Helicopter mooring seat design method

Abstract

The invention relates to the technical field of ships, in particular to a helicopter mooring seat design method which comprises the following steps: S1, analyzing mechanical properties of materials of a conventional mooring seat structure to obtain replaceable new materials; s2, optimizing the structure of the mooring seat, designing a ball disc into a hollow column model, thickening a panel model to a set thickness, forming four open holes in the panel model at intervals, enabling the middle part of the panel model to be cross-shaped, and assembling the panel model and the hollow column model to form a mooring seat model; s3, checking the strength of the mooring seat model, and optimizing the mooring seat model; s4, a hollow column and a panel are manufactured through the optimized mooring seat model, the panel is welded to the hollow column, and a mooring seat body is formed at the position, located at an opening of the hollow column, of the panel; and S5, carrying out a fracture test and a tension test on the mooring seat body. According to the invention, the manufacturing difficulty can be reduced, the manufacturing cost can be reduced, and the requirement of equipment on a ship is met.

Description

Technical Field

[0001] The present invention relates to the technical field of ships, and in particular to a design method for a helicopter mooring seat. Background Art

[0002] A test vessel is equipped with a mooring system for securing helicopters. The design, manufacture, and installation of a mooring seat, a key component of a commonly used mooring system, must consider the influence of a variety of complex factors, including the ship's roll, wind and wave impact, and the aircraft's own weight and inertia. Currently, the main type of mooring seat used in China is the male cross type, consisting of a mooring seat body and a cover. The mooring seat body includes a ball disc with a panel welded to the opening. The ball disc of the mooring seat body is a bowl-shaped structure, which requires high processing requirements, mold production, high force requirements, and product inspection testing. The unit price of the mooring seat product is relatively high, and the procurement cycle is also long.

[0003] With the increasing deployment of helicopters on ships, the need for extensive mooring bays is increasing. However, the procurement of these bays cannot meet the planned and cost requirements for the planned mooring bays. For example, a test vessel with four bays required approximately 300 mooring bays. Conventional procurement procedures would significantly impact the construction of the hull structure. Furthermore, the mooring bays are constructed from 907A or 921A high-strength steel, a specialty steel plate that is difficult to procure and expensive, making them unsuitable for mass production.

[0004] Therefore, a helicopter mooring seat design method is needed to solve the above problems. Summary of the Invention

[0005] The object of the present invention is to provide a design method for a helicopter mooring seat, which can reduce the manufacturing difficulty and cost and meet the needs of equipment on ships.

[0006] To achieve this object, the present invention adopts the following technical solutions:

[0007] The design method of a helicopter mooring seat comprises the following steps:

[0008] S1. Analyze the mechanical properties of conventional mooring seat structures to obtain new materials that can be replaced;

[0009] S2. Optimize the mooring seat structure by designing the ball plate into a hollow column model, thicken the panel model to a set thickness, and provide four openings on the panel model at intervals so that the middle portion of the panel model is cross-shaped. Assemble the panel model and the hollow column model to form a mooring seat model.

[0010] S3. Performing strength check on the mooring seat model and optimizing the mooring seat model;

[0011] S4. Using the optimized mooring seat model, manufacture a hollow column and a panel, weld the panel to the hollow column, and position it at the opening of the hollow column to form a mooring seat body;

[0012] S5. Perform a breaking test and a tensile test on the mooring seat body.

[0013] In some embodiments, in step S1, the mechanical properties of the material include material yield properties, tensile properties, and impact resistance.

[0014] In some embodiments, in step S2, the corners of the four openings of the panel model are all designed with rounded chamfers.

[0015] In some embodiments, in step S3, set tensile loads are applied to the cross-shaped structure of the panel model at three different angles to obtain a maximum force value, and the maximum force value is compared with the standard allowable value to determine whether the design requirements are met.

[0016] In some embodiments, in step S4, the hollow column includes a cylinder and a bottom plate, the bottom plate is welded to an end of the cylinder away from the panel, and the bottom plate is located in the cylinder, and the lower end surface of the bottom plate is flush with the end surface of the cylinder.

[0017] In some embodiments, a first welding groove is opened at the edge of the lower end surface of the bottom plate, and welding is performed along the circumference of the bottom plate at the first welding groove of the bottom plate and at the intersection line of the upper end surface of the bottom plate and the cylinder.

[0018] In some embodiments, in step S4, a second welding groove is opened at the outer edge of the opening of the hollow column, and the hollow column is welded to the panel at the second welding groove along the circumference of the hollow column.

[0019] In some embodiments, in step S5, the breaking test is performed by applying a set breaking load to the cross-shaped structure of the panel and continuing for a set time, and the tensile test is performed by applying a set tensile load to the cross-shaped structure of the panel and continuing for a set time.

[0020] In some embodiments, the method further includes step S6 of welding the mooring seat body to the deck of the hull for load testing.

[0021] In some embodiments, in step S6, it is necessary to first weld a docking plate to the outer peripheral surface of the panel of the mooring seat body, and the docking plate is welded to the deck.

[0022] Beneficial effects of the present invention:

[0023] The present invention provides a method for designing a helicopter mooring seat. The method analyzes the mechanical properties of conventional mooring seat materials to identify new materials that can be replaced. The mooring seat structure is optimized, a ball plate is designed as a hollow column model, and a panel model is thickened to a set thickness. Four openings are provided in the panel model at intervals, forming a cross-shaped center. The panel model and the hollow column model are assembled to form a mooring seat model. The mooring seat model is strength-checked and optimized. The optimized mooring seat model is used to manufacture a hollow column and panel. The panel is welded to the hollow column and positioned at the opening of the hollow column to form the mooring seat body. The mooring seat body is then subjected to breaking and tensile tests. By replacing the original ball plate with a new material with similar mechanical properties and modeling based on the mechanical properties of the new material, the original ball plate structure is optimized and designed as a hollow column model. The panel model is thickened and assembled to form the mooring seat model. The use of the hollow column model reduces the difficulty of subsequent manufacturing, and the thickened panel model improves the strength of the subsequent panel. By performing strength checks on the mooring base model, it can be further optimized to ensure that subsequent mooring bases meet requirements. Once the mooring base is manufactured, breaking and tensile tests are performed to verify its structural strength. This approach reduces manufacturing complexity and costs, ensuring it meets shipboard equipment requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in describing the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without any creative work.

[0025] Figure 1 It is a flow chart of a method for designing a helicopter tie-down seat according to the present invention;

[0026] Figure 2 It is a partial cross-sectional view of a mooring seat body in a method for designing a helicopter mooring seat according to the present invention;

[0027] Figure 3 The utility model is a top view of a mooring seat body in a design method of a helicopter mooring seat of the present invention.

[0028] In the picture:

[0029] 1. Mooring seat body; 11. Cylinder; 12. Bottom plate; 13. Panel; 131. Opening; 2. Docking plate. DETAILED DESCRIPTION

[0030] Before any embodiments of the present application are explained in detail, it is to be understood that the application is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the foregoing drawings.

[0031] In this application, the terms "comprises," "includes," "has," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not preclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0032] In this application, the terms "connect," "combine," "couple," and "install" may refer to direct connection, combination, coupling, or installation, or indirect connection, combination, coupling, or installation. For example, a direct connection refers to two parts or components being connected together without an intermediary, and an indirect connection refers to two parts or components being connected to at least one intermediary, with the two parts or components being connected via the intermediary. Furthermore, "connect" and "couple" are not limited to physical or mechanical connections or couplings and may include electrical connections or couplings.

[0033] In this application, it will be understood by those skilled in the art that the function performed by an assembly can be performed by one assembly, multiple assemblies, one part, or multiple parts. Similarly, the function performed by a part can also be performed by one part, one assembly, or a combination of multiple parts.

[0034] In the present application, the terms "upper", "lower", "left", "right", "front", "back" and other directional words are described based on the orientation and positional relationship shown in the accompanying drawings, and should not be understood as limiting the embodiments of the present application. In addition, in the context, it is also necessary to understand that when it is mentioned that an element is connected to another element "upper" or "lower", it can not only be directly connected to the other element "upper" or "lower", but also be indirectly connected to the other element "upper" or "lower" through an intermediate element. It should also be understood that directional words such as upper side, lower side, left side, right side, front side, back side, etc. not only represent the positive orientation, but can also be understood as the lateral orientation. For example, below can include directly below, lower left, lower right, lower front and lower back, etc.

[0035] In the process of designing and manufacturing mooring seats, in order to reduce the manufacturing difficulty and cost, and meet the needs of equipment on ships, such as Figure 1-Figure 3 As shown, the present invention provides a method for designing a helicopter tie-down seat. The method for designing a helicopter tie-down seat comprises the following steps:

[0036] S1. Analyze the mechanical properties of conventional mooring seat structures to obtain new materials that can be replaced;

[0037] S2. Optimize the mooring seat structure by designing the ball plate into a hollow column model, thicken the panel model to a set thickness, and provide four openings 131 on the panel model at intervals, so that the middle portion of the panel model is cross-shaped. Assemble the panel model and the hollow column model to form a mooring seat model.

[0038] S3. Perform strength check on the mooring seat model and optimize the mooring seat model;

[0039] S4. Using the optimized mooring seat model, a hollow column and a panel 13 are manufactured. The panel 13 is welded to the hollow column and positioned at the opening of the hollow column to form the mooring seat body 1.

[0040] S5. Perform a breaking test and a tensile test on the mooring seat body 1.

[0041] By replacing the original ball-disc structure with a new material with similar mechanical properties and modeling based on the mechanical properties of the new material, the original ball-disc structure is optimized and designed as a hollow column model. The panel model is then thickened and assembled to form a mooring seat model. The use of a hollow column model reduces the difficulty of subsequent manufacturing. By thickening the panel model, the strength of the subsequently manufactured panel 13 can be improved. By performing a strength check on the mooring seat model, the mooring seat model can be further optimized to ensure that the subsequently manufactured mooring seat meets the requirements. After the mooring seat body 1 is manufactured, a breaking test and a tensile test are performed to verify the structural strength of the mooring seat body 1. The above method can reduce the difficulty of manufacturing and reduce the manufacturing cost, meeting the needs of ship equipment.

[0042] In some embodiments, in step S1, the material mechanical properties include yield strength, tensile strength, and impact resistance. By analyzing the yield strength, tensile strength, and impact resistance, a comprehensive reflection of the material's performance can be achieved. In this embodiment, the prior art uses 907A steel. DH36 steel is similar to 907A in terms of yield strength, tensile strength, and impact resistance. Therefore, DH36 steel can be selected as the material for the load-bearing components of the mooring seat. This eliminates the need for specialized 907A steel for design and construction.

[0043] In some embodiments, in step S2, the corners of the four openings 131 of the panel model are all designed with rounded chamfers. This design can avoid stress concentration at the corners and improve the mechanical properties of the panel model.

[0044] In some embodiments, in step S3, a set tensile load is applied to the cross-shaped structure of the panel model at three different angles to obtain the maximum force value, and compared with the standard allowable value to determine whether the design requirements are met. In this embodiment, the angle between the force direction of the mooring seat model and the plane is not less than 35°, the tensile force is not less than 137.2kN, and the breaking load is not less than 210kN. The calculated load is a tensile force of 210kN loaded at the cross center position of the panel model, and the tensile working conditions of 35°, 45° and 90° are used as a check. The equivalent stress cloud map and shear stress cloud map under each working condition are obtained through finite element calculation and analysis. The maximum force calculated values ​​of the stress cloud map and the shear stress cloud map are extracted, and compared with the standard allowable value to obtain the calculated stress results under each working condition. By comparing with the standard allowable value to determine whether the design requirements are met, if it does not meet the requirements, the mooring seat model is thickened to increase the strength.

[0045] In some embodiments, in step S4, the hollow column includes a cylinder 11 and a bottom plate 12. The bottom plate 12 is welded to the end of the cylinder 11 away from the panel 13. The bottom plate 12 is located in the cylinder 11, and the lower end surface of the bottom plate 12 is flush with the end surface of the cylinder 11. By manufacturing the mooring seat body 1 in this manner, the bottom plate 12 can be prevented from occupying additional space, thereby facilitating subsequent installation on the deck of the hull.

[0046] In some embodiments, a first welding groove is formed at the edge of the lower end surface of the bottom plate 12, and welding is performed along the circumference of the bottom plate 12 at the first welding groove of the bottom plate 12 and at the intersection of the upper end surface of the bottom plate 12 and the cylinder 11. This welding method can ensure a stable connection between the bottom plate 12 and the cylinder 11.

[0047] In some embodiments, in step S4, a second welding groove is formed at the outer edge of the opening of the hollow column, and the hollow column is welded to the panel 13 at the second welding groove along the circumference of the hollow column. In this way, a stable connection between the hollow column and the panel 13 can be ensured.

[0048] In some embodiments, in step S5, a breaking load is applied to the cross-shaped structure of panel 13 for a set duration to perform a breaking test, and a tensile load is applied to the cross-shaped structure of panel 13 for a set duration to perform a tensile test. The test is performed using an electronic universal testing machine. After applying a rated load to the mooring base body 1 via the testing machine's hook and maintaining the load for 1 minute, no damage is observed to the mooring base body 1. The rated load of the testing machine is selected based on the mooring base's breaking load of 210 kN. A tensile test of 137.2 kN is performed on the mooring base body 1 using the same test procedure, and no deformation is observed to the mooring base body 1.

[0049] In some embodiments, the system further includes step S6, welding the mooring base body 1 to the ship's deck for a load test. To verify the correctness and completeness of the new mooring base body 1, five mooring base bodies 1 were randomly selected from each parking area for a load test. The mooring base bodies 1 were connected using mooring rigging simulating interface components, and a vertical tensile force T (171.5 kN) was applied to the mooring base bodies 1 for a duration of no less than 30 seconds. After the tensile load test, the appearance of the mooring base body 1 and the welds of the docking structure were observed, and all inspection results were satisfactory.

[0050] In some embodiments, in step S6, it is necessary to first weld the outer circumference of the panel 13 of the mooring seat body 1 to the docking plate 2, and then weld the docking plate 2 to the deck. By providing the docking plate 2, a stable connection between the mooring seat body 1 and the deck can be ensured, reducing the difficulty of welding.

[0051] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A method for designing a helicopter mooring seat, characterized in that: The steps include: S1. Analyze the mechanical properties of conventional mooring seat structures to obtain new materials that can be replaced; S2, optimizing the mooring seat structure, designing the ball plate into a hollow column model, and thickening the panel model to a set thickness, providing four openings (131) on the panel model at intervals, so that the middle of the panel model is a cross shape, and assembling the panel model and the hollow column model to form a mooring seat model; S3. Performing strength check on the mooring seat model and optimizing the mooring seat model; S4, manufacturing a hollow column and a panel (13) using the optimized mooring seat model, welding the panel (13) to the hollow column and locating it at the opening of the hollow column to form a mooring seat body (1); S5. Perform a breaking test and a tensile test on the mooring seat body (1).

2. The helicopter mooring seat design method according to claim 1, characterized in that: In step S1, the mechanical properties of the material include the yield strength, tensile strength and impact resistance of the material.

3. The helicopter mooring seat design method according to claim 1, characterized in that: In the step S2, the corners of the four openings (131) of the panel model are all designed with rounded chamfers.

4. The helicopter mooring seat design method according to claim 1, characterized in that: In step S3, set tensile loads are applied to the cross-shaped structure of the panel model at three different angles to obtain the maximum force value, and the maximum force value is compared with the standard allowable value to determine whether the design requirements are met.

5. The helicopter mooring seat design method according to claim 1, characterized in that: In step S4, the hollow column comprises a cylinder (11) and a bottom plate (12), the bottom plate (12) is welded to an end of the cylinder (11) away from the panel (13), and the bottom plate (12) is located in the cylinder (11), and the lower end surface of the bottom plate (12) is flush with the end surface of the cylinder (11).

6. The helicopter mooring seat design method according to claim 5, characterized in that: A first welding groove is provided at the edge of the lower end surface of the bottom plate (12), and welding is performed along the circumference of the bottom plate (12) at the intersection of the first welding groove of the bottom plate (12) and the upper end surface of the bottom plate (12) and the cylinder (11).

7. The helicopter mooring seat design method according to claim 1, characterized in that: In the step S4, a second welding groove is opened at the outer edge of the opening of the hollow column, and the hollow column is welded to the panel (13) at the second welding groove along the circumference of the hollow column.

8. The helicopter mooring seat design method according to claim 1, characterized in that: In the step S5, the breaking test is performed by applying a set breaking load to the cross-shaped structure of the panel (13) and continuing for a set time, and the tensile test is performed by applying a set tensile load to the cross-shaped structure of the panel (13) and continuing for a set time.

9. The helicopter mooring seat design method according to claim 1, characterized in that: The method further comprises step S6, welding the mooring seat body (1) to the deck of the ship to perform a load test.

10. The helicopter mooring seat design method according to claim 9, characterized in that: In the step S6, it is necessary to first weld a docking plate (2) to the outer peripheral surface of the panel (13) of the mooring seat body (1), and the docking plate (2) is welded to the deck.

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