KR101334326B1 - Heli-deck for a ship - Google Patents

Abstract

A marine helicopter landing pad is disclosed. Marine helicopter landing place according to an embodiment of the present invention, the planar (plank) forming a place where the helicopter is taken off and landing; And a hot air guide module disposed adjacent to the flank and guiding the hot air discharged from the cabin in which the hot air of a relatively higher temperature than the outside air is used toward the flank.

Description

Helicopter Landing Site {Heli-deck for a ship}

The present invention relates to a helicopter landing pad, and more particularly, to a marine helicopter landing pad having an improved freezing prevention structure.

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.

Helicopter landings are often installed at the top level of the living quarter building where workers live. If the area where the ship is sailing or the work area is very cold or snowy, It is necessary to prevent freezing of the plank, the upper deck of the helipad, for safe takeoff and landing of the helicopter.

For example, if a ship drilling oil, such as a drillship, is anchored for a certain period of time in the cold region near the North Pole or the South Pole, the snow will accumulate on the surface of the flank and it will be easy to freeze. Since it is not possible to guarantee takeoff and landing, it is desirable to have an anti-icing means in the helipad.

A heating tracing cable is an anti-icing means for helicopter landings that are currently or are being considered. In other words, the heating tracing cable is connected to the flank of the helicopter landing area as if it is a boiler pipe to supply electricity to melt snow or ice accumulated on the flank by the heating of the heating tracing cable.

However, such a conventional method is not easy to construct the heating tracing cable, and if a disconnection occurs at any one part, the operation is not easy because the whole operation is not easy.

In addition, the heating tracing cable has a structure that melts snow or ice by heat transfer after being in direct contact with the flank, which requires a substantial amount of power. Therefore, there is a problem in that the power consumption is unnecessarily increased, in particular, in the case of a ship having a limited power generation facility (power generation) it may be difficult to provide the effect of freezing prevention by encountering the problem of power generation capacity constraints.

Therefore, it is necessary to develop a structure to prevent freezing of the helicopter landing pad, but to consider new alternatives or complementary measures in terms of economic feasibility.

Therefore, the technical problem to be achieved by the present invention is that the construction is simple, and thus the construction is more convenient than the conventional construction, and the maintenance is also easy. It is possible to significantly lower power consumption, thereby providing a marine helicopter landing site that can be sufficiently applied to a vessel with limited power generation facilities.

According to an aspect of the invention, the helicopter (plank) to form a place to take off and landing; And a warm air guide module disposed adjacent to the flank and guiding the warm air discharged from the cabin in which warm air of a relatively higher temperature is used than the outside air to the flank.

The cabin may be any one or more of a living quarter in which a worker lives, a living quarter equipped with a heating air conditioning system, an engine room in which an internal combustion engine is provided, and a boiler room.

The hot air guide module may include: a main air duct for guiding one end of the hot air guide to guide the hot air discharged from the cabin; And a plurality of hot air spraying branch ducts branched from the other end of the hot air guide main duct toward the flank to inject the hot air toward the flank.

The warm air guide module may further include a warm air connection duct connecting the warm air guide main duct and the plurality of hot air injection branch ducts.

The warm air connection duct may be formed such that the radius of the warm air connection duct gradually decreases in a direction away from the main wind duct main duct.

A blower fan for guiding the warm air may be further provided in at least one of the warm air guide main duct, the plurality of hot air spray branch ducts, and the warm air connection duct.

The hot air guide may further include a hot air heater provided in at least one of the main air duct, the plurality of hot air injection branch ducts, and the hot air connection duct to heat the hot air passing through the duct.

A temperature sensing unit provided on the flank to sense a temperature of the flank; And a controller for controlling the operation of the warm air heater based on the temperature of the flank detected by the temperature sensing unit.

It may further include a damper provided in the hot air guide main duct to selectively control the flow of the warm air discharged from the cabin.

The damper may be a louver-type damper or the disc-shaped rotary damper based on a rotation operation, and may further include a damper driver connected to the damper to drive the damper.

The flank, the upper frame to which the helicopter takes off and landing; A lower frame spaced apart from the upper frame; And a reinforcing connection part configured to connect the upper and lower frames while reinforcing each other between the upper and lower frames, and the warm air connection duct may be supported by an upper surface of the lower frame.

Embodiments of the present invention, because the structure is simple, not only convenient construction than the conventional, but also easy to maintain, in particular, it is possible to utilize the warm air discharged from the cabin in which the warm air of a relatively high temperature than the outside air is used to reduce the power consumption. It can be significantly lowered and, therefore, adequately applied to ships with limited power generation.

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.
FIG. 2 is a schematic side view structural view of the marine helicopter landing area shown in FIG. 1.
3 is an enlarged view of the main part of Fig.
4 is a modified example of the damper shown in FIG.
5 is a side structural view of a marine helicopter landing area 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 site 100 is a place provided for takeoff and landing of a helicopter, not shown, and may be installed at a top level of a living quarter building where workers live. Of course, the position of the helicopter landing pad 100 may be changed as far as shown.

The ship of FIG. 1 in which the helipad 100 is provided may be a special ship (drillship, FPSO, War ship, etc.), but considering that floating offshore structures are within the scope of the ship, helicopters may also be used for other types of ships other than the special ship. Landing area 100 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 and 3.

FIG. 2 is a schematic side view structural view of the marine helicopter landing area shown in FIG. 1, FIG. 3 is an enlarged view of main parts of FIG. 2, and FIG. 4 is a modification of the damper shown in FIG. 2.

As shown in these figures, the marine helicopter landing pad 100 of the present embodiment has a flank 110, which forms a place where a helicopter, not shown, takes off and lands, and is disposed adjacent to the flank 110 and relatively relatively to outside air. It includes a hot air guide module 130 for guiding the hot air discharged from the cabin in which the high temperature hot air is used toward the flank 110.

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, it is preferable to make the flank 110 into a unit flank (not shown) having a plurality of unit sizes, and to combine one of the flanks 110 by assembling the adjacent unit flanks.

At this time, the coupling between adjacent unit flanks may be applied to the uneven coupling method. That is, by forming a protrusion on one of the unit flanks, and forming a protrusion groove into which the protrusion is inserted into the other, the protrusion and the protrusion groove may be coupled to the unevenness so that one flank may be manufactured.

The flank 110 manufactured as described above may form an octagonal structure in planar projection as shown in FIG. 1. 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.

As shown in detail in FIG. 3, the flank 110 is disposed between the upper frame 110a, the lower frame 110b spaced apart from the upper frame 110a, and the upper and lower frames 110a and 110b. In the upper and lower frames (110a, 110b) includes a reinforcement connecting portion (110c) for connecting while reinforcing each other.

The upper frame 110a is a part where the helicopter is taken off and landed while being substantially in contact with the support. The same applies to the lower frame 110b, but in particular the upper frame 110a should form a flat surface. Only then can the helicopter take off and land stably.

The lower frame 110b is a portion disposed to be parallel to the upper frame 110a and may form the same area as the upper frame 110a.

The reinforcement connection part 110c is a part for connecting the upper and lower frames 110a and 110b while reinforcing each other. As shown, it may have an X-shaped pattern. Of course, unlike the drawing it may be formed a vertical pattern in the vertical direction.

On the other hand, the warm air guide module 130 is disposed between the flank 110 and the cabin in which the warm air of a relatively higher temperature than the outside air is used. In the case of the present embodiment, a cabin in which warm air of a relatively higher temperature is used than the outside air is described as a living quarter equipped with a heating and air conditioning system 120.

Assuming that the vessel of the present embodiment is a drill ship for drilling crude oil, for example, the drill ship is anchored for a certain period of time in the cold region adjacent to the North Pole or the South Pole, and the worker's living quarters are heated. Heating and air conditioning system for 120 may be equipped.

Here, the heating air conditioning system 120 may be an electronic product including an air conditioner, a hot air generator, or the like, or may be a heating boiler.

Whatever type is applied, if the heating air conditioning system 120 is provided in the residence, the interior space in the residence may be warmed by hot air, that is, warm air.

The warm air is circulated in the room to be discharged to the outside of the inlet, the discharged air is generally maintained to remain warm than the outside air in the present embodiment, such a warm exhaust air, that is, the warm air to the hot air guide module 130 Guide to the flank 110 through) to help prevent freezing of the flank 110.

Although the temperature of the warm air guided by the warm air guide module 130 is not very high, it may help to prevent the flank 110 from freezing if such warm air is continuously and also concentrated toward the flank 110 for a long time.

Since the structure of the present embodiment is simple, the construction is not only convenient than the conventional construction, but also easy to maintain, and can significantly reduce the power consumption compared with the conventional, and thus can be sufficiently applied to a vessel having limited power generation facilities. There will be.

The warm air guide module 130 is provided to guide the warm air in the residential area toward the flank 110, the main air duct 140 for hot air guide, a plurality of hot air spraying branch duct 150, and the hot air connection duct 160 ).

The hot air guide main duct 140, the plurality of hot air injection branch duct 150, and the hot air connection duct 160 may be all made of stainless steel material that is rigid but not easily corroded by sea water.

The main air duct for hot air guide 140 is connected to the one end portion to guide the hot air discharged from the residence. One end of the main wind duct 140 for hot air guide may be connected to a louver or the like in a residential area.

The blowing fan 145 may be provided inside the main air duct 140 for hot air. Due to the blowing fan 145 which may be applied as a cross flow fan, the warm air that is separated out of the residence can be guided along the main air duct 140 for warm air guide.

The hot air guide main duct 140 may be provided with a damper 146 to selectively control the flow of the warm air discharged from the inlet. In this embodiment, the damper 146 is applied as a louver type damper 146. The louver type damper 146 may be mechanical or electric.

The louver-type damper 146 may serve to shield the inner opening of the main air duct 140 for warm air guidance in seasons such as spring, summer, and fall that do not require freezing prevention.

For reference, unlike FIG. 3, the damper 146a may be a disk-shaped rotary damper 146a as shown in FIG. 4, and the damper driver 147 for driving the disk-shaped rotary damper 146a may be connected to the disk-shaped rotary damper 146a. Can be.

The damper driver 147 may include a drive shaft 147a connected to the disc-shaped rotary damper 146a and a motor 147b connected to the drive shaft 147a to rotate the drive shaft 147a in the forward and reverse directions. have. As a result, the disk-shaped rotary damper 146a may be opened or closed by opening the hot air guide main duct 140 while the motor 147b is rotated as a dotted line in a solid line or a solid line in a dotted line.

Of course, since the scope of the present invention does not need to be limited to this matter, in addition to the louver-type damper 146 or the disk-type rotary damper 146a, the disk type for opening and closing the opening of the main air duct 140 for hot air guide based on the sliding action. It may also be a sliding damper (not shown).

The plurality of hot air injection branch duct 150 is branched toward the flank 110 at the other end of the hot air guide main duct 140 serves to inject the warm air toward the flank 110.

If the number of branch duct 150 for hot air spraying is provided as much as possible, it may be more advantageous to provide warm air evenly to the entire region of the flank 110. Although not shown, a nozzle tip may be further connected to an end portion of the branch duct 150 for warm air injection as a means for increasing the spray strength of the warm air.

The hot air connection duct 160 serves to connect the hot air guide main duct 140 and the plurality of hot air injection branch duct 150.

In this case, the warm air connection duct 160 may be formed such that the radius of the warm air connection duct 160 gradually decreases along the direction away from the main air guide duct 140. This may be one design method for increasing the speed of air instead of decreasing the amount of air because the amount of air decreases away from the main air duct 140 for warm air guidance.

The warm air connection duct 160 may be supported on an upper surface of the lower frame 110b of the flank 110. As the warm air connection duct 160 is supported on the upper surface of the lower frame 110b, the warm air connection duct 160 does not sag.

By this configuration, when the louver-type damper 146 is opened and the operation of the blower fan 145 is turned on, the warm air warming the inside of the residence port is the hot air guide main duct 140 and the hot air connection duct 160. After flowing through the), it may be directed to the flank 110 through a plurality of hot air injection branch duct 150, by the continuous guide operation of the hot air hot air evenly sprays the warm air to the entire region of the flank 110 While being able to help prevent freezing of the flank 110.

In the case of manufacturing and using the helipad 100 as such a structure, the construction is simpler than the conventional construction because of the simple structure, and also easy to maintain, and in particular, it is possible to utilize the warm air used for heating of the residential area, power consumption Can be significantly lowered, and thus can be sufficiently applied to ships with limited power generation facilities.

On the other hand, while using the above structure, if the temperature of the outside air is too sharply lowered, the warm air directed toward the flank 110 may be further heated. This is illustrated in the examples below.

5 is a side structural view of a marine helicopter landing area according to a second embodiment of the present invention.

Referring to this drawing, in the present embodiment, the warm air guide main duct 140 is provided with a warm air heater 270 for heating the warm air passing through the warm air guide main duct 140. And the flank 110 is provided with a temperature sensor 271 for sensing the temperature of the flank 110.

When such a structure is provided, the controller 272 controls the operation of the warm air heater 270 based on the temperature of the flank 110 sensed by the temperature sensor 271.

The range of control includes all of adjusting the strength or strength of the warm air heater 270, including turning on / off operation of the warm air heater 270.

When the warm air heater 270, the temperature sensing unit 271 and the controller 272 is provided in this way, since the warm air discharged from the inlet side is further heated to increase its temperature, it is sent to the flank 110, and thus the flank It may be more effective in melting snow or frozen ice accumulated at (110).

However, in this case, the power consumption required for the operation of the warm air heater 270 is expected, but since the warm air heater 270 is temporarily operated only when the temperature of the flank 110 is lower than the preset temperature, power consumption is extremely low compared to the conventional art. It will be poor.

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 descriptions.

In the above-described embodiment, the hot air guide module guides the warm air from the residence port to the flank, but the hot air guide module is connected to the engine room or the boiler room to guide the hot air from the engine room or the boiler room to the flank. It can also provide the effects of this embodiment.

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: upper frame 110b: lower frame
110c: reinforcement connection 120: heating air conditioning system
130: hot air guide module 140: main duct for hot air guide
145: blower fan 146: damper
150: branch duct for hot air injection 160: hot air connection duct
270: warm air heater 271: temperature sensing unit
272: controller

Claims (11)

A flank forming a place where the helicopter takes off and lands; And
It is disposed adjacent to the flank, and includes a hot air guide module for guiding the hot air discharged from the cabin in which the hot air of a relatively higher temperature than the outside air is used toward the flank,
The warm air guide module,
A hot air guide main duct whose one end is connected to the cabin side to guide the warm air discharged from the cabin; And
And a plurality of hot air spraying branch ducts branched from the other end of the hot air guiding main duct toward the flank to inject the hot air toward the flank. The method of claim 1,
The cabin is a space in which a worker lives, a living quarter (living quarter) equipped with a heating and air conditioning system, an engine room in which an internal combustion engine is provided, and a boiler landing space, which is at least one of a boiler room. delete The method of claim 1,
The hot air guide module, the ship landing pad further comprises a hot air connection duct for connecting the hot air guide main duct and the plurality of hot air injection branch duct. 5. The method of claim 4,
The hot air connection duct is a marine helicopter landing pad is formed such that the radial size of the hot air connection duct gradually decreases along the direction away from the main air guide duct. 5. The method of claim 4,
At least one of the hot air guide main duct, the plurality of hot air injection branch duct and the hot air connection duct is a marine helicopter landing pad is further provided with a blowing fan for guiding the hot air. The method according to any one of claims 1, 4, 5 or 6,
And a hot air heater provided in at least one of the hot air guiding main duct, the plurality of hot air spraying branch ducts, and the hot air connecting duct to heat the hot air passing through the duct. The method of claim 7, wherein
A temperature sensing unit provided on the flank to sense a temperature of the flank; And
And a controller for controlling the operation of the warm air heater based on the temperature of the flank detected by the temperature sensing unit. The method according to any one of claims 1, 4, 5 or 6,
And a damper provided in the main wind duct main duct to selectively control the flow of the warm air discharged from the cabin. delete 7. The method according to any one of claims 4 to 6,
The flank,
An upper frame on which the helicopter takes off and lands;
A lower frame spaced apart from the upper frame; And
Reinforcing connecting portion for connecting while reinforcing the upper and lower frames mutually between the upper and lower frames,
The hot air connection duct is a marine landing pad that is supported on the upper surface of the lower frame.

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