a rear frame 2, a bottom wall panel 3, a cover 4, a front pad 5, a rear pad 6, and a supporting longitudinal beam 7.

[0047] Front-end frame 1 and back-end frame 2 are positioned relative to each other along the aircraft's flight path, as follows: Figure 2 As shown, the two ends are connected to the left and right metal sidewalls inside the fuselage. With the left and right metal sidewalls fixed in position, the distance between the front frame 1 and the rear frame 2 is determined according to the space requirements for the disassembly, assembly and maintenance of the airborne equipment.

[0048] The front frame 1 and the rear frame 2 are metal parts with ribs on one side. The ribs on the front frame 1 are arranged in the forward direction, and the ribs on the rear frame 2 are arranged in the backward direction.

[0049] Wiring holes and maintenance holes are provided on the front frame 1 and the rear frame 2 to facilitate wiring and maintenance of airborne equipment inside the cabin.

[0050] The bottom panel 3 connects between the front frame 1 and the rear frame 2, and is also connected between the left and right metal sidewalls. The space enclosed by the bottom panel 3, the front frame 1, the rear frame 2, and the left and right metal sidewalls constitutes the equipment compartment on the top of the aircraft.

[0051] The bottom wall panel 3 is a metal sheet metal structure with longitudinal and transverse stiffeners. The longitudinal and transverse stiffeners are connected to the front frame 1, the rear frame 2 and the left and right metal side walls respectively. The front frame 1 and the rear frame 2 are provided with L-shaped profiles on their inner sides. The bottom wall panel 3 overlaps the L-shaped profiles at the front and rear.

[0052] Drainage holes are provided on the bottom wall panel 3 to prevent water accumulation inside the cabin.

[0053] 4-fold lid Figure 3 As shown, the front and rear frames 1 and 2, as well as the upper parts of the left and right metal sidewalls, are covered with serrated edges that fit with the fuselage skin 8. The gaps between the serrations are strictly controlled according to the requirements for the seam width of the low-observable aircraft skin. Low-observable tape is also pasted in the gaps between the serrations to ensure the low observability of the aircraft.

[0054] The projection lines of the serrated edges on the front and rear edges of the cover 4 onto the horizontal plane of the aircraft structure are parallel to the projection lines of the leading and trailing edges of the wing or the leading edge of the fuselage. The number of serrations should follow the principle of minimizing the number of serrations, and the tooth height should be determined according to the design requirements for low detectability.

[0055] The cover 4 is a honeycomb sandwich composite material, which is lightweight and has good rigidity.

[0056] Based on the size of the equipment compartment opening and the maintenance frequency of the airborne equipment, the cover 4 is divided into sections to facilitate easy disassembly and removal during maintenance of the airborne equipment. Typically, the cover 4 can be divided into two parts, left and right. When maintaining the airborne equipment, a single section or the entire cover can be disassembled as needed.

[0057] Front pad 5, rear pad 6 as follows Figure 4 As shown, it is connected to the top outer side of the front frame 1 and the rear frame 2. Specifically, it can be connected to the top edge strip of the front frame (1) and the rear frame (2). The outer edge is serrated and is placed under the front and rear edges of the cover 4, extending into the underside of the body skin 8.

[0058] The fuselage skin 8 is made of metal or composite materials, and its thickness differs from that of the cover 4, which is typically thicker. The front pad 5 and rear pad 6 are partially recessed in the overlapping areas with the front and rear edges of the cover 4. This serves two purposes: firstly, it positions the cover 4, and secondly, it compensates for the thickness difference between the cover 4 and the fuselage skin 8, ensuring that the cover 4 is flush with the outer surface of the fuselage skin 8.

[0059] The front and rear edges of the cover 4 are connected to the front pad 5 and the rear pad 6 by fasteners. The distance between the front and rear edges of the cover 4 and the edges of the front pad 5 and the rear pad 6 is 2.5D when the fuselage skin 8 is a composite material and 2D+1 when the fuselage skin 8 is a metal part, where D is the diameter of the fastener.

[0060] A fastener is placed at the tip of the serrated edge of the front and rear edges of the cover 4, and two fasteners are placed symmetrically on both sides of the peak and valley, serving as the edge pressing fasteners for the serrated edge of the front and rear edges of the cover 4, and connecting with the front pad 5 and the rear pad 6.

[0061] The fasteners can be movable pallets or non-detachable cover locks. The spacing of the movable pallets is 6D-8D, and the edge distance of the movable pallets is 3D when the body skin 8 is a composite material and 2D+1 when the body skin 8 is a metal material. The spacing and edge distance of the non-detachable cover locks are increased accordingly, with a spacing of 10D or more.

[0062] A polytetrafluoroethylene sealing strip is installed between the cover 4 and the front pad 5, the rear pad 6, and the left and right metal sidewalls to prevent water from entering.

[0063] The front pad 5 and the rear pad 6 are metal parts designed with a serrated shape to reduce structural weight. Furthermore, the outer edges of the front pad 5 and the rear pad 6 can be designed to have a straight structure at the peaks and valleys of the serrations, and an outward convex structure at the fastener connection points. The inner edges also have an outward convex structure at the peaks and valleys of the serrations, specifically a small tooth structure. This design can enhance waterproof performance, increase the distance between the pad and the fasteners, and enhance the fatigue resistance of the structure.

[0064] The front pad 5, rear pad 6 and fuselage skin 8 are connected by double rows of high-lock bolts and nuts. One bolt is placed at the tip of the serrated edge of the fuselage skin 8, and two bolts are placed symmetrically on both sides of the peak and valley. The bolt edge distance is 2D+1 and the spacing is 4D-6D.

[0065] Supporting longitudinal beam 7 Figure 5 As shown, there are multiple detachable connections between the front frame 1 and the rear frame 2 to enhance the overall strength and rigidity of the structure. The supporting longitudinal beam 7 at the joint of the cover 4 is designed to have an I-shaped cross section, while the supporting longitudinal beam 7 at other locations has a channel-shaped cross section.

[0066] The left and right sides of the cover 4 are also connected to the left and right metal sidewalls and the supporting longitudinal beam 7 with fasteners.

[0067] The bottom wall panel 3 can provide support for the installation of airborne equipment. The airborne equipment can be connected and fixed by arranging lug joints on the front frame 1, rear frame 2, and support longitudinal beam 7 and connecting them with tie rods.

[0068] The aircraft top equipment bay disclosed in the above embodiments has a simple overall structure, good strength, rigidity, and waterproof performance, facilitates the disassembly and maintenance of airborne equipment, and has low detectability.

[0069] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An aircraft top equipment bay, characterized in that, Includes front frame (1), rear frame (2), bottom wall panel (3), opening cover (4), front pad (5), rear pad (6); The front frame (1) and the rear frame (2) are set opposite each other, and the two ends are connected to the left and right metal sidewalls inside the body; The bottom panel (3) is connected between the front frame (1) and the rear frame (2), and between the left and right metal sidewalls; The cover (4) covers the front frame (1), the rear frame (2) and the upper part of the left and right metal sidewalls, with the front and rear edges serrated with the fuselage skin (8); The projection lines of the serrated edges on the front and rear edges of the flap (4) onto the horizontal plane of the aircraft structure are parallel to the projection lines of the leading and trailing edges of the wing or the leading edge of the fuselage. The front pad (5) and the rear pad (6) are connected to the top outer side of the front frame (1) and the rear frame (2), with the outer edge being serrated. They are placed below the front and rear edges of the cover (4) and extend into the underside of the fuselage skin (8). The overlapping areas of the front pad (5), rear pad (6) and the front and rear edges of the cover (4) are partially recessed to compensate for the thickness difference between the cover (4) and the fuselage skin (8), so that the cover (4) is flush with the outside of the fuselage skin (8). The front and rear edges of the cover (4) are connected to the front pad (5) and the rear pad (6) by fasteners. A fastener is arranged at the tip of the serrated edge of the front and rear edges of the cover (4), and two fasteners are arranged symmetrically on both sides of the peak and valley. The outer edges of the front pad (5) and the rear pad (6) are flat at the serrated peaks and valleys, while the inner edges have a convex structure at the serrated peaks and valleys.

2. The aircraft top equipment bay according to claim 1, characterized in that, The front frame (1) and the rear frame (2) are metal parts with ribs on one side. The upper ribs of the front frame (1) are arranged in front of the heading, and the upper ribs of the rear frame (2) are arranged in rear of the heading. Wiring holes and maintenance holes are provided on the front frame (1) and the rear frame (2) to facilitate wiring and maintenance of the airborne equipment inside the cabin.

3. The aircraft top equipment bay according to claim 2, characterized in that, The bottom wall panel (3) is a metal longitudinal and transverse stiffened sheet metal structure. The longitudinal and transverse stiffeners are connected to the front frame (1), the rear frame (2) and the left and right metal side walls respectively. The front frame (1) and the rear frame (2) are provided with L-shaped profiles on the inside. The bottom wall panel (3) overlaps the L-shaped profiles at the front and back. Drainage holes are provided on the bottom wall panel (3).

4. The aircraft top equipment bay according to claim 3, characterized in that, Adhesive tape is pasted between the front and rear edges of the cover (4) and the serrations of the fuselage skin (8).

5. The aircraft top equipment bay according to claim 4, characterized in that, The cover (4) is a honeycomb sandwich composite material; The lid (4) is divided into two parts, left and right.

6. The aircraft top equipment bay according to claim 5, characterized in that, The fasteners can be either movable trays or non-detachable cover locks.

7. The aircraft top equipment bay according to claim 6, characterized in that, A polytetrafluoroethylene sealing strip is provided between the cover (4) and the front pad (5), the rear pad (6) and the left and right metal sidewalls.

8. The aircraft top equipment bay according to claim 7, characterized in that, The front pad (5) and the rear pad (6) are metal parts; The outer edges of the front pad (5) and the rear pad (6) have an outward convex structure at the fastener connection point.

9. The aircraft top equipment bay according to claim 8, characterized in that, The front pad (5), rear pad (6) and fuselage skin (8) are connected by double-row staggered high-lock bolts and nuts; A bolt is placed at the tip of the serrated edge of the fuselage skin (8), and two bolts are placed symmetrically on both sides of the peak and valley.

10. The aircraft top equipment bay according to claim 9, characterized in that, It also includes the supporting longitudinal beam (7); There are multiple supporting longitudinal beams (7), which are detachably connected between the front frame (1) and the rear frame (2); The supporting longitudinal beam (7) located at the joint of the flap (4) has an I-shaped cross section.

11. The aircraft top equipment bay according to claim 10, characterized in that, The left and right sides of the cover (4) are connected to the left and right metal sidewalls and the supporting longitudinal beam (7) by fasteners.

12. The aircraft top equipment bay according to claim 11, characterized in that, Ear-shaped connectors are arranged on the front frame (1), rear frame (2), and supporting longitudinal beam (7), and the airborne equipment is connected and fixed by means of tie rod connection.

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