KR101323789B1 - Heli-deck for a ship - Google Patents

Abstract

A marine helicopter landing pad is disclosed. Marine helicopter landing site according to an embodiment of the present invention, the upper frame and the lower frame spaced apart side by side with the upper frame, the helicopter is taken off and land, and the upper and lower frames between the upper and lower frames are connected to each other while reinforcing at least Plank having a reinforcing connection portion forming a triangular pattern of a triangular shape; And a flank support for supporting the flank apart from the deck of the hull.

Description

Helicopter Landing Site {Heli-deck for a ship}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a helicopter landing pad, and more particularly, to a helicopter landing pad for ships applied to a ship.

The marine helicopter landing site is a huge structure that is coupled to the upper area of the hull and forms the place where the helicopter takes off and lands. Commonly called a heli-deck, it is installed on special ships (drillships, FPSOs, war ships, etc.).

Such a helicopter landing site may be shaped according to the location of the installation, the shape of the ship, and the influence of the movement of the ship. Basically, the helicopters to be taken off and land are designed accordingly.

Meanwhile, the helipad may be installed on the ground such as a roof of a building, and in the case of the helipad installed on the ground, the helipad is applied to ships in a variety of external forces such as external force caused by waves or external force caused by wind. I receive a lot. Therefore, the helicopter landing pad must be structurally stable and excellent in strength.

In view of this, various types of helicopter landing sites using stainless steel, aluminum (Al), or composite materials have been developed and are being applied or being prepared for application.

On the other hand, aluminum is, as is widely known, has been favored by ship owners because of its high corrosion resistance and low specific gravity compared to conventional stainless steel materials.

As described above, aluminum has excellent characteristics in terms of materials, but when the helicopter landing pad is simply manufactured using aluminum, for example, when the aluminum plate is placed in a ladder shape or an X shape and welded, the helicopter landing pad is manufactured. The complexity of the structure may decrease productivity.

In particular, in this case, a large number of reinforcing structures are required, and thus a new alternative is required because the weight may be excessive, which may be a factor in inhibiting the volumetric capacity of the ship.

Therefore, the technical problem to be achieved by the present invention is to implement the structure simplification away from the conventional complex structure to improve productivity according to the reduction of working time, as well as to reduce the weight of the structure, structurally stable and strength surface Is to provide an excellent marine helicopter landing pad.

According to an aspect of the present invention, the helicopter is taken off and landed, the lower frame spaced apart parallel to the upper frame and the upper and lower frames between the upper and lower frames are connected to each other while reinforcing each other at least partially Plank having a reinforcing connection forming a triangular pattern of a triangular shape (plank); And a flank support for supporting the flanks with respect to the deck of the hull may be provided.

The reinforcing connection part may include a plurality of reinforcing frames regularly arranged spaced apart from each other along the lateral direction between the upper and lower frames.

The reinforcement frame may include a pair of first inclined frames each having an upper end connected to the upper frame and inclined symmetrically toward the opposite side such that the triangular pattern is formed therein; A load transfer frame formed along a direction of gravity at a point where the pair of first inclined frames abuts to transfer the load of the helicopter downward; And a pair of second inclined frames branched from the point where the load transfer frame ends and connected to the lower frame, respectively, and symmetrically inclined toward the opposite side so that the triangular pattern is formed therein.

The pair of first slanted frames and the pair of second slanted frames may be provided symmetrically with respect to the load transfer frame.

The first inclined frame and the second inclined frame may have an asymmetrical structure based on the load transfer frame.

The flanks may include a plurality of unit flanks, and the plurality of unit flanks may be contiguous with each other to form an octagonal structure in planar projection.

The flank support includes: a first support supported on the deck of the hull; And a second support disposed on the first support to connect the flank and the first support.

The first support may be provided by an H-beam made of stainless steel, and the second support may be provided by an I-beam made of stainless steel. The first support, the second support and the flank may be bolted to each other.

The apparatus may further include a joint pad disposed between the first support and the second support and coupled together by the bolt.

Embodiments of the present invention, by implementing the structure simplification away from the conventional complex structure can not only improve the productivity according to the reduction of working time, but also can be reduced in weight of the structure, not only structurally stable but also excellent effect in terms of strength To provide.

1 is a perspective view of a ship to which the helicopter landing site according to the first embodiment of the present invention is applied.
2 is a plan view of the ship's helicopter landing site.
3 is a sectional view taken along the line AA in Fig.
4 is a perspective view of a unit flank.
5 is a sectional view taken along the line BB in Fig.
6 is a partial cross-sectional structural view of a marine helicopter landing site according to a second embodiment of the present invention.

In order to fully understand the present invention, operational advantages of the present invention, and objects achieved by the practice of the present invention, reference should be made to the accompanying drawings and the accompanying drawings which illustrate preferred embodiments of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. Like reference symbols in the drawings denote like elements.

1 is a perspective view of a ship to which the helicopter landing site according to the first embodiment of the present invention is applied.

As shown in this figure, one side of the deck (2, deck) of the hull 1 is provided with a ship landing pad 100 for ships. The marine helicopter landing pad 100 is a place provided for takeoff and landing of a helicopter (not shown).

The vessel on which the helipad 100 is provided may be a special ship (drillship, FPSO, War ship, etc.), but considering that the floating offshore structure is included within the scope of the ship, the helipad (100) may also be used for other types of ships other than the special ship. ) May be applied.

For reference, the helipad 100 illustrated in the drawing of FIG. 1 is schematically illustrated for convenience, and the detailed structure of the helipad 100 will be described with reference to FIGS. 2 to 5 below.

FIG. 2 is a plan view of a helicopter landing pad for ships, FIG. 3 is a cross-sectional view taken along the line A-A of FIG. 2, FIG. 4 is a perspective view of the unit flank, and FIG. 5 is a cross-sectional view taken along the line B-B of FIG. 4.

Referring to these drawings, the helipad 100 according to the present embodiment supports the flank 110 spaced apart from the plank 110 on which the helicopter is taken off and lands, and the deck 2 of the hull 1 (see FIG. 1). To include flank support 160.

Since the flank 110 is a part where the helicopter is taken off and landed, its upper surface forms a flat surface.

Considering that the helicopter can be taken off and landed only when the upper surface of the flank 110 has a large area, the flank 110 is bulky, and thus it is practically difficult to be integrally manufactured at a time in a factory or the like.

Therefore, as shown in the present embodiment, the flank 110 is formed into a plurality of unit flanks 110a and 110b, and the unit flanks 110a and 110b are combined to form adjacent ones so that one flank 110 is completed. desirable.

At this time, the coupling between the adjacent unit flanks (110a, 110b) may be applied to the concave-convex coupling method as shown in FIG. That is, the projections P1 are formed in one of the unit flanks 110a and 110b, and the projections P1 are formed in the other one, and the projections P1 and the projection grooves P2 are uneven. By being combined, one flank 110 can be manufactured.

The flank 110 manufactured as described above may form an octagonal structure in planar projection as shown in FIG. 2. Of course, since the flank 110 does not necessarily have to form an octagonal structure, the scope of the present embodiment does not need to be limited to the shape of the drawings.

For reference, FIG. 3 illustrates the concave-convex structures of the projection P1 and the projection groove P2 only for the region of the upper frame 120 of the flank 110, but the same applies to the region of the lower frame 130. And the concave-convex coupling structure of the flank 110 is shown only in the enlarged portion in FIG. 3, the rest of the drawings are omitted for convenience.

As shown in detail in FIGS. 4 and 5, the flank 110 includes an upper frame 120, a lower frame 130 spaced apart from the upper frame 120, and upper and lower frames 120 and 130. It includes a reinforcing connector 140 for connecting the upper and lower frames 120 and 130 while reinforcing each other.

The upper frame 120 is a part where the helicopter is taken off and landed while being substantially in contact support. The same applies to the lower frame 130 but in particular the upper frame 120 should form a flat surface. Only then can the helicopter take off and land stably.

The lower frame 130 may be disposed to be parallel to the upper frame 120 and may form the same area as the upper frame 120. As shown in FIG. 4, the lower frame 130 has a through hole H through which the bolt B1 passes.

The through hole H may be formed in the lower frame 130 between the reinforcing frames 150, and the flank 110 may be formed by the bolt B1 through the through hole H and the second support of the flank support 160. And may be combined with 180.

The reinforcing connection part 140 is a part for connecting the upper and lower frames 120 and 130 while reinforcing each other to form a triangular pattern P having a triangular shape.

The reinforcing connection portion 140 has an approximately dumbbell type when viewed from the side as shown in FIGS. 3 to 5. The reinforcement connection 140 will be described in detail.

The reinforcing connector 140 includes a plurality of reinforcing frames 150 arranged regularly spaced apart from each other along the lateral direction between the upper and lower frames 120 and 130.

Taking the unit flank 110a shown in FIGS. 4 and 5 as an example, three reinforcement frames 150 are regularly arranged in the unit flank 110a to be spaced apart from each other along the lateral direction. Of course, this is only one embodiment, the number of the reinforcement frame 150 may be less or more than three.

The reinforcement frame 150 includes a pair of first inclined frames 151 connected to the upper frame 120, a pair of second inclined frames 152 connected to the lower frame 130, and a first And a load transfer frame 153 connecting the second inclined frames 151 and 152.

The pair of first inclined frames 151 are connected to the upper end of the upper frame 120 so that a triangular pattern P is formed therein, and are inclined symmetrically toward the opposite side. That is, referring to Figure 5, the pair of first inclined frame 151 serves to collect the load of the helicopter toward the load transfer frame 153.

The load transfer frame 153 is formed along the direction of gravity at the point where the pair of first inclined frames 151 abut to transfer the load of the helicopter downward, that is, toward the pair of second inclined frames 152. do. That is, the load transfer frame 153 has a straight structure when viewed from the side.

A pair of second inclined frame 152 is branched at the end of the load transfer frame 153, the lower end is connected to the lower frame 130, respectively, so that the triangular pattern (P) is formed inside the symmetrical toward the other side Is inclined.

The pair of second inclined frames 152 serves to branch the load of the helicopter, which is transmitted from the load transmission frame 153, back to the lower frame 130.

As a result, the pair of first inclined frames 151 has an inverted triangular shape, and the pair of second inclined frames 152 have a triangular shape, so that the first inclined frame 151 is based on the load transfer frame 153. The 151 and the second inclined frame 152 may be provided symmetrically with each other.

When the first inclined frame 151 and the second inclined frame 152 are provided symmetrically with each other as in this embodiment, the load provided from the upper frame 120 side may be provided to the same position of the lower frame 130 side. As a result, deformation of the flank 110 can be prevented. Therefore, by being able to use the flank 110 for a long time, maintenance costs can also be reduced.

Meanwhile, in the present embodiment, the inclination θ of the pair of first inclination frames 151 and the pair of second inclination frames 152 may be determined in a range of 30 degrees to 60 degrees, and the pair of first inclinations The inclination θ of the frame 151 and the pair of second inclined frames 152 may be 45 degrees.

When the inclination θ of the pair of first inclined frames 151 and the pair of second inclined frames 152 is 45 degrees, the triangular pattern P therein may be an isosceles triangle. The structure may be a structure that can transfer the load from the helicopter well below without deformation.

Indeed, as in the present embodiment, a straight load transfer is simply performed without fabricating a reinforcement frame 150 having a pair of first inclined frames 151, a pair of second inclined frames 152, and a load transfer frame 153. When the deformation amount analysis is performed by comparing the reinforcement frame (not shown) structure in which only a plurality of frames 153 are arranged with the reinforcement frame 150 of the present embodiment, the structure of the reinforcement frame 150 of the present embodiment is approximately 38%. It was confirmed that deformation | transformation generation can be suppressed within the range.

The flank 110 having such a structural feature, that is, the unit flank 110a shown in FIG. 4 may be manufactured by extrusion molding of aluminum (Al).

Extrusion molding is a molding method in which a raw material is supplied to an extruder, pushed out of a mold, and transformed into a continuum having a uniform cross section, and a specific shape can be continuously manufactured using aluminum materials such as thermoplastic resin and the present embodiment. It is a molding method.

By making the unit flank 110a shown in FIG. 4 by such extrusion, the continuous production and the rapid production are possible, thereby reducing the overall time or cost loss.

In other words, if the upper and lower frames 120 and 130 and the reinforcing connection portion 140 therebetween are formed at a time by extrusion of aluminum, a multilayer structure is formed around the reinforcing connection portion 140 and excellent in terms of structural or strength. Therefore, there is no need to use reinforcing aluminum or stainless steel as before.

In particular, when manufacturing the unit flank 110a by extrusion of aluminum, it is desirable to increase the size of the extrusion as much as possible, so that the structure can be simplified, resulting in high efficiency productivity.

Next, the flank supporter 160 serves to support the flank 110 with respect to the deck 2 of the hull 1. The height of the flank support 160 may be appropriately changed depending on the size of the vessel.

As shown in FIG. 3, the flank supporter 160 is disposed on the first supporter 170 supported by the deck 2 of the hull 1 and the upper part of the first supporter 170 and the flank 110. And a second support 180 connecting the first support 170.

The flank supporter 160 may be made of stainless steel, whereas the flank 110 is made of aluminum (Al). Although stainless steel is somewhat heavier than aluminum, it is known to be much stronger.

In the present embodiment, the first support 170 is provided by an H-beam made of stainless steel, and the second support 180 is provided by an I-beam made of stainless steel, and flanks are provided. 110, the second support 180 and the first support 170 are coupled to each other bolts B1 and B2.

As such, when the flange 110, the second support 180, and the first support 170 are coupled to the bolts B1 and B2, the welding work can be reduced accordingly, and the convenience of the work can be increased. It is easy to maintain because it is easy.

While the second support 180 provided with the I-beam is directly bolted to the flank 110, the first support 170 provided with the H-beam and the second support 180 are provided between the second support 180. The bolt B2 is engaged after the joint pad 190 is further interposed. When the bolt B2 is coupled after using the joint pad 190 as in the present embodiment, the bonding strength between the first support 170 and the second support 180 may be further increased to form a stable lower structure. Of course, this matter is one way for strength reinforcement may be omitted in the configuration.

In addition, in the present embodiment, the first support 170 is made of stainless steel H-beam, the second support 180 is made of stainless steel I-beam, but the scope of the present invention Since it is not limited, materials and shapes of the first and second supports 170 and 180 may be changed.

By this configuration, the unit flanks 110a and 110b are manufactured by extrusion molding of aluminum, and the unit flanks 110a and 110b are unevenly bonded to adjacent ones to form one flank 110, and the hull 1 The helicopter landing pad 100 may be manufactured by coupling bolts B2 and B1 while stacking the first support 170, the second support 180, and the flank 110 from the deck 2.

In the case of manufacturing and using the helicopter landing pad 100 as such a structure, it is possible to improve productivity according to the reduction of working time by implementing the structure simplification away from the conventional complicated structure.

In addition, it is possible to reduce the weight of the structure, it is structurally stable and can provide an excellent effect in terms of strength.

6 is a partial cross-sectional structural view of a marine helicopter landing site according to a second embodiment of the present invention.

In the above-described embodiment, the unit flank 110a in which the first inclined frames 151 and the second inclined frames 152 are provided symmetrically with respect to the load transfer frame 153 has been described.

However, as shown in FIG. 6, based on the load transfer frame 253, the first inclined frames 251 and the second inclined frames 252 are not symmetrical with each other, that is, the unit flank 210a having an asymmetric structure. ) May be applied.

That is, as shown in FIG. 6, the distance L1 between the first inclination frames 251 may be shorter than the distance L2 between the second inclination frames 252, and the distance L1 between the first inclination frames 251 is It may be longer than the distance L2 between the second inclined frames 252. Although the first inclined frames 251 and the second inclined frames 252 have a shape that is not symmetrical with each other as shown in the drawing, if their shapes have a triangular shape, the load from the helicopter is collected toward the load transfer frame 253 and then again. Since it can be stably dispersed toward the second inclined frame 252, structural stability can be achieved.

Therefore, the first inclined frame 251 and the second inclined frame 252 may have a shape that is not symmetrical with each other as in this embodiment.

Although the present embodiment has been described in detail with reference to the drawings, the scope of the present invention is not limited to the above-described drawings and description.

Although the description is omitted in the above embodiment, the load transfer frame may be made thicker than the first and second inclined frames. In other words, the load transfer frame serves to transfer the load from the first inclined frame toward the second inclined frame, so that when the load transfer frame is made thicker than the first and second inclined frames, the load is stable toward the second inclined frame. Can be advantageously delivered.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the invention. Accordingly, such modifications or variations are intended to fall within the scope of the appended claims.

1: hull 2: deck
100: helicopter landing zone 110: flank
110a, 110b: unit flank 120: upper frame
130: lower frame 140: reinforced connection
150: reinforcement frame 151: first inclined frame
152: second inclined frame 153: load transfer frame
160: flank support 170: first support
180: second support 190: joint pad

Claims (9)

An upper frame on which the helicopter is taken off and landed, a lower frame spaced apart from the upper frame, and the upper and lower frames are connected to each other while reinforcing the upper and lower frames, each of which forms a triangular pattern having a triangular shape. Flanks having reinforcing connections; And
A first support supported on the deck of the hull, and a second support disposed on the first support and connecting the flank to the first support, the deck being attached to the deck of the hull. A flank support for spaced apart support,
The reinforcing connecting portion includes a plurality of reinforcing frames arranged regularly spaced apart from each other along the lateral direction between the upper and lower frames,
The reinforcing frame
A pair of first inclined frames each having an upper end connected to the upper frame and inclined symmetrically toward the opposite side such that the triangular pattern is formed therein;
A load transfer frame formed along a direction of gravity at a point where the pair of first inclined frames abuts to transfer the load of the helicopter downward; And
And a pair of second inclined frames branched at the end of the load transfer frame and connected to the lower frame, respectively, and symmetrically inclined toward the opposite side so that the triangular pattern is formed therein.
The pair of first sloped frames and the pair of second sloped frames are provided symmetrically with respect to the load transfer frame.
The first support is provided by an H-beam of stainless steel (stainless steel),
The second support is provided by an I-beam of stainless steel,
And the first support, the second support, and the flank are bolted to each other. delete delete delete delete The method of claim 1,
The flank comprises a plurality of unit flanks,
The plurality of unit flanks are adjacent to each other concave-convex to form a octagonal structure when the plane projected helicopter landing pad for ships. delete delete The method of claim 1,
And a joint pad disposed between the first support and the second support and joined together by the bolt.

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