KR20230083872A - Airship of vertical wing shape - Google Patents

Abstract

The invention relates to an airship. According to an embodiment of the present invention, an airship comprises: a body having a flotation gas inside and one or more support frames; and one or more propellers. The body has a vertical wing shape with a streamlined cross-sectional shape that is left and right symmetrical.

Description

Airship of vertical wing shape}

The present invention relates to an airship, and more particularly, to an airship having a vertical wing shape having a streamlined cross section.

Airships consume less carbon energy because they use the buoyancy of lighter-than-air gases, but the airships have a very large volume and are greatly affected by the wind, and are slower than airplanes or helicopters, so they are not widely used in modern times.

In the middle latitudes such as Korea, the stratosphere starts at 10 to 13 km above the ground and extends to about 50 km above the ground. For the past 20 years, active research has been conducted to moor an airship at a point at this altitude for a long period of time and utilize it as a platform for Internet communication/relay or earth observation/monitoring. An airship that functions as a platform while hovering for a long time at a stratospheric altitude, which is much lower than the satellite orbit, while having a function similar to that of an artificial satellite, is simply referred to as a 'stratospheric airship'. In addition, the term 'stratosphere' simply means the stratosphere at an altitude of about 20 km below.

In the stratosphere, the pressure of the atmosphere is usually reduced to about 1/20 of that of the ground, and the density is also reduced to about 1/15. Therefore, in order for an airship to rise to the stratosphere, the volume of the bubble must be expanded by about 15 times compared to that on the ground.

In the stratosphere above the Korean Peninsula, westerly winds are mainly blowing, and wind speeds of 5 to 10 m/s on average and temporarily up to 35 m/s are known to occur in winter when the wind speed is strong. Therefore, in order to overcome this wind and stay at one point, it is necessary to design the airship in a shape that minimizes the aerodynamic drag caused by wind speed.

Stratospheric airships are greatly influenced by the wind even while they rise from the ground to the stratosphere. Especially when passing through the jet stream zone, you have to overcome the high wind speed. Therefore, it is advantageous for an airship to have an aerodynamic shape that can quickly reach the stratosphere while being less affected by wind, if possible, even during vertical movement in the troposphere as well as horizontal movement for apex flight in the stratosphere. Of course, even when descending to the ground, it is necessary to secure a shape and operation plan that can quickly and accurately move vertically to a desired point on the ground. That is, it is necessary to design the shape of the airship so as to have small resistance to the wind both in vertical and horizontal movement.

The appearance of airships known to have been promoted at home and abroad so far has a streamlined cylindrical shape similar to a traditional airship shape, as shown in FIG. 1, with an X-shaped or V-shaped tail end. However, until now, no case of an airship that has succeeded in long-term endurance in the stratosphere has been known not only in Korea but also abroad. Therefore, it is not known what shape the airship should be manufactured to be most advantageous for long-term apex endurance in the stratosphere and upward/descent movement in the troposphere.

Such prior art is technical information possessed by the inventor for derivation of the present invention or acquired during the derivation process of the present invention, and cannot necessarily be referred to as known art disclosed to the general public prior to filing the present invention.

Japanese Laid-Open Patent Publication JP 1994-199290 A

The present invention is an invention for solving the above problems, it is possible to provide an airship of a new shape considering the operating concept of the airship.

However, these problems are exemplary, and the problem to be solved by the present invention is not limited thereto.

An airship according to an embodiment of the present invention is an airship including a body having a buoyant gas and one or more support frames therein, and one or more propellers, wherein the body has a vertical wing shape having a streamlined shape with a left-right symmetrical cross-sectional shape. have

In the airship according to an embodiment of the present invention, the one or more propellers may include a front propeller disposed at the front end of the body to generate thrust and a rear propeller disposed at the rear of the body to change direction.

In the airship according to an embodiment of the present invention, the front propeller and the rear propeller may be disposed below the central axis in the height direction of the body.

In the airship according to an embodiment of the present invention, the front propellers may be disposed in pairs on both sides of the body.

In the airship according to an embodiment of the present invention, the front propeller and the rear propeller may rotate in a predetermined direction to generate upward or downward thrust.

In the airship according to an embodiment of the present invention, the one or more support frames are disposed between a plurality of horizontal support frames disposed along the inner surface of the body and the front and rear ends of the body, the plurality of horizontal support frames It may include a plurality of vertical support frames connecting the.

In the airship according to an embodiment of the present invention, the plurality of horizontal support frames may be elastically deformable in a horizontal direction according to a difference in internal and external pressure of the airship.

In the airship according to an embodiment of the present invention, in a state in which the internal air of the body is discharged, the plurality of horizontal support frames maintain a straight shape, and the one or more support frames are attached to the tip of the plurality of horizontal support frames. It may further include a streamlined front frame to be mounted.

In the airship according to an embodiment of the present invention, the one or more support frames may include a plurality of auxiliary support straps or perforated horizontal membranes disposed between the horizontal support frames in the thickness direction of the body.

The auxiliary support strap is connected not only to the horizontal support frame at the same height but also to the horizontal support frame at different heights to prevent the air bag from being twisted.

In the airship according to an embodiment of the present invention, it may further include a plurality of solar cell panels disposed on the side of the body.

In the airship according to an embodiment of the present invention, it is disposed inside the body and may further include an auxiliary air bag through which external air is introduced and discharged.

In the airship according to an embodiment of the present invention, disposed at the rear of the body, it may further include a control surface for controlling the attitude of the airship.

In the airship according to an embodiment of the present invention, the body has a cutout in which a lower portion of the rear end is cut, and the control surface may be rotatably connected to one side of the cutout.

In the airship according to an embodiment of the present invention, it is disposed as a payload of the airship, and may further include a lift gas tank for supplying lift gas into the body to control the lifting speed of the airship.

Other aspects, features, and advantages other than those described above will become clear from the detailed description, claims, and drawings for carrying out the invention below.

Airship according to an embodiment of the present invention, unlike conventional airships, by having a thin wing shape in the vertical direction, it is possible to rapidly ascend and descend to the stratosphere.

An airship according to an embodiment of the present invention can utilize the effect of a rapid elevation operation not only in the stratosphere but also in the troposphere.

1 shows a conventional airship.
2 to 4 show an airship according to an embodiment of the present invention.
5 shows a state in which the body expands.
6 shows a state in which the airship of the present invention descends.
7 to 9 show an operation of the airship ascending according to an embodiment of the present invention.
10 shows an airship according to another embodiment of the present invention.
11 shows an airship according to another embodiment of the present invention.
12 and 13 show an airship according to another embodiment of the present invention.
14 shows an airship according to another embodiment of the present invention.

Since the present invention can apply various transformations and have various embodiments, specific embodiments will be illustrated in the drawings and described in detail in the description of the invention. However, this is not intended to limit the present invention to specific embodiments, and should be understood to include all conversions, equivalents, or substitutes included in the spirit and scope of the present invention. In describing the present invention, even if shown in different embodiments, the same identification numbers are used for the same components.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings, and when describing with reference to the drawings, the same or corresponding components are assigned the same reference numerals, and overlapping descriptions thereof will be omitted. .

In the following embodiments, terms such as first and second are used for the purpose of distinguishing one component from another component without limiting meaning.

In the following examples, expressions in the singular number include plural expressions unless the context clearly dictates otherwise.

In the following embodiments, terms such as include or have mean that features or components described in the specification exist, and do not preclude the possibility that one or more other features or components may be added.

In the drawings, the size of components may be exaggerated or reduced for convenience of description. For example, since the size and thickness of each component shown in the drawings are arbitrarily shown for convenience of description, the present invention is not necessarily limited to the illustrated bar.

In the following embodiments, the x-axis, y-axis, and z-axis are not limited to the three axes of the Cartesian coordinate system, and may be interpreted in a broad sense including these. For example, the x-axis, y-axis, and z-axis may be orthogonal to each other, but may refer to different directions that are not orthogonal to each other.

When an embodiment is otherwise implementable, a specific process sequence may be performed differently from the described sequence. For example, two processes described in succession may be performed substantially simultaneously, or may be performed in an order reverse to the order described.

Terms used in this application are only used to describe specific embodiments, and are not intended to limit the present invention. In this application, the terms "include" or "have" are intended to designate that there is a feature, number, step, operation, component, part, or combination thereof described in the specification, but one or more other features It should be understood that the presence or addition of numbers, steps, operations, components, parts, or combinations thereof is not precluded.

1 shows a conventional airship 2. 2 to 4 show an airship 1 according to an embodiment of the present invention, FIG. 5 shows a state in which the body expands, and FIG. 6 shows a state in which the airship 1 of the present invention descends, 7 to 9 show an operation of the airship 1 ascending according to an embodiment of the present invention.

The airship 1 according to an embodiment of the present invention is an airship that moves in the stratosphere at a target altitude, for example, 10 km to 50 km above the ground by injecting a lift gas from the ground. More specifically, the airship 1 can move in the stratosphere at a height of 15 km to 25 km from the ground and, more specifically, 20 km from the ground.

2 to 6, the airship 1 according to an embodiment of the present invention may have a vertical wing shape. That is, as shown in FIG. 1, the conventional airship is a cylindrical airship 2 with a streamlined tip like a torpedo or bullet, whereas the airship 1 according to an embodiment of the present invention is a vertical airship having a streamlined cross section. It may have a wing shape. In addition, the airship 1 may have a streamlined shape with a symmetrical cross-sectional shape. In addition, the airship 1 may have a length in the first direction (eg, the x-axis direction) greater than a length in the second direction (eg, the y-axis direction). Through such a shape, the airship 1 can lower the drag coefficient compared to a conventional cylindrical airship.

In one embodiment, the airship 1 may include a body 10 having a buoyancy gas and one or more support frames 20 therein, and one or more propellers 30 .

As shown in FIGS. 2 to 4 , the body 10 may extend from a streamlined front end to a rear end. In addition, on the longitudinal section, for example, the YZ plane of FIG. 2, both edges may have a straight line shape. For reference, unless otherwise specified, hereinafter "longitudinal section" represents a cross section in the height direction when the airship (1) is viewed from the front, that is, a YZ plane, and "cross section" is the longitudinal direction when the airship (1) is viewed from the top. represents a cross section into, that is, the XY plane.

In one embodiment, the body 10 may have a symmetrical streamlined shape with respect to a first direction (eg, the X-axis direction of FIG. 2) extending from the front end to the rear end. For example, as shown in FIG. 3, when the airship 1 is viewed from the top, the body 10 is symmetric about the central axis AX1 in the longitudinal direction, and the tip may have a streamlined shape. In other words, the airship 1 according to an embodiment of the present invention may have a vertical wing shape. Here, the central axis AX1 may be located at the center in the height direction of the body 10 .

Through this configuration, the airship 1 according to an embodiment of the present invention has a single airfoil shape without having a tail section and a control surface, so that the drag coefficient can be lowered compared to the conventional airship 2 .

In one embodiment, the body 10 has an internal space, and air or floating gas may flow in and out. The type of the buoyancy gas is not particularly limited, and may include a gas having a lower density than air and high stability. For example, the lift gas may be hydrogen gas or helium gas.

In one embodiment, the body 10 may include a body portion 11 . The body portion 11 has a streamlined tip and may have a rectangular profile when viewed from the front and side. For example, as shown in FIG. 2, when viewed from the side, the front and rear ends of the main body 11 are spaced apart in a first direction (eg, the X-axis direction in FIG. 2) and are arranged in parallel to form a long side of a rectangle. can do. In addition, the upper and lower ends of the body portion 11 may be spaced apart in a third direction (eg, the Z-axis direction of FIG. 2) and disposed in parallel to form a rectangular short side.

In one embodiment, the height H of the body portion 11 may be greater than the length L of the body portion. Here, the height H represents the height in the third direction, that is, the Z-axis direction, and the length L represents the length in the first direction, that is, the X-axis direction.

The shape of the airship 1 has a vertical wing shape as a whole, and a specific shape is not particularly limited. For example, the airship 1 may have a rectangular, parallelepiped or trapezoidal or elliptical shape when viewed from the side. In addition, the cross section of the airship 1 does not necessarily have to have a certain shape or size, and may have a shape and size corresponding to the shape of the side of the airship 1. In addition, even when viewed from the front, the body portion 11 of the airship 1 may have a rectangular, parallelepiped, trapezoidal, or elliptical shape. Hereinafter, as an embodiment, a case in which the body portion 11 has a rectangular shape when viewed from the side will be mainly described, but this is an example for convenience of explanation, and the airship 1 or the body 10 or the body portion 11 ) is not necessarily limited to a specific shape.

As shown in FIG. 4, when the airship 1 is viewed from the front, the body portion 11 has a pair of long sides extending in the height direction, and a second direction perpendicular to the height direction (e.g., Y in FIG. 4). axial direction) may include a pair of short sides.

In one embodiment, the body portion 11 may appear as a rectangle on a longitudinal section. For example, both sides of the body portion 11 may have a straight line shape on a longitudinal section. In addition, the body portion 11 may include a pair of long sides extending in a height direction on a longitudinal section and a pair of short sides extending in a second direction perpendicular to the height direction.

In one embodiment, the body portion 11 may have a constant cross section in the height direction. For example, as shown in FIGS. 2 and 3 , the body portion 11 may have a constant cross section regardless of its position in the height direction. That is, the body portion 11 may have the same shape, for example, a shape in which airfoil shapes having a streamlined tip are stacked in the height direction.

Accordingly, the outer surface of the body portion 11 may have a region in which the curvature changes in the first direction and/or the second direction, and may have a constant curvature (infinite curvature because it is a straight line) in the third direction.

As the airship 1 rises, the upper part 13 of the airbag expands due to lower atmospheric pressure, and expands upward as shown in FIGS. 2 and 4 . Accordingly, when the airship 1 reaches the target altitude, the shape of the upper part 13 of the airbag may have a shape similar to that of the upper part of the streamlined cylindrical shape.

In one embodiment, the upper part 13 of the air bag may be made of an elastic material and may be thicker than other parts of the body 10, for example, the body part 11. Alternatively, the upper part 13 of the air bag may further include a reinforcing member (not shown). That is, the upper part 13 of the airbag is a part that receives a lot of the buoyant load of the airship 1 in the process of flying the airship 1, and may have a thick thickness or include the reinforcing member to support such a load. . The reinforcing member may be a thin film such as a tape disposed inside or outside the upper part 13 of the bag and connected to the support frame 20 to be described later. The reinforcing member may be connected to the horizontal support frame 21 and/or the vertical support frame 23 of the support frame 20 to distribute the load received during flight of the airship 1.

Like the upper part 13 of the bladder, the lower portion 15 of the bladder also expands convexly downward as the atmospheric pressure decreases as the airship 1 rises. Accordingly, as shown in FIGS. 2 and 4 , it may have a shape similar to the bottom of the streamlined cylindrical shape.

In one embodiment, like the upper part 13 of the bladder, the lower portion 15 of the bladder may have a thicker thickness than the body portion 11 or may have the reinforcing member.

In one embodiment, when the airship 1 reaches the target altitude, the sides of the bag, that is, the main body 11, the upper part 13 of the bag, and the lower part 15 of the bag are inflated. When the body 10 is viewed from the front in this state, as shown in FIG. 4, the edges of both sides of the main body 11 extend in the height direction, and the upper part 13 and the lower part 15 of the bag are respectively The upper and lower portions of both sides of the body portion 11 extend in an arc.

One or more support frames 20 may be disposed on one side of the body 10 to maintain the shape of the airship 1 . For example, as shown in FIG. 2 , the support frame 20 is disposed inside the body 10 to maintain a streamlined airfoil shape when the airship 1 reaches a target altitude.

In one embodiment, the support frame 20 may have elasticity. For example, the airship 1 is located on the ground, after the internal air is exhausted, and before the buoyancy gas is injected, the support frame 20 may maintain a folded state inside the body 10. Thereafter, the buoyancy gas is injected, and when the atmospheric pressure decreases as the airship 1 rises and reaches a target altitude, the body 10 expands while the support frame 20 unfolds to maintain a predetermined shape. That is, the plurality of support frames 20 may be elastically deformable according to a difference in internal and external pressure of the airship 1 .

In one embodiment, the support frame 20 may include a horizontal support frame 21 and a vertical support frame 23 .

A plurality of horizontal support frames 21 may be disposed along the inner surface of the body 10 . For example, as shown in FIG. 2 , the horizontal support frame 21 has a shape corresponding to the cross section of the body 10 and may be disposed inside the body portion 11 .

In one embodiment, the plurality of horizontal support frames 21 may be spaced apart from each other by a predetermined height in the height direction of the body 10 . For example, as shown in FIG. 2, a plurality of horizontal support frames 21 are arranged at equal intervals in the height direction, and when the airship 1 reaches a target altitude, as the body 10 expands, the plurality of horizontal supports While the frame 21 is unfolded, the shape of the body 10 may be maintained.

2, it is shown that five horizontal support frames 21 are disposed in the height direction, but the number is not particularly limited. Four or less or six or more horizontal support frames 21 may be disposed.

The vertical support frame 23 is disposed between the front and rear ends of the body 10 and may be disposed to connect a plurality of horizontal support frames 21 . For example, as shown in Figure 2, the vertical support frame 23 is disposed inside the body 10, a plurality of disposed in the longitudinal direction of the body 10, each of a plurality of horizontal support frame 21 and can be connected

In one embodiment, the vertical support frame 23 may be rectangular. 2 and 4, the vertical support frame 23 has a pair of long sides extending in the longitudinal direction of the body 10 and a pair of short sides extending between the pair of long sides when viewed from the front. It may be a rectangle containing A pair of long sides may be arranged to connect a plurality of horizontal support frames 21 , and a pair of short sides may be arranged to extend between the horizontal support frames 21 .

2 shows that two vertical support frames 23 are disposed, but the number is not particularly limited. For example, one or more vertical support frames 23 may be disposed.

In one embodiment, the support frame 20 may further include an auxiliary support frame 25 . As shown in FIG. 2 , the auxiliary support frame 25 may be disposed between the horizontal support frames 21 in the thickness direction of the body 10 , for example, in the Y-axis direction of FIG. 2 .

As shown in Figure 2 in one embodiment, a plurality of auxiliary support frame 25 is disposed between both ends in the longitudinal direction of the body 10, may also be disposed between the vertical support frame (23). Accordingly, it is possible to prevent the body 10 from rapidly contracting or expanding in the thickness direction due to a change in external pressure, and to maintain the shape of the body 10 in the thickness direction.

2 shows that three auxiliary support frames 25 are disposed, but the number is not particularly limited. For example, two or less or four or more auxiliary support frames 25 may be disposed. In addition, two or more auxiliary support frames 25 may be disposed between both ends of the body 10 and the vertical support frame 23 closest thereto. In addition, two or more auxiliary support frames 25 may be disposed between the vertical support frames 23 .

Accordingly, the overall shape of the support frame 20 is as follows. A plurality of horizontal support frames 21 having a streamlined shape are disposed spaced apart by a predetermined interval in the height direction, and a plurality of rectangular vertical support frames 23 are disposed between ends of the horizontal support frames 21 in the longitudinal direction. this is placed In addition, a plurality of auxiliary support frames 25 are disposed in the thickness direction of the horizontal support frame 21 so as not to overlap with the short side of the vertical support frame 23 .

In one embodiment, the support frame 20 may further include a front frame 27 . As shown in FIG. 5, the front frame 27 is mounted on the front end of the body 10 and/or the front end of the horizontal support frame 21, and may have a streamlined shape. For example, the front frame 27 has a curved shape convex to one side when viewed from the top, and may have a shape corresponding to a part of the outer surface of the cylinder when viewed from the front.

The front frame 27 having such a shape is disposed at the front end of the body 10 to support the front end of the horizontal support frame 21 and maintain the shape of the body 10 in a streamlined airfoil shape.

In one embodiment, the support frame 20 may be a plurality of auxiliary support straps or perforated horizontal membranes disposed between the horizontal support frames 21 in the thickness direction of the body 10 . These plurality of auxiliary support straps or perforated horizontal membranes are disposed between the horizontal support frames 21 in the thickness direction of the body 10, and when the airship 1 reaches the target altitude, it expands and the volume of the body 10 increases. It becomes the maximum, and the streamlined vertical wing shape is completed.

Although not shown in FIG. 2 , the auxiliary support strap is connected not only to horizontal support frames of the same height but also to horizontal support frames of different heights to prevent distortion of the air bag.

More specifically, a state in which the body 10 according to an embodiment of the present invention expands will be described with reference to FIG. 5 .

When the support frame 20 is disposed inside the body 10 and all internal air is discharged, the body 10 has an elongated shape extending in the longitudinal direction as shown in FIG. 5(a). Here, the support frame 20 may maintain a folded state inside the body 10 . In particular, the horizontal support frame 21 of the support frame 20 may be contracted in a straight line by maintaining a folded state. In addition, the vertical support frame 23 and the auxiliary support frame 25 may be disposed between the horizontal support frame 21 in the longitudinal direction.

Here, since the internal air cannot be smoothly discharged when the support frame 20 has a streamlined shape, all internal air of the body 10 must be discharged before the support frame 20 has a streamlined shape.

When the next buoyancy gas is injected, a part of the body 10 expands, and the support frame 20 disposed therein, in particular, the horizontal support frame 21 is unfolded. Here, the front frame 27 may be mounted on the front end of the body 10 as shown in (b) and (c) of FIG. 5 . That is, in order to smoothly discharge the internal air, the support frame 20 must be streamlined again after all internal air of the body 10 is discharged before the support frame 20 is streamlined. To this end, the shape of the support frame 20 can be easily maintained by mounting the streamlined front frame 27 to the front end of the body 10 .

And when the airship 1 reaches the target altitude, the body 10 fully expands while the support frame 20 unfolds, and may have a final shape as shown in (d) of FIG. 5 .

One or more propellers 30 may be disposed on one side of the body 10 to generate thrust of the airship 1 or adjust the direction of the airship 1.

As shown in FIGS. 2 to 4 in one embodiment, the propeller 30 is disposed at the front end of the body 10 to generate thrust and the front propeller 31 disposed at the rear of the body 10 to change direction. It may include a rear propeller 33 that does.

In one embodiment, the front propeller 31 may be disposed below the central axis AX1 of the body 10 . In particular, as shown in FIG. 2 , in the front propeller 31 , at least a portion of the blades may be positioned under the body 10 through a support structure extending downward from the front end of the body 10 . Through this, it is possible to minimize thrust loss by preventing air flow from being blocked by the body 10 .

In one embodiment, the angle of the front propeller 31 and the rear propeller 33 may be adjustable. For example, the front propeller 31 and the rear propeller 33 may be connected to the support structure rotatably connected to the body 10 . Accordingly, by adjusting the directions of the front propeller 31 and the rear propeller 33, the airship 1 can be raised and lowered. In addition to this, the front propeller 31 and the rear propeller 33 can rotate around the X, Y and Z axes.

More specifically, as shown in FIG. 6, when the airship 1 is to be lowered, the buoyant gas outlet 40 disposed on one side of the body 10 is opened to discharge the buoyant gas from the body 10 to the outside. . In addition, by adjusting the direction of the front propeller 31 and the rear propeller 33 to face upward, it is possible to lower the airship 1 by generating downward thrust.

Here, since the buoyancy gas is lighter than air, the buoyancy gas outlet 40 may be disposed above the body 10, for example, at the rear of the top of the body 10. In addition, as the buoyant gas is discharged, as shown in FIG. 6 , the lower part of the body 10 is gradually contracted, so that the support frame 20 can be folded and folded.

With reference to FIGS. 7 to 9 , an operation of the airship 1 ascending will be described.

First, buoyancy gas is injected into the body 10 to raise the airship 1. Considering the atmospheric pressure in the stratosphere, the buoyant gas may correspond to 1/15 of the maximum volume in which the body 10 can expand. Since the injected lift gas is lighter than air, it moves to the upper part of the airship 1, and accordingly, the upper part of the body 10, that is, the upper part 13 of the air bag expands, and the lower part, that is, the lower part 15 of the air bag still contracts become a state

Accordingly, as shown in FIGS. 8 and 9, the airship 1 has a thin plate shape in the vertical direction as a whole, so it can rise quickly while receiving relatively small air resistance compared to a general airship.

In one embodiment, the airship 1 may further include a buoyancy gas tank 50 . As shown in FIG. 2 , the lift gas tank 50 may be disposed as a payload of the airship 1 .

The buoyancy gas tank 50 may replenish a small amount of buoyancy gas flowing out as the airship 1 stays in the air for a long time by discharging the buoyancy gas into the body 10 . In addition, the buoyancy gas tank 50 increases buoyancy by discharging a small amount of buoyancy gas near the ground to the inside of the body 10 when the airship 1 descends, thereby lowering the landing speed of the airship 1 to land safely. can make it

In one embodiment, the airship 1 may further include a gondola 60. As shown in FIG. 2 , the gondola 60 may be disposed under the airship 1 . The gondola 60 may be equipped with loads necessary for the airship 1 to perform its mission, or a power supply (such as a battery) for propulsion or control of the airship 1, a measurement device, a communication device, or a control device. In one embodiment, the buoyancy gas tank 50 may be mounted on the gondola 60.

10 shows an airship 1A according to another embodiment of the present invention.

When compared with the airship 1 described above, the airship 1A according to FIG. 10 has a different configuration regarding the front propeller 31A, and the rest of the configuration may be the same. Hereinafter, the structure related to the front propeller 31A will be mainly described.

The airship 1A may include a plurality of front propellers 31A. For example, as shown in Fig. 10, the front propellers 31A may be arranged in pairs on both sides of the body 10A. 10 shows that a pair of front propellers 31A are disposed on the left and right sides, but is not limited thereto, and the number of front propellers 31A may be provided in an even number such as two, four, or six. In this way, the thrust of the airship 1A can be further increased by providing a plurality of forward propellers 31A. In particular, since each of the front propellers 31A is disposed on both sides of the body 10A, it is possible to minimize a decrease in propulsion efficiency due to the blocking of air flow by the front propeller 31A by the body 10A.

11 shows an airship 1B according to another embodiment of the present invention.

Compared to the airship 1 described above, the airship 1B according to FIG. 11 may further include a solar cell panel 50B, and other configurations may be the same. Hereinafter, the configuration of the solar cell panel 50B will be mainly described.

As shown in Figure 11, the airship (1B) may further include a plurality of solar cell panels (50B) disposed on the side of the body (10B). A plurality of solar cell panels 50B may be disposed on the side of the body 10B in the form of a thin film. Alternatively, the solar cell panel 50B itself may be used as the outer skin of the body 10B through a separate surface treatment. Accordingly, by generating electric power through the solar cell panel 50B, it is possible to achieve long endurance of the airship 1B.

12 and 13 show an airship 1C according to another embodiment of the present invention.

Compared to the airship 1 described above, the airship 1C according to FIGS. 12 and 13 may further include an auxiliary airbag 60C, and the rest of the configuration may be the same. Hereinafter, the structure of the auxiliary air bag 60C will be mainly described.

As shown in FIGS. 12 and 13 , the auxiliary air bag 60C is disposed inside the body 10C and external air can be introduced and discharged. For example, the auxiliary air bag 60C may be disposed below the body 10C in consideration of the difference in density between the air and the buoyancy gas.

The auxiliary bladder 60C may be used to elevate the airship 1C. For example, as described above, the airship 1C is lowered by injecting or discharging the buoyant gas, rotating the propeller 30 to generate upward or downward thrust, and simultaneously injecting outside air into the auxiliary airbag 60C. Alternatively, the airship 1C can be raised by discharging air from the auxiliary air bag 60C.

That is, as shown in (a) of FIG. 13 , when the airship 1C intends to ascend, the air contained in the auxiliary airbag 60C can be discharged to the outside. Accordingly, the auxiliary air bag 60C may be in close contact with the lower side of the body 10 . And, as shown in (b) of FIG. 13, when the airship 1C wants to descend, outside air can be injected into the auxiliary air bag 60C. Accordingly, the auxiliary bladder 60C is inflated.

14 shows an airship 1D according to another embodiment of the present invention.

Compared to the airship 1 described above, the airship 1D according to FIG. 14 may further include a control surface 70D, and the rest of the configuration may be the same. Hereinafter, the configuration of the control surface 70D will be mainly described.

As shown in FIG. 14 , the airship 1D may not include the rear propeller 33 . Instead, the airship (1D) may further include a control surface (70D) disposed at the rear of the body (10D) to control the attitude of the airship (1D).

In one embodiment, the body 10D may further include an incision 80D in which a lower part of the rear end is cut. Also, the control surface 70D may be rotatably connected to one side of the cutout 80D. More specifically, the control surface 70D may have a shape with a streamlined tip end similar to the body 10D, and may be seated on the cutout 80D and rotatably connected to the upper surface of the cutout 80D through a rotation shaft. there is.

Accordingly, the attitude of the airship 1D can be controlled while the control surface 70D rotates around the axis of rotation.

As such, the present invention has been described with reference to the embodiments shown in the drawings, but this is only an example. Those skilled in the art can fully understand that various modifications and equivalent other embodiments are possible from the embodiments. Therefore, the true technical protection scope of the present invention should be determined based on the appended claims.

Specific technical details described in the embodiments are examples, and do not limit the technical scope of the embodiments. In order to briefly and clearly describe the description of the invention, descriptions of conventional general techniques and configurations may be omitted. In addition, the connection of lines or connection members between the components shown in the drawing is an example of functional connection and / or physical or circuit connection, which can be replaced in an actual device or additional various functional connections, physical connections, or circuit connections. In addition, if there is no specific reference such as "essential" or "important", it may not necessarily be a component necessary for the application of the present invention.

“Above” or similar designations described in the description and claims of the invention may refer to both singular and plural, unless otherwise specifically limited. In addition, when a range is described in an embodiment, it includes an invention in which individual values belonging to the range are applied (unless there is no description to the contrary), and each individual value constituting the range is described in the description of the invention. same. In addition, if there is no clear description or description of the order of steps constituting the method according to the embodiment, the steps may be performed in an appropriate order. Embodiments are not necessarily limited according to the order of description of the steps. The use of all examples or exemplary terms (eg, etc.) in the embodiments is simply to describe the embodiments in detail, and unless limited by the claims, the examples or exemplary terms limit the scope of the embodiments. It is not. In addition, those skilled in the art will appreciate that various modifications, combinations and changes may be made according to design conditions and factors within the scope of the appended claims or equivalents thereof.

1: airship
10: body
20: support frame
30: propeller

Claims (13)

An airship comprising a body having a buoyancy gas and one or more support frames therein and one or more propellers,
The body has a vertical wing shape with a streamlined shape in which the shape of the cross section is symmetrical, the airship. According to claim 1,
the one or more propellers
A front propeller disposed at the front end of the body to generate thrust; and
An airship comprising a; rear propeller disposed at the rear of the body to change direction. According to claim 2,
The front propellers are disposed in pairs on both sides of the body, the airship. According to claim 2,
The front propeller and the rear propeller are rotatable in a predetermined direction to generate upward or downward thrust, the airship. According to claim 1,
The one or more support frames
a plurality of horizontal support frames disposed along an inner surface of the body; and
A plurality of vertical support frames disposed between the front and rear ends of the body and connecting the plurality of horizontal support frames; including, the airship. According to claim 5,
Wherein the plurality of horizontal support frames are elastically deformable in a horizontal direction according to a difference in pressure between the inside and outside of the airship, the airship. According to claim 6,
In a state in which the internal air of the body is discharged, the plurality of horizontal support frames maintain a straight shape,
The at least one support frame further comprises a streamlined front frame mounted on the front ends of the plurality of horizontal support frames, the airship. According to claim 5,
The one or more support frames include a plurality of auxiliary support straps or perforated horizontal membranes disposed between the horizontal support frames in the thickness direction of the body. According to claim 1,
Further comprising a plurality of solar cell panels disposed on the side of the body, the airship. According to claim 1,
Arranged inside the body and further comprising an auxiliary air bag through which external air is introduced and discharged, the airship. According to claim 1,
Arranged at the rear of the body, further comprising a control surface for controlling the posture of the airship, the airship. According to claim 11,
The body has an incision in which a lower portion of the rear end is cut,
The control surface is rotatably connected to one side of the incision, the airship. According to claim 1,
Arranged as a payload of the airship, further comprising a lift gas tank for supplying lift gas to the inside of the body to control the lifting speed of the airship, the airship.

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