Large-slenderness-ratio split type light skin reinforced cabin structure

Abstract

The invention relates to the field of structural design, and provides a large slenderness ratio split type light skin reinforced cabin structure which comprises a skin cylinder, short boss welding blocks, long boss welding blocks and axial reinforcing ribs, the short boss welding blocks are welded to the skin cylinder, the long boss welding blocks and the transverse reinforcing ribs form a cylindrical shell, and the long boss welding blocks are welded to the long boss welding blocks. The cylindrical shell is cut along the horizontal reference line to form a split type lower shell and a split type upper shell, and the split type lower shell and the split type upper shell are closed through a connecting strip. According to the invention, mechanical interfaces such as equipment mounting holes, antenna mounting holes, test ports, front and rear end frame connecting holes and the like are processed by adopting a metal plate forming process and an in-cabin spot welding reinforcing rib forming process, meanwhile, a butt joint end frame structure is spot-welded at a split position, and finally, the split type light skin reinforced cabin body structure with a large slenderness ratio is obtained. The problems of feasibility and assembly manufacturability of installation of large-size complex equipment in the cabin with the large slenderness ratio are solved, and meanwhile the extreme requirement for light weight of the cabin is met.

Description

Technical Field

[0001] The invention relates to the field of structural design, in particular to a cabin structure with a large slenderness ratio split-type lightweight skin reinforcement. Background Art

[0002] At present, most cabins at home and abroad adopt an integral structure. The equipment on the missile enters the cabin through the axial front and rear ports and is fixed to the inside of the cabin by wall mounting. For cabins with large slenderness ratios (diameter is usually <φ500mm, slenderness ratio>1.7), the assembly personnel cannot drill into the cabin to operate. When installing large-volume equipment, there are problems such as poor assembly processability or even inability to assemble. At the same time, most of the cabins are formed by casting and other processes, the cabin wall thickness is locally reinforced, and many non-installation surfaces inside the cabin cannot be precisely processed to the designed size, which cannot meet the urgent needs of lightweight design of the cabin.

[0003] Therefore, it is necessary to design a cabin that can install large-volume equipment (the maximum outer diameter of the equipment is larger than the inner diameter of the front and rear ports of the cabin), taking into account the extreme needs of facilitating the processing of the cabin's internal structure and lightweight cabin. To this end, the present invention designs a cabin structure with a large slenderness ratio and a light-weight skin reinforcement, which solves the above-mentioned problems. Summary of the invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a cabin structure with a large slenderness ratio and a flap-type lightweight skin reinforcement. The problem to be solved is the feasibility and assembly process difficulty of installing large-sized complex equipment (such as a liquid power system) in a cabin with a large slenderness ratio, while meeting the extreme demand for lightweight cabins. The present invention provides a design and manufacturing scheme for a flap-type lightweight skin reinforcement cabin structure, which realizes the manufacturability design of 1mm thin-walled flap-type upper and lower half cabins in the cabin, improves the utilization efficiency of the cabin's internal space and expands the operating space when installing equipment in the cabin, and can also realize the quick closing of the flap-type half cabins.

[0005] According to the present invention, a cabin structure with a large length-slenderness ratio and a light-weight skin reinforcement is provided, comprising: a skin cylinder, a short boss welding block, a long boss welding block and an axial reinforcement rib, the skin cylinder is welded with a short boss welding block, a long boss welding block and a transverse reinforcement rib to form a cylindrical shell, the cylindrical shell is cut along a horizontal reference line to form a split lower shell and a split upper shell, and the split lower shell and the split upper shell are connected by a connecting strip;

[0006] The skin cylinder includes a front column section skin, annular reinforcement ribs, a rear column section skin, a front docking frame and a rear docking frame. The front end of the front column section skin is welded with a front docking frame, the rear end of the front column section skin is welded with a rear column section skin, the rear end of the rear column section skin is welded with a rear docking frame, and annular reinforcement ribs are welded at the connection between the front column section skin and the rear column section skin.

[0007] Preferably, the axial reinforcing rib is in the shape of an elongated strip, and the cross section of the axial reinforcing rib is in the shape of a "convex" character, and the convex-shaped bottom of the axial reinforcing rib is welded to the skin cylinder.

[0008] Preferably, the axial reinforcing ribs include first axial reinforcing ribs, second axial reinforcing ribs and third axial reinforcing ribs, and the axes of the first axial reinforcing ribs, the second axial reinforcing ribs and the third axial reinforcing ribs are maintained on the same horizontal line;

[0009] The first axial reinforcement rib is located between the front column segment skin and the annular reinforcement rib, the second axial reinforcement rib is located between the annular reinforcement rib and the long boss welding block, and the third axial reinforcement rib is located between the long boss welding block and the rear docking frame.

[0010] Preferably, countersunk through holes are processed on the front docking frame and the rear docking frame in the cylindrical shell, and the short boss welding block and the long boss welding block are respectively matched with countersunk through holes in the rear column section skin.

[0011] Preferably, the connecting strip is made of titanium alloy and is in a fishbone shape;

[0012] The connecting strips include an upper connecting strip and a lower connecting strip. The lower connecting strip is welded on the split lower shell body, and connecting through holes are arranged on the lower connecting strip. The connecting through holes are screwed and riveted with support plate nuts to form a split lower cabin body; the upper connecting strip is welded on the split upper shell body, and connecting countersunk holes are punched on the upper connecting strip to form a split upper cabin body.

[0013] Preferably, a rectangular groove is provided on the lower connecting strip, and a silicone rubber sealing strip is bonded in the rectangular groove.

[0014] Preferably, the equipment bracket is screwed onto the inner wall of the split-flap lower cabin, and the equipment bracket is ring-shaped;

[0015] A self-locking nut or a self-locking wire screw sleeve is installed on the equipment installation interface on the cylindrical shell or the equipment bracket to realize the anti-loosening design of the connection between the equipment and the cabin.

[0016] Preferably, a front end frame and a rear end frame are respectively screwed on both ends of the split lower cabin body, the front end frame is adaptably connected to the front docking frame, and the rear end frame is adaptably connected to the rear docking frame.

[0017] Preferably, the petal-type lower cabin body and the petal-type upper cabin body are screwed together to form a cabin body, and a low-density flexible silicone rubber-based heat-resistant coating is sprayed on the outer surface of the cabin body;

[0018] A countersunk hole is provided on the outer surface of the cabin, and the countersunk hole is adapted to be installed with a fixing screw.

[0019] Preferably, an antenna installation interface is provided at the connection between the split-flap lower cabin body and the split-flap upper cabin body, and the antenna structure passes through the antenna installation interface.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] (1) The present invention improves the utilization efficiency of the internal space of the cabin and expands the operating space for installing equipment in the cabin through the split design of the split lower cabin and the split upper cabin, and can also realize the quick closing of the split half cabin;

[0022] (2) The present invention achieves the connection strength at the cabin fixing point through the boss welding block, cooperates with the welding of the fishbone-shaped connecting strip to reduce the weight, and locally strengthens the installation interface on the cabin without thickening the cabin over a large area, thereby improving the cabin lightweight efficiency;

[0023] (3) The present invention adds long strip axial reinforcing ribs to increase the bending resistance of the thin-walled cabin; designs an annular equipment bracket, which can strengthen the connection strength and rigidity of the upper and lower cabins;

[0024] (4) The heat-resistant coating is sprayed on the cabin exterior of the present invention to provide heat protection for the equipment inside the cabin; and the silicone rubber sealing strip is used to achieve heat sealing at the interface between the upper and lower cabins. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0026] Figure 1 It is a schematic diagram of a cabin structure with a split-flap lightweight skin reinforcement provided by the present invention;

[0027] Figure 2 It is a front view of the skin cylinder provided by the present invention;

[0028] Figure 3 is a front view of the cylindrical housing provided by the present invention;

[0029] Figure 4 is a schematic diagram of the split-flap lower housing after wire cutting provided by the present invention;

[0030] Figure 5 It is a schematic diagram of the split-flap upper shell;

[0031] Figure 6 It is a schematic diagram of the split-flap lower cabin body provided by the present invention after the lower connecting strip is welded and the supporting plate nut is riveted;

[0032] Figure 7 This is the front view of the split-flap lower cabin;

[0033] Figure 8 yes Figure 7 A partial view of the connecting strip along the AA line section;

[0034] Fig. 9 It is a schematic diagram of the split-flap upper cabin body provided by the present invention after the upper connecting strip is welded and the supporting plate nut is riveted;

[0035] Fig.10 This is the front view of the split-flap upper cabin;

[0036] Fig.11 yes Fig.10 A partial view of the connecting strip along the BB line section;

[0037] Fig.12 yes Figure 1 A cross-sectional view of

[0038] Among them, (a) is the main view of the cabin structure, (b) is the left view of the CC line section, and (c) is a partial enlarged view of the CC section.

[0039] The figure shows: front column segment skin 1, annular reinforcement ribs 2, rear column segment skin 3, front docking frame 4, rear docking frame 5, skin cylinder 6, short boss welding block 7, long boss welding block 8, first axial reinforcement ribs 9, second axial reinforcement ribs 10, third axial reinforcement ribs 11, split lower shell 12, split upper shell 13, first lower connecting strip 14, second lower connecting strip 15, third lower connecting strip 16, first upper connecting strip 17, second upper connecting strip 18, third upper connecting strip 19, split lower cabin 20, split upper cabin 21, front end frame 22, equipment bracket 23, rear end frame 24. DETAILED DESCRIPTION

[0040] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0041] Example

[0042] According to the present invention, a cabin structure with large length-slenderness ratio and light-weight skin reinforcement is provided. Figure 1-12 As shown, it includes a cylindrical shell, a skin cylinder 6, a short boss welding block 7, a long boss welding block 8 and an axial reinforcement rib. The skin cylinder 6 is welded with a short boss welding block 7, a long boss welding block 8 and a transverse reinforcement rib by laser welding or spot welding to form a cylindrical shell. The axial reinforcement rib is in the shape of a long strip to increase the bending resistance of the thin-walled cabin. The cross section is in a "convex" shape, and the "convex" bottom is welded to the skin. Figure 4-5 As shown, the cylindrical shell is divided into two half shells along a horizontal reference by a wire cutting process to form a split-flap lower shell 12 and a split-flap upper shell 13.

[0043] The axial reinforcement ribs include a first axial reinforcement rib 9, a second axial reinforcement rib 10 and a third axial reinforcement rib 11, and the axes of the first axial reinforcement rib 9, the second axial reinforcement rib 10 and the third axial reinforcement rib 11 are maintained on the same horizontal line; the first axial reinforcement rib 9 is located between the front column segment skin 1 and the annular reinforcement rib 2, the second axial reinforcement rib 10 is located between the annular reinforcement rib 2 and the long boss welding block 8, and the third axial reinforcement rib 11 is located between the long boss welding block 8 and the rear docking frame 5.

[0044] like Figure 6-8 As shown, a first lower connecting bar 14, a second lower connecting bar 15, and a third lower connecting bar 16 made of titanium alloy are welded on the left and right sides of the split lower shell 12 to form a split lower half cabin 20; connecting through holes are arranged on the three lower connecting bars, and support plate nuts are riveted on the connecting bars. Figures 9 to 11 As shown, the first upper connecting bar 17, the second upper connecting bar 18, and the third upper connecting bar 19 made of titanium alloy are welded on the left and right sides of the split upper shell 13 to form a split upper half cabin 21; and connecting countersunk holes are arranged on the upper connecting bars. The upper connecting bars and the lower connecting bars are in the shape of fish bones to reduce weight.

[0045] The split upper cabin 20 and split upper cabin 21 are radially connected, and the cabin is formed by rolling and bending a plate with a thinner wall thickness than the conventional cast cabin, which is conducive to the lightweight requirements of the cabin. The cabin wall adopts a 1mm titanium alloy skin. Before docking, the rubber sealing strip is bonded to the rectangular groove of the lower connecting strip of the split lower cabin 20 to achieve thermal sealing at the interface between the upper and lower cabins. The axially welded reinforcing rib skeleton is radially connected with the end frame and the equipment bracket 23 to form a radial skeleton, which facilitates the installation of large-size equipment while ensuring the rigidity and strength of the overall structure of the cabin section. Considering the heat protection requirements of the cabin, a low-density flexible silicone rubber-based heat-resistant coating can be sprayed on the outer surface of the cabin to achieve thermal protection of the equipment in the cabin. The outer surface of the cabin is designed as a countersunk hole, and the fixing screws can be installed under the condition of a thin-walled cabin without occupying the external space of the cabin. At the same time, a self-locking nut or a self-locking wire screw sleeve is installed on the equipment installation interface or the equipment bracket 23 to achieve an anti-loosening design for the connection between the equipment and the cabin.

[0046] like Figure 2As shown, the skin cylinder 6 is an integral cylindrical structure, including a front column segment skin 1, annular stiffeners 2, a rear column segment skin 3, a front docking frame 4 and a rear docking frame 5. The front end of the front column segment skin 1 is welded with the front docking frame 4, the rear end of the front column segment skin 1 is welded with the rear column segment skin 3, the rear end of the rear column segment skin 3 is welded with the rear docking frame 5, and the connection between the front column segment skin 1 and the rear column segment skin 3 is welded with annular stiffeners 2. The annular stiffeners 2, the front docking frame 4 and the rear docking frame 5 serve as the radial dimension skeleton of the shell, and are made of the same titanium alloy material as the skin, and have good weldability. The skin cylinder is assembled into a whole by welding. In order to ensure the processing accuracy of the installation interface on the cabin, all the installation interfaces need to be processed in place in the cylinder state.

[0047] like Figure 3 As shown, the cylindrical shell is formed by welding 4 short boss welding blocks 7, 6 long boss welding blocks 8, 2 first axial reinforcing ribs 9, 2 second axial reinforcing ribs 10, and 2 third axial reinforcing ribs 11 made of titanium alloy on the skin cylinder 6. The positions of the short boss welding blocks 7 and the long boss welding blocks 8 match the positions of the connection holes on the equipment bracket 23. Countersunk through holes are processed on the front docking frame 4 and the rear docking frame 5 in the cylindrical shell. The short boss welding blocks 7 and the long boss welding blocks 8 are respectively matched with countersunk through holes with the rear column section skin 3. The axial reinforcing ribs serve as the axial skeleton of the cabin, which improves the axial stiffness and tensile and compressive properties of the thin-walled slender cabin, and at the same time ensures the axial stability of the cabin. After the cylindrical shell is formed, the installation interface on the cabin is locally strengthened by locally welding the boss welding blocks, without the need to thicken the cabin over a large area, thereby providing cabin lightweight efficiency.

[0048] like Fig.12 As shown, the split-flap lightweight skin reinforced cabin structure includes: a split-flap lower cabin 20, a split-flap upper cabin 21, a front frame 22, an equipment bracket 23, and a rear frame 24. The split-flap lower cabin 20 is 1mm titanium alloy wall thickness, and is fixedly connected to the front frame 22 and the rear frame 24 by 24 screws; the front frame 22 is adaptively connected to the front docking frame 4, and the rear frame 24 is adaptively connected to the rear docking frame 5. The equipment bracket 23 is used to install the required equipment in the cabin, and is fixedly connected to the split-flap lower cabin 20 by 12 screws. The equipment bracket 23 can strengthen the connection strength and rigidity of the split-flap lower cabin 20 and the split-flap upper cabin 21, and the equipment can be installed on the bracket. After the equipment in the cabin is installed, the split-flap upper cabin 21 is aligned with the split-flap lower cabin 20, and then radial cabin docking is performed, and the 24 screws at the left and right joints are tightened to form the cabin structure after the cabin is closed.

[0049] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0050] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A cabin structure with large slenderness ratio and light-weight skin reinforcement, characterized in that: include: A skin cylinder (6), a short boss welding block (7), a long boss welding block (8) and an axial reinforcing rib, wherein the short boss welding block (7), the long boss welding block (8) and the transverse reinforcing rib are welded on the skin cylinder (6) to form a cylindrical shell, wherein the cylindrical shell is cut along a horizontal reference line to form a split-type lower shell (12) and a split-type upper shell (13), and the split-type lower shell (12) and the split-type upper shell (13) are connected by a connecting strip; The skin cylinder (6) comprises a front column segment skin (1), an annular stiffener (2), a rear column segment skin (3), a front docking frame (4) and a rear docking frame (5); the front end of the front column segment skin (1) is welded with the front docking frame (4); the rear end of the front column segment skin (1) is welded with the rear column segment skin (3); the rear end of the rear column segment skin (3) is welded with the rear docking frame (5); and the annular stiffener (2) is welded at the connection between the front column segment skin (1) and the rear column segment skin (3).

2. The cabin structure with large slenderness ratio and light-weight skin reinforcement according to claim 1 is characterized in that: The axial reinforcing rib is in the shape of an elongated strip, and the cross section of the axial reinforcing rib is in the shape of a "convex" character, and the convex-shaped bottom of the axial reinforcing rib is welded to the skin cylinder (6).

3. The cabin structure with large slenderness ratio and light-weight skin reinforcement according to claim 2 is characterized in that: The axial reinforcing ribs include a first axial reinforcing rib (9), a second axial reinforcing rib (10) and a third axial reinforcing rib (11), and the axes of the first axial reinforcing rib (9), the second axial reinforcing rib (10) and the third axial reinforcing rib (11) are maintained on the same horizontal line; The first axial reinforcing rib (9) is located between the front column segment skin (1) and the annular reinforcing rib (2), the second axial reinforcing rib (10) is located between the annular reinforcing rib (2) and the long boss welding block (8), and the third axial reinforcing rib (11) is located between the long boss welding block (8) and the rear docking frame (5).

4. The cabin structure with large slenderness ratio and light-weight skin reinforcement according to claim 1 is characterized in that: The front docking frame (4) and the rear docking frame (5) in the cylindrical shell are both machined with countersunk through holes, and the short boss welding block (7) and the long boss welding block (8) are respectively matched with countersunk through holes in the rear column section skin (3).

5. The cabin structure with large slenderness ratio and light-weight skin reinforcement according to claim 1 is characterized in that: The connecting strip is made of titanium alloy and is in a fishbone shape; The connecting strip comprises an upper connecting strip and a lower connecting strip, the lower connecting strip is welded on the split lower shell (12), a connecting through hole is arranged on the lower connecting strip, and a riveted support plate nut is screwed on the connecting through hole to form a split lower cabin (20); the upper connecting strip is welded on the split upper shell (13), and a connecting countersunk hole is arranged on the upper connecting strip to form a split upper cabin (21).

6. The cabin structure with large slenderness ratio split-type lightweight skin reinforcement according to claim 5 is characterized in that: The lower connecting strip is provided with a rectangular groove, and a silicone rubber sealing strip is bonded in the rectangular groove.

7. The cabin structure with large slenderness ratio split-type lightweight skin reinforcement according to claim 5 is characterized in that: An equipment bracket (23) is screwed onto the inner wall of the split lower cabin (20), and the equipment bracket (23) is ring-shaped; A self-locking nut or a self-locking wire screw sleeve is installed on the equipment installation interface on the cylindrical shell or the equipment bracket (23) to achieve an anti-loosening design for the connection between the equipment and the cabin.

8. The cabin structure with large slenderness ratio split-type lightweight skin reinforcement according to claim 1 is characterized in that: The two ends of the split lower cabin body (20) are respectively screwed with a front end frame (22) and a rear end frame (24); the front end frame (22) is adaptably connected to the front docking frame (4), and the rear end frame (24) is adaptably connected to the rear docking frame (5).

9. The cabin structure with large slenderness ratio split-type lightweight skin reinforcement according to claim 5 is characterized in that: The split-flap lower cabin body (20) and the split-flap upper cabin body (21) are screwed together to form a cabin body, and a low-density flexible silicone rubber-based heat-resistant coating is sprayed on the outer surface of the cabin body; A countersunk hole is provided on the outer surface of the cabin, and the countersunk hole is adapted to be installed with a fixing screw.

10. The cabin structure with large slenderness ratio split-type lightweight skin reinforcement according to claim 5, characterized in that: An antenna installation interface is provided at the connection between the split-flap lower cabin body (20) and the split-flap upper cabin body (21), and an antenna structure passes through the antenna installation interface.

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