A method for quickly installing a cabin bottom layer

Abstract

The application discloses a kind of engine room bottom layer quick loading method, in turn through dividing section, building section, dividing engine room unit and building engine room unit, transport section and engine room unit, total group section, in the engine room bottom layer total section total group bulk parts, hoist part engine room unit to engine room bottom layer total section, load engine room bottom layer total section, again hoist engine room unit to engine room bottom layer total section, hoist side total section and transverse bulkhead section.The application avoids the interference between hoist side total section total group and engine room unit on engine room bottom layer total section, shortens gantry unhooking time and dock period.The application divides bulk parts into multiple connected bulk sections, and engine room unit requiring butt joint is built using the same mold, which improves shipbuilding precision.

Description

Technical Field

[0001] This invention relates to the field of shipbuilding technology, and in particular to a method for rapid assembly of the engine room floor. Background Technology

[0002] As a core resource in shipyards, the rational utilization of gantry cranes and the reduction of hook-up time are currently research topics being studied by various shipyards. The engine room bottom level, being the area with the densest arrangement of outfitting components inside a ship, not only has a large number of pipes but also a dense concentration of equipment and various platforms. These outfitting components need to be placed in the engine room before the side sections are installed. To reduce the installation time of outfitting components, some are generally made into units and installed as a whole before the side sections are hoisted. During the hoisting process, interference often occurs between the structure on the side sections and the outfitting components on the engine room bottom level. To solve this problem, it is necessary to temporarily remove the outfitting components or raise the height of the engine room bottom level section above the outfitting component unit platform. Temporarily removing outfitting components will result in a longer hook-up time for the shipbuilding gantry crane and rework of the outfitting components, affecting the dock cycle; raising the height of the engine room bottom level section will increase the difficulty of precision control of the engine room bottom level section. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this application provides a method for rapid assembly of the engine room bottom layer, thereby solving the technical problems of long gantry crane unhooking time or difficulty in precision control of engine room bottom layer segments in existing technologies.

[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0005] A method for rapid mounting of components in the lower deck of an aircraft includes the following steps:

[0006] S1, the engine room bottom section is divided into multiple engine room sections, the side section is divided into multiple side sections, the part that interferes with the outfitting of the engine room bottom section is defined as a bulk component, the bulk component is divided into multiple connected bulk sections, and a transverse bulkhead section is provided at the upper front of the engine room bottom section.

[0007] S2 involves the construction of the engine room sections, transverse bulkhead sections, side sections, and bulk sections divided by S1.

[0008] S3, according to the principle of the same system and the same unit, divide the outfitting components on the bottom section of the cabin into multiple cabin units, and construct the cabin units;

[0009] S4, transporting painted and constructed engine room sections, transverse bulkhead sections, side sections, bulk sections and engine room units;

[0010] S5, the engine room sections are assembled into the engine room bottom section and the side sections are assembled into the side section respectively;

[0011] S6, assembles the pre-built bulk sections into bulk components on the bottom section of the engine room;

[0012] S7, which lifts the cabin unit without interference with the lifting bracket onto the bottom section of the cabin for installation;

[0013] S8, equipped with the lower section of the engine compartment;

[0014] S9, hoisting the cabin unit that interferes with the lifting bracket to the bottom section of the cabin;

[0015] S10, hoisting the side sections and transverse bulkhead sections to complete the installation of the engine room bottom layer.

[0016] In one embodiment, in S1, the bottom section of the cabin includes a first intermediate section, a first side section, a second side section, a second intermediate section, a third side section, and a fourth side section. The front end of the first intermediate section is connected to the rear end of the second intermediate section. The first and second side sections are symmetrically distributed on both sides of the first intermediate section, and the third and fourth side sections are symmetrically distributed on both sides of the second intermediate section. The front end of the first side section is connected to the rear end of the third side section, and the front end of the second side section is connected to the rear end of the fourth side section. The transverse bulkhead section is located at the upper front of the second intermediate section.

[0017] In one embodiment, in S1, the side section includes a first side segment, a second side segment, a third side segment, and a fourth side segment. The first and second side segments are symmetrically distributed on both sides of the first intermediate segment of the engine room. The lower end of the first side segment is connected to the upper surface of the first side segment of the engine room, and the lower end of the second side segment is connected to the upper surface of the second side segment of the engine room. The third and fourth side segments are symmetrically distributed on both sides of the second intermediate segment of the engine room. The lower end of the third side segment is connected to the upper surface of the third side segment of the engine room, and the lower end of the fourth side segment is connected to the upper surface of the fourth side segment of the engine room. The front end of the first side segment is connected to the rear end of the third side segment, and the front end of the second side segment is connected to the rear end of the fourth side segment.

[0018] In one embodiment, the bulk components are distributed within the side bulkhead section and the transverse bulkhead section, and multiple bulk sections are connected sequentially. The bulk components include a first bulk section, a second bulk section, a third bulk section, a fourth bulk section, a fifth bulk section, a sixth bulk section, a seventh bulk section, an eighth bulk section, a ninth bulk section, a tenth bulk section, an eleventh bulk section, and a twelfth bulk section. The first and third bulk sections are located within the first side bulkhead section, the second and fourth bulk sections are located within the second side bulkhead section, and the fifth bulk section... The sixth, seventh, and eighth bulk sections are located within the third side section; the ninth, tenth, and eleventh bulk sections are located within the fourth side section; and the twelfth bulk section is located within the transverse bulkhead section. The first, fifth, eighth, twelfth, eleventh, ninth, and second bulk sections are connected end to end. The third bulk section is assembled from outer plating and is connected to the first bulk section in the beam direction; the fourth bulk section is assembled from outer plating and is connected to the second bulk section in the beam direction.

[0019] In one embodiment, the joint between the bulk section and the side section is located above the bottom platform of the engine room.

[0020] In one embodiment, in S2, a transverse reinforcement is temporarily fixed inside the side section. The transverse reinforcement is set along the beam direction, and both ends of the transverse reinforcement are connected to the longitudinal bulkhead inside the side section. The middle part of the transverse reinforcement is connected to the inner rib of the side section.

[0021] In one implementation, the cabin units that need to be docked in S3 are constructed using the same mold.

[0022] In one implementation, the cabin segment described in S4 employs normal transport.

[0023] In one implementation, the lower section of the engine room is mounted using two gantry cranes in the S8, with the trolleys on the gantry cranes arranged in a row.

[0024] In one implementation, the transverse bulkhead sections are hoisted first in S10, followed by the main side sections.

[0025] Compared with the prior art, this application has at least the following beneficial effects:

[0026] This invention divides the engine room bottom section into multiple engine room segments, the side section into multiple side segments, and the bulk components into multiple interconnected bulk sections. The outfitting components on the engine room bottom section are divided into multiple engine room units. The constructed bulk sections are assembled into bulk components on the engine room bottom section. The engine room units are then hoisted onto the engine room bottom section for installation. Finally, the side section is hoisted onto the engine room bottom section. In other words, during the assembly process, interfering parts are first installed on the engine room bottom section, and then the engine room units are installed on the engine room bottom section. This avoids interference between the hoisted side section and the engine room units on the engine room bottom section during the hoisting of the side section, shortening the gantry unhooking time and docking cycle. This invention divides the bulk components into multiple interconnected bulk sections and uses a single-piece construction method for the engine room units that need to be docked, improving the precision of shipbuilding. Attached Figure Description

[0027] Figure 1 This is a three-dimensional schematic diagram of the completed engine room bottom section, transverse bulkhead section and side section in the embodiments of this application;

[0028] Figure 2 This is a three-dimensional schematic diagram of the cabin bottom section and the transverse bulkhead sections in the embodiments of this application;

[0029] Figure 3 yes Figure 1 The left view;

[0030] Figure 4 This is a left view of the laterally reinforced side section in this embodiment of the application;

[0031] Figure 5 This is a diagram of the segmented transport layout of the lower deck of the engine room in this application embodiment;

[0032] Figure 6 yes Figure 5 Sectional view of AA in the middle;

[0033] Figure 7 This is a layout diagram of the bottom compartment unit in an embodiment of this application;

[0034] Figure 8 This is a schematic diagram of the bulk fragment structure in an embodiment of this application;

[0035] Figure 9 This is a schematic diagram of the hoisting of the bottom section of the engine room in an embodiment of this application.

[0036] Reference numerals: 1. Engine room bottom section; 2. Side section; 3. First intermediate section of engine room; 4. First side section of engine room; 5. Second side section of engine room; 6. Second intermediate section of engine room; 7. Third side section of engine room; 8. Fourth side section of engine room; 9. First side section; 10. Second side section; 11. Third side section; 12. Fourth side section; 13. Transverse bulkhead section; 14. Transverse reinforcement; 15. First engine room unit; 16. Second engine room unit; 17. Third engine room unit; 18. Fourth engine room unit; 19. Fifth engine room unit; 20. Sixth engine room unit; 21. Seventh engine room unit; 22. First bulk section; 23. Second bulk section; 24. Third bulk section; 25. Fourth bulk section; 26. Fifth bulk section; 27. Sixth bulk section; 28. Seventh bulk section; 29. ​​Eighth bulk section; 30. Ninth bulk section; 31. Tenth bulk section; 32. Eleventh bulk section; 33. Twelfth bulk section; 34. Transport gantry; 35. Transport reinforcement; 36. Transport dunnage. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0038] The terminology used in this disclosure is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The singular forms “a,” “the,” and “the” as used in this disclosure and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any and all possible combinations of one or more of the associated listed items.

[0039] It should be understood that although the terms first, second, third, etc., may be used in this disclosure to describe various information, such information should not be limited to these terms and should not be construed as indicating or implying relative importance. These terms are used only to distinguish information of the same type from one another. For example, without departing from the scope of this disclosure, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if" as used herein may be interpreted as "when," "when," or "in response to determination."

[0040] In the description of this invention, unless otherwise specified and limited, it should be noted that the terms "installation", "connection" and "linking" should be interpreted broadly. For example, they can refer to mechanical connection or internal connection between two components. They can be direct connection or indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms according to the specific circumstances.

[0041] To better understand the technical solution of the present invention, the present invention will be described in detail below with reference to the accompanying drawings.

[0042] This embodiment provides a method for rapid loading into the lower part of the aircraft cabin, specifically including the following steps:

[0043] S1, the engine room bottom section 1 is divided into multiple engine room sections, the side section 2 is divided into multiple side sections, the part that interferes with the outfitting of the engine room bottom section 1 is defined as a bulk component, the bulk component is divided into multiple connected bulk sections, and a transverse bulkhead section 13 is provided at the upper front of the engine room bottom section 1.

[0044] Taking into account the size of the construction site, the load capacity of the transportation equipment, and the assembly precision, such as Figure 1-3 As shown, in this embodiment, the bottom section 1 of the cabin includes a first intermediate section 3, a first side section 4, a second side section 5, a second intermediate section 6, a third side section 7, and a fourth side section 8. The front end of the first intermediate section 3 is connected to the rear end of the second intermediate section 6. The first side section 4 and the second side section 5 are symmetrically distributed on both sides of the first intermediate section 3. The third side section 7 and the fourth side section 8 are symmetrically distributed on both sides of the second intermediate section 6. The front end of the first side section 4 is connected to the rear end of the third side section 7. The front end of the second side section 5 is connected to the rear end of the fourth side section 8. The transverse bulkhead section 13 is located at the upper front of the second intermediate section 6.

[0045] The side section 2 includes a first side section 9, a second side section 10, a third side section 11, and a fourth side section 12. The first side section 9 and the second side section 10 are symmetrically distributed on both sides of the first intermediate section 3 of the engine room. The lower end of the first side section 9 is connected to the upper surface of the first side section 4 of the engine room. The lower end of the second side section 10 is connected to the upper surface of the second side section 5 of the engine room. The third side section 11 and the fourth side section 12 are symmetrically distributed on both sides of the second intermediate section 6 of the engine room. The lower end of the third side section 11 is connected to the upper surface of the third side section 7 of the engine room. The lower end of the fourth side section 12 is connected to the upper surface of the fourth side section 8 of the engine room. The front end of the first side section 9 is connected to the rear end of the third side section 11. The front end of the second side section 10 is connected to the rear end of the fourth side section 12.

[0046] Bulk components are distributed within the side bulkhead section 2 and the transverse bulkhead section 13, and multiple bulk sections are connected sequentially, such as... Figure 8 As shown, in this embodiment, the bulk component includes a first bulk section 22, a second bulk section 23, a third bulk section 24, a fourth bulk section 25, a fifth bulk section 26, a sixth bulk section 27, a seventh bulk section 28, an eighth bulk section 29, a ninth bulk section 30, a tenth bulk section 31, an eleventh bulk section 32, and a twelfth bulk section 33. The first bulk section 22 and the third bulk section 24 are disposed within the first side section 9, the second bulk section 23 and the fourth bulk section 25 are disposed within the second side section 10, the fifth bulk section 26, the sixth bulk section 27, the seventh bulk section 28, and the eighth bulk section 29 are disposed within the third side section 11, the ninth bulk section 30, the tenth bulk section 31, and the eleventh bulk section 32 are disposed within the fourth side section 12, and the twelfth bulk section 33 is disposed within the transverse bulkhead section 13. The first bulk section 22, the fifth bulk section 26, the eighth bulk section 29, the twelfth bulk section 33, the eleventh bulk section 32, the ninth bulk section 30, and the second bulk section 23 are connected end to end. The third bulk section 24 is an outer plate assembly and is connected to the first bulk section 22 in the beam direction; the fourth bulk section 25 is an outer plate assembly and is connected to the second bulk section 23 in the beam direction.

[0047] The joint between the bulk section and the side section 2 is located above the bottom platform of the engine room, which facilitates welding when the chord section and the bulk section are joined. In this embodiment, the joint between the bulk section and the side section 2 is located 100mm above the bottom platform of the engine room.

[0048] S2 involves constructing the engine room section, transverse bulkhead section 13, side sections, and bulk sections divided by S1.

[0049] In this embodiment, a transverse reinforcement 14 is temporarily fixed inside the side section. The transverse reinforcement 14 is arranged along the beam direction, with both ends connected to the longitudinal bulkheads inside the side section, and the middle of the transverse reinforcement 14 connected to the inner rib plate of the side section. By setting the transverse reinforcement 14, the width of the side section is ensured during final assembly. The transverse reinforcement 14 is an I-beam channel steel.

[0050] S3, according to the principle of the same system and the same unit, divide the outfitting components on the bottom section 1 of the engine room into multiple engine room units, and construct the engine room units.

[0051] The principle of "one system, one unit" means that related outfitting components within the same system are grouped into one unit, facilitating the assembly of these components. In this embodiment, the cabin units that need to be docked are constructed using the same mold to reduce docking deviations during cabin unit assembly and improve assembly efficiency. For example... Figure 7As shown, the outfitting components on the bottom section 1 of the engine room are divided into seven engine room units: the first engine room unit 15, the second engine room unit 16, the third engine room unit 17, the fourth engine room unit 18, the fifth engine room unit 19, the sixth engine room unit 20, and the seventh engine room unit 21. Among them, the first engine room unit 15 and the second engine room unit 16 are the units that need to be docked. The first engine room unit 15 and the second engine room unit 16 are located on the second intermediate section 6 of the engine room.

[0052] S4, transporting the painted and constructed engine room sections, transverse bulkhead sections 13, side sections, bulk sections, and engine room units.

[0053] In this embodiment, the cabin sections are transported using a normal transport method, thereby avoiding the need to flip the cabin sections again when assembling the bottom section 1 of the cabin assembly. For example... Figure 5 , 6 As shown, the first section 4 on the side of the cabin is placed on the transport gantry 34 during transport. To prevent the first section 4 on the side of the cabin from sliding during transport, transport pads 36 are provided at the contact position between the first section 4 on the side of the cabin and the transport gantry 34. To prevent the first section 4 on the side of the cabin from overturning during transport, a number of vertically placed transport reinforcements 35 are provided between the first section 4 on the side of the cabin and the transport gantry 34. One end of the transport reinforcement 35 abuts against the lower surface of the first section 4 on the side of the cabin, and the other end abuts against the transport gantry 34.

[0054] S5, the engine room sections are assembled into engine room bottom section 1 and the side sections are assembled into side section 2 respectively.

[0055] In this embodiment, the six engine room sections are assembled into the engine room bottom section 1, and the four side sections are assembled into the side section 2.

[0056] S6, assemble the constructed bulk sections into bulk components on the bottom section 1 of the engine room.

[0057] To improve the assembly accuracy of bulk components and avoid embedded mounting of bulk sections, the bulk sections are assembled sequentially according to their connection order.

[0058] S7, the cabin unit that does not interfere with the lifting bracket is hoisted onto the bottom section 1 of the cabin for installation.

[0059] S8, equipped with the lower section of the cabin 1.

[0060] like Figure 9 As shown, this embodiment uses two gantry cranes to lift and mount the bottom section of the engine room, and the trolleys on the gantry cranes need to be arranged in a row.

[0061] S9, hoisting the cabin unit that interferes with the lifting bracket to the bottom section 1 of the cabin.

[0062] Step S7 improves the integrity of the underlying section 1 of the engine room and reduces the docking time. In this embodiment, the engine room units that interfere with the lifting brackets are the first engine room unit 15 and the second engine room unit 16.

[0063] S10, hoisting the side section 2 and transverse bulkhead section 13 to complete the installation of the engine room bottom layer.

[0064] In this embodiment, the transverse bulkhead section 13 is hoisted first, and then the side section 2 is hoisted to avoid embedding the loose sections and affecting the mounting accuracy.

[0065] The bulk components are located at the bottom of the engine room unit. Through the cooperation of S6-S10, interference between the hoisting of the side section and the engine room unit on the bottom section of the engine room is avoided.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the invention or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solutions of the present invention, and all such modifications and substitutions should be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. A method for rapid mounting of components on the lower deck of an aircraft, characterized in that, Includes the following steps: S1, the engine room bottom section is divided into multiple engine room sections, the side section is divided into multiple side sections, the part that interferes with the outfitting of the engine room bottom section is defined as a bulk component, the bulk component is divided into multiple connected bulk sections, and a transverse bulkhead section is provided at the upper front of the engine room bottom section. S2 involves the construction of the engine room sections, transverse bulkhead sections, side sections, and bulk sections divided by S1. S3, according to the principle of the same system and the same unit, divide the outfitting components on the bottom section of the cabin into multiple cabin units, and construct the cabin units; S4, transporting painted and constructed engine room sections, transverse bulkhead sections, side sections, bulk sections and engine room units; S5, the engine room sections are assembled into the engine room bottom section and the side sections are assembled into the side section respectively; S6, assembles the pre-built bulk sections into bulk components on the bottom section of the engine room; S7, which lifts the cabin unit without interference with the lifting bracket onto the bottom section of the cabin for installation; S8, equipped with the lower section of the engine compartment; S9, hoisting the cabin unit that interferes with the lifting bracket to the bottom section of the cabin; S10, hoisting the side sections and transverse bulkhead sections to complete the installation of the engine room bottom layer.

2. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, In S1, the lower section of the engine room includes a first intermediate section, a first side section, a second side section, a second intermediate section, a third side section, and a fourth side section. The front end of the first intermediate section is connected to the rear end of the second intermediate section. The first and second side sections are symmetrically distributed on both sides of the first intermediate section, and the third and fourth side sections are symmetrically distributed on both sides of the second intermediate section. The front end of the first side section is connected to the rear end of the third side section, and the front end of the second side section is connected to the rear end of the fourth side section. The transverse bulkhead section is located at the upper front of the second intermediate section.

3. The rapid loading method for the lower deck of the aircraft according to claim 2, characterized in that, In S1, the side section includes a first side segment, a second side segment, a third side segment, and a fourth side segment. The first and second side segments are symmetrically distributed on both sides of the first intermediate segment of the engine room. The lower end of the first side segment is connected to the upper surface of the first side segment of the engine room, and the lower end of the second side segment is connected to the upper surface of the second side segment of the engine room. The third and fourth side segments are symmetrically distributed on both sides of the second intermediate segment of the engine room. The lower end of the third side segment is connected to the upper surface of the third side segment of the engine room, and the lower end of the fourth side segment is connected to the upper surface of the fourth side segment of the engine room. The front end of the first side segment is connected to the rear end of the third side segment, and the front end of the second side segment is connected to the rear end of the fourth side segment.

4. The rapid loading method for the lower deck of the aircraft according to claim 2, characterized in that, The bulk components are distributed within the side bulkhead sections and transverse bulkhead sections, and multiple bulk sections are connected sequentially. The bulk components include a first bulk section, a second bulk section, a third bulk section, a fourth bulk section, a fifth bulk section, a sixth bulk section, a seventh bulk section, an eighth bulk section, a ninth bulk section, a tenth bulk section, an eleventh bulk section, and a twelfth bulk section. The first and third bulk sections are located within the first side bulkhead section, the second and fourth bulk sections are located within the second side bulkhead section, and the fifth and sixth bulk sections... Section 1, Section 7, and Section 8 are located within the third side section; Section 9, Section 10, and Section 11 are located within the fourth side section; Section 12 is located within the transverse bulkhead section; Sections 1, 5, 8, 12, 11, 9, and 2 are connected end to end; Section 3 is assembled from outer plating and is connected to Section 1 in the beam direction; Section 4 is assembled from outer plating and is connected to Section 2 in the beam direction.

5. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, The joint between the bulk section and the side section is located above the bottom platform of the engine room.

6. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, In S2, the interior of the side section is temporarily fixed with transverse reinforcement. The transverse reinforcement is set along the beam direction. Both ends of the transverse reinforcement are connected to the longitudinal bulkheads inside the side section, and the middle of the transverse reinforcement is connected to the inner rib of the side section.

7. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, In S3, the cabin units that need to be docked are constructed using the same mold.

8. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, The cabin sections described in S4 employ normal transport.

9. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, In the S8, two gantry cranes are used to lift and mount the bottom section of the engine room, and the trolleys on the gantry cranes need to be arranged in a row.

10. The rapid loading method for the lower deck of the aircraft according to claim 1, characterized in that, In S10, the transverse bulkhead sections are hoisted first, followed by the main side sections.

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