KR102607046B1 - Airship of vertical wing shape - Google Patents

Abstract

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

Description

Airship of vertical wing shape}

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

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

In mid-latitude areas such as Korea, the area starting from 10 to 13 km above the ground and extending up to about 50 km is called the stratosphere. Even in the stratosphere, the altitude of about 20 to 25 km above the ground has relatively small wind speeds and shows stable meteorological phenomena compared to other altitudes in the stratosphere. , Research on mooring an airship at this altitude for a long period of time and using it as a platform for Internet communication/relay or earth observation/surveillance has been actively researched for over 20 years. An airship that has a function similar to that of a satellite but acts as a platform while hovering for a long period of time at a stratospheric altitude, which is much lower than the satellite orbit, is hereinafter referred to simply as a ‘stratospheric airship.’ Additionally, hereinafter simply referred to as ‘stratosphere’ refers to the stratosphere at an altitude of approximately 20 km.

In the stratosphere, atmospheric pressure is usually lowered to about 1/20 of that on the ground, and density is also lowered to about 1/15, so in order for an airship to rise to the stratosphere, the volume of the air sac must be expanded to about 15 times compared to that on the ground.

Westerly winds mainly blow in the stratosphere above the Korean Peninsula, and wind speeds are known to occur at an average of 5 to 10 m/s and temporarily up to 35 m/s during winter when wind speeds are strong. Therefore, in order to overcome this wind and remain in one point, it is necessary to design the airship in a shape that minimizes aerodynamic drag due to wind speed.

Stratospheric airships are greatly affected by wind even while departing from the ground and ascending to the stratosphere. In particular, high wind speeds must be overcome when passing through the jet stream zone. Therefore, it is advantageous for the airship to have an aerodynamic shape that can quickly reach the stratosphere with as little influence from the wind as possible, not only when moving horizontally for apex endurance in the stratosphere, but also when moving vertically in the troposphere. Of course, even when lowering 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. In other words, it is necessary to design the shape of the airship to have low resistance to wind during both vertical and horizontal movement.

Most of the airships known to have been promoted at home and abroad to date have a streamlined cylindrical shape similar to the traditional airship shape, as shown in Figure 1, with an X-shaped or V-shaped tail. However, to date, there are no known cases of airships that have succeeded in long-term flight in the stratosphere, not only domestically but also overseas. Therefore, it is not known what shape an airship should be manufactured in that is most advantageous for long-term apex endurance in the stratosphere and ascending/descending movement in the troposphere.

Such prior art is technical information that the inventor possessed for deriving the present invention or acquired in the process of deriving the present invention, and cannot necessarily be said to be known art disclosed to the general public before the application for the present invention.

Japanese Patent Publication JP 1994-199290 A

The present invention is an invention to solve the above-mentioned problems, and can provide an airship of a new shape considering the operating concept of the airship.

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

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

In an airship according to an embodiment of the present invention, the one or more propellers may include a front propeller disposed at the tip 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 arranged 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 be able to rotate in a predetermined direction to generate thrust upward or downward.

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 a front end and a rear end of the body, and 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 the horizontal direction according to the difference in internal and external pressure of the airship.

In the airship according to an embodiment of the present invention, the plurality of horizontal support frames maintain a straight shape when the internal air of the body is discharged, and the one or more support frames are located at the front ends of the plurality of horizontal support frames. It may further include a streamlined front frame that is 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 strings or a perforated horizontal membrane disposed between the horizontal support frames in the thickness direction of the body.

The auxiliary support string is connected not only to the horizontal support frame at the same height but also to the horizontal support frame at a different height, thereby preventing the air sac from being distorted.

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 sac through which external air is introduced and discharged.

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

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

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 flotation gas tank that supplies flotation gas into the interior of the body to control the lifting and lowering speed of the airship.

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

Unlike conventional airships, the airship according to an embodiment of the present invention has a thin wing shape in the vertical direction, enabling rapid lifting and lowering operations to the stratosphere.

The airship according to an embodiment of the present invention can utilize the effect of rapid lifting and lowering operations not only in the stratosphere but also in the troposphere.

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

Since the present invention can be modified in various ways and can 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 transformations, equivalents, and substitutes included in the spirit and technical scope of the present invention. In describing the present invention, the same identification numbers are used for the same components even if they are shown in different embodiments.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. When describing with reference to the drawings, identical or corresponding components will be assigned the same reference numerals and redundant description thereof will be omitted. .

In the following embodiments, terms such as first and second are used not in a limiting sense but for the purpose of distinguishing one component from another component.

In the following examples, singular terms include plural terms unless the context clearly dictates otherwise.

In the following embodiments, terms such as include or have mean that the features or components described in the specification exist, and do not exclude in advance the possibility of adding one or more other features or components.

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

In the following embodiments, the x-axis, y-axis, and z-axis are not limited to the three axes in the Cartesian coordinate system, but can 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 also refer to different directions that are not orthogonal to each other.

In cases where an embodiment can be implemented differently, a specific process sequence may be performed differently from the described sequence. For example, two processes described in succession may be performed substantially at the same time, or may be performed in an order opposite to that in which they are described.

The terms used in this application are only used to describe specific embodiments and are not intended to limit the invention. In this application, terms such as “comprise” or “have” are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Figure 1 shows a conventional airship 2. In addition, Figures 2 to 4 show an airship (1) according to an embodiment of the present invention, Figure 5 shows a state in which the body is expanded, and Figure 6 shows a state in which the airship (1) of the present invention is descended, Figures 7 to 9 show the 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 is injected with levitating gas from the ground and moves in the stratosphere at a target altitude, for example, 10 km to 50 km above the ground. More specifically, the airship 1 can move in the stratosphere at a height of 15 km to 25 km above the ground, and more specifically at a height of 20 km above the ground.

Referring to FIGS. 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 Figure 1, the conventional airship is a cylindrical airship (2) with a streamlined tip like a torpedo or bullet, while the airship (1) according to an embodiment of the present invention is a vertical airship (2) with a streamlined cross-section. It may have a wing shape. Additionally, the airship 1 may have a streamlined cross-sectional shape with left and right symmetry. Additionally, the length of the airship 1 in the first direction (eg, x-axis direction) may be greater than the length in the second direction (eg, y-axis direction). Through this 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 flotation 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. Additionally, in a longitudinal cross-section, for example, the YZ plane of FIG. 2, both edges may have a straight shape. For reference, unless there is a special limitation, hereinafter, “longitudinal section” refers to the cross section in the height direction when the airship (1) is viewed from the front, that is, the YZ plane, and “transverse section” refers to the longitudinal direction when the airship (1) is viewed from above. represents the cross section, that is, the XY plane.

In one embodiment, the body 10 may have a streamlined shape that is symmetrical with respect to a first direction extending from the front end to the rear end (for example, the X-axis direction in FIG. 2). For example, as shown in FIG. 3, when the airship 1 is viewed from the top, the body 10 is symmetrical 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 of the body 10 in the height direction.

Through this configuration, the airship (1) according to an embodiment of the present invention does not have a tail portion and a control surface, and has a single airfoil shape, thereby lowering the drag coefficient when compared to the conventional airship (2). .

In one embodiment, the body 10 has an internal space through which air or floating gas can flow in and out. The type of flotation gas is not particularly limited, and may include gases with lower density and higher stability than air. For example, the flotation gas may be hydrogen gas or helium gas.

In one embodiment, the body 10 may include a main body portion 11. The main body 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 portion 11 are arranged in parallel and spaced apart in a first direction (e.g., the X-axis direction in FIG. 2) to form long sides of a rectangle. can do. Additionally, the upper and lower ends of the main body 11 may be arranged in parallel and spaced apart in a third direction (for example, the Z-axis direction in FIG. 2) to form a rectangular short side.

In one embodiment, the height H of the main body portion 11 may be greater than the length L of the main 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 an overall vertical wing shape, and the 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. Additionally, 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 side shape of the airship (1). Also, when viewed from the front, the main body portion 11 of the airship 1 may have a rectangular, parallelepiped, trapezoidal, or elliptical shape. Hereinafter, as an example, the description will focus on the case where the main body 11 has a rectangular shape when viewed from the side, but this is an example for convenience of explanation and the airship 1, the body 10, or the main body 11 ) is not necessarily limited to a specific shape.

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

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

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

Accordingly, the outer surface of the main body 11 may have a region where the curvature changes in the first and/or second directions, 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 air sac expands as the atmospheric pressure decreases, 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 air bag may have a shape similar to the upper part of the streamlined cylindrical shape.

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

Like the upper part of the air sac (13), the lower part of the air sac (15) 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 streamlined cylindrical lower part.

In one embodiment, the lower part 15 of the air sac, like the upper part 13 of the air sac, may be thicker than the main body 11 or may have the reinforcing member.

In one embodiment, when the airship 1 reaches the target altitude, the side portions of the air sac, that is, the main body 11, the upper part of the air sac 13, and the lower part 15 of the air sac, are expanded. In this state, when the body 10 is viewed from the front, as shown in FIG. 4, both edges of the main body 11 extend in the height direction, and the upper part 13 of the air sac and the lower part 15 of the air sac are each The upper and lower ends of both edges of the main body 11 are extended 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 the streamlined airfoil shape when the airship 1 reaches the target altitude.

In one embodiment, the support frame 20 may have elasticity. For example, when the airship 1 is located on the ground, the support frame 20 may remain folded inside the body 10 after the internal air is exhausted and before the flotation gas is injected. Afterwards, the flotation gas is injected, and as the airship 1 rises and reaches the target altitude, the atmospheric pressure decreases, and the body 10 expands and the support frame 20 unfolds to maintain a predetermined shape. That is, the plurality of support frames 20 may be elastically deformed according to the 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 arranged 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 main body 11 .

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

Although FIG. 2 shows five horizontal support frames 21 arranged in the height direction, the number is not particularly limited. The number of horizontal support frames 21 may be four or less or six or more.

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

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

In Figure 2, two vertical support frames 23 are shown, but the number is not particularly limited. For example, one or three or more vertical support frames 23 may be arranged.

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.

In one embodiment, as shown in FIG. 2, a plurality of auxiliary support frames 25 are disposed between both ends of the body 10 in the longitudinal direction, and may also be disposed between vertical support frames 23. Accordingly, the body 10 can be prevented from rapidly shrinking or expanding in the thickness direction due to changes in external pressure, and the shape of the body 10 in the thickness direction can be maintained.

In Figure 2, three auxiliary support frames 25 are shown, but the number is not particularly limited. For example, two or more or four or more auxiliary support frames 25 may be arranged. Additionally, 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. Additionally, 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 arranged at predetermined intervals in the height direction, and a plurality of rectangular vertical support frames 23 are provided between longitudinal ends of the horizontal support frames 21. This is placed. In addition, a plurality of auxiliary support frames 25 are arranged in the thickness direction of the horizontal support frame 21 so as not to overlap 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 that is convex on one side when viewed from the top, and may have a shape corresponding to a portion of the outer surface of the cylinder when viewed from the front.

The front frame 27 of this shape is disposed at the front end of the body 10 to support the front end of the horizontal support frame 21, thereby maintaining 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 strings or a perforated horizontal membrane disposed between the horizontal support frames 21 in the thickness direction of the body 10. These plural auxiliary support strings or perforated horizontal membranes are disposed between the horizontal support frames 21 in the thickness direction of the body 10, and expand when the airship 1 reaches the target altitude, increasing the volume of the body 10. becomes maximum, and the streamlined vertical wing shape is completed.

Although not shown in FIG. 2, the auxiliary support string can be connected not only to the horizontal support frame of the same height but also to the horizontal support frame of a different height to prevent distortion of the air sac.

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

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

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

When the next flotation gas is injected, a part of the body 10 expands, and the support frame 20 disposed inside, especially the horizontal support frame 21, unfolds. Here, the front frame 27 can be mounted on the front end of the body 10, as shown in Figures 5 (b) and (c). That is, in order to smoothly discharge the internal air, the support frame 20 must be streamlined again after all the internal air of the body 10 has been 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 at the front end of the body 10.

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

One or more propellers 30 are disposed on one side of the body 10, and can generate thrust of the airship 1 or control the direction of the airship 1.

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

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, the front propeller 31 may have at least a portion of its blades positioned below the body 10 through a support structure extending downward from the tip of the body 10. Through this, it is possible to minimize thrust loss by preventing the 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, the airship (1) can be raised and lowered by adjusting the directions of the front propeller (31) and the rear propeller (33). 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 it is desired to lower the airship (1), the flotation gas outlet (40) disposed on one side of the body (10) is opened to discharge the flotation gas from the body (10) to the outside. . In addition, the direction of the front propeller 31 and the rear propeller 33 can be adjusted to face upward, generating downward thrust to lower the airship (1).

Here, since the levitating gas is lighter than air, the levitating gas outlet 40 may be disposed on the upper side of the body 10, for example, at the upper rear of the body 10. Additionally, as the flotation gas is discharged, as shown in FIG. 6, the lower part of the body 10 may gradually contract, and the support frame 20 may be folded.

The operation of the airship 1 ascending will be described with reference to FIGS. 7 to 9.

First, flotation gas is injected into the body 10 to raise the airship 1. Here, considering atmospheric pressure in the stratosphere, the levitating gas may correspond to 1/15 of the maximum volume to which the body 10 can expand. Since the injected flotation gas is lighter than air, it moves to the upper part of the airship (1), and accordingly the upper part of the body 10, i.e. the upper part 13 of the air sac, expands and the lower part, i.e. the lower part 15 of the air sac, is still contracted. It becomes a state.

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

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

The flotation gas tank 50 discharges flotation gas into the body 10, thereby replenishing a small amount of flotation gas leaked as the airship 1 hovers for a long period of time. In addition, the flotation gas tank 50 increases buoyancy by discharging a small amount of flotation gas into the interior of the body 10 near the ground when the airship 1 descends, thereby lowering the landing speed of the airship 1 to land safely. You can do it.

In one embodiment, the airship 1 may further include a gondola 60. As shown in FIG. 2, the gondola 60 may be placed at the bottom of the airship 1. The gondola 60 may be equipped with payloads necessary for the airship 1 to perform its mission, or a power supply (battery, etc.), measurement device, communication device, or control device for propulsion or control of the airship 1. In one embodiment, the flotation gas tank 50 may be mounted on the gondola 60.

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

The airship 1A according to FIG. 10 has a different configuration regarding the front propeller 31A compared to the airship 1 described above, and the remaining configuration may be the same. Hereinafter, the description will focus on the configuration of the front propeller (31A).

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. In Figure 10, the front propellers 31A are shown as a pair arranged on the left and right sides, but the present invention is not limited thereto, and the number of front propellers 31A may be an even number such as 2, 4, or 6. By providing a plurality of front propellers (31A) in this way, the thrust of the airship (1A) can be further increased. In particular, since each front propeller (31A) is disposed on both sides of the body (10A), it is possible to minimize the decrease in propulsion efficiency due to the air flow by the front propeller (31A) being blocked by the body (10A).

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

Compared to the above-described airship 1, the airship 1B according to FIG. 11 may further include a solar cell panel 50B, and the remaining configuration may be the same. Hereinafter, the description will focus on the configuration of the solar panel 50B.

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 arranged in a thin film form on the side of the body 10B. Alternatively, the solar panel 50B itself can be used as the skin of the body 10B through separate surface treatment. Accordingly, by producing power through the solar panel (50B), long-term endurance of the airship (1B) can be achieved.

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 air bladder 60C, and the remaining configuration may be the same. Below, the description will focus on the configuration of the auxiliary air sac (60C).

As shown in FIGS. 12 and 13, the auxiliary air bladder 60C is disposed inside the body 10C and allows external air to flow in and out. For example, the auxiliary air bladder 60C may be placed at the lower part of the body 10C, taking into account the difference in density between air and buoyant gas.

The auxiliary air bladder 60C can be used to raise and lower the airship 1C. For example, as described above, the flotation gas is injected or discharged, the propeller 30 is rotated to generate upward or downward thrust, and at the same time, external air is injected into the auxiliary air bag 60C to lower the airship 1C. Alternatively, the airship (1C) can be raised by expelling air from the auxiliary air bag (60C).

That is, as shown in (a) of FIG. 13, when the airship 1C wants to ascend, the air contained in the auxiliary air bag 60C can be discharged to the outside. Accordingly, the auxiliary air sac (60C) can 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, external air can be injected into the auxiliary air bag 60C. Accordingly, the auxiliary air sac (60C) expands.

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

Compared to the above-described airship 1, the airship 1D according to FIG. 14 may further include a control surface 70D, and the remaining configuration may be the same. Hereinafter, the description will focus on the configuration of the control surface 70D.

As shown in Figure 14, airship 1D may not include a 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 a cut portion 80D in which a portion of the lower portion of the rear end is cut. And the control surface (70D) may be rotatably connected to one side of the cutout portion (80D). More specifically, the control surface 70D may have a streamlined shape at the tip, similar to the body 10D, and may be seated on the cutout part 80D and rotatably connected to the upper surface of the cutout part 80D through a rotation axis. there is.

Accordingly, the control surface (70D) rotates around the rotation axis to control the attitude of the airship (1D).

Although the present invention has been described with reference to the embodiments shown in the drawings, these are merely examples. 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 attached claims.

The specific technical content described in the embodiment is an example and does not limit the technical scope of the embodiment. In order to describe the invention concisely and clearly, descriptions of conventional general techniques and configurations may be omitted. In addition, the connection of lines or the absence of connections between components shown in the drawings exemplify functional connections and/or physical or circuit connections, and in actual devices, various functional connections or physical connections may be replaced or added. It can be expressed as connections, or circuit connections. Additionally, if there is no specific mention such as “essential,” “important,” etc., it may not be a necessary component for the application of the present invention.

“The” or similar designators used in the description and claims may refer to both the singular and the plural, unless otherwise specified. In addition, when a range is described in an example, the invention includes the application of individual values within the range (unless there is a statement to the contrary), and each individual value constituting the range is described in the description of the invention. same. Additionally, unless the order of the steps constituting the method according to the embodiment is clearly stated or there is no description to the contrary, the steps may be performed in an appropriate order. The embodiments are not necessarily limited by the order of description of the steps above. The use of any examples or illustrative terms (e.g., etc.) in the embodiments is merely to describe the embodiments in detail, and unless limited by the claims, the examples or illustrative terms do not limit the scope of the embodiments. That is not the case. Additionally, 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 their equivalents.

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

Claims (13)

An airship comprising a body having flotation gas therein 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,
The one or more support frames are
a plurality of horizontal support frames disposed along the inner surface of the body; and
A streamlined front frame mounted on the front end of the plurality of horizontal support frames. According to claim 1,
The one or more propellers
a front propeller disposed at the tip of the body to generate thrust; and
An airship including a rear propeller disposed at the rear of the body to change direction. According to clause 2,
An airship, wherein the front propellers are arranged in pairs on both sides of the body. According to clause 2,
The front propeller and the rear propeller are capable of rotating in a predetermined direction to generate upward or downward thrust. According to claim 1,
The one or more support frames are
An airship comprising: a plurality of vertical support frames disposed between the front and rear ends of the body and connecting the plurality of horizontal support frames. According to clause 5,
The plurality of horizontal support frames are elastically deformable in the horizontal direction according to the difference in internal and external pressure of the airship. According to clause 6,
An airship wherein the plurality of horizontal support frames maintain a straight shape while the internal air of the body is discharged. An airship comprising a body having flotation gas therein 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,
The one or more support frames are
a plurality of horizontal support frames disposed along the inner surface of the body; and
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 or 8,
An airship, further comprising a plurality of solar panels disposed on sides of the body. According to claim 1 or 8,
An airship disposed inside the body and further comprising an auxiliary air sac through which external air is introduced and discharged. According to claim 1 or 8,
An airship disposed at the rear of the body, further comprising a control surface that controls the attitude of the airship. According to claim 11,
The body has an incision in the lower part of the rear end,
The control surface is rotatably connected to one side of the incision, an airship. According to claim 1,
The airship is disposed as a payload of the airship and further includes a flotation gas tank that supplies flotation gas to the interior of the body to control the lifting and lowering speed of the airship.

Images