KR102085916B1 - The apparatus for unfolded glide wings - Google Patents

Abstract

The present invention relates to an accommodating and unfolding device for a glide wing. The accommodating and unfolding device for a glide wing is inserted into a projectile. The accommodating and unfolding device for a glide wing includes: a case unit including a body and a wing hole, wherein the body includes an accommodation space divided by a partition installed at the center and the wing hole is connected to the accommodation space and formed symmetrically on both sides of the body; and a wing unfolding unit including a first wing, a second wing, and a link assembly. The first wing includes a link moving groove on one side and is piled on the partition in order. The second wing is piled on one side of the first wing. The link assembly is vertically connected between one end of the second wing and one end of the link moving groove. The first wing passes through the wing hole to protrude and be unfolded, and the link moving groove is horizontally moved. The link assembly rotates at the other end of the link moving groove, and the first wing and the second wing are horizontally connected.

Description

Gliding wing storage deployment device {The apparatus for unfolded glide wings}

The present invention relates to a gliding wing accommodating device, and to a gliding wing accommodating device for deploying a gliding wing after reaching the target altitude to allow the projectile having the gliding to fly with minimal energy.

The artillery is divided into plain sand (gun), mortar (mortar) and howitzer (howitzer) according to the angle of trajectory in which the shell flies.

It is necessary to implement the gliding wing on the outside of the projectile so that the gliding flight is possible to secure the range of the shell which is gradually becoming a long distance.

For the above technique, a wing deployment apparatus has been disclosed in Korean Patent Registration No. 10-1688951 'Finger Wing Symmetrical Deployment Apparatus and Aircraft Having The Same'. However, the invention of Korean Patent No. 10-1688951 requires an opening 11 corresponding to the length of the wing to be formed in the body, so it may require a tall body or there may be a limitation in the length of the wing.

In addition to the above invention, the existing developed wing structure may be difficult to apply to a system of a projectile as most of the wing structures are applied to missiles or drones or airdrop missiles. Therefore, it is possible to operate the gliding flight while maintaining the shape of a projectile such as artillery, and in order to store and deploy wings of a certain size, it is necessary to develop a technology for a gliding wing of a new concept.

Korean Registered Patent No. 10-1356554 (Registration Date: 2014. 01. 22) Korea Patent Registration No. 10-1688951 (Registration Date: 2016. 12. 16)

The technical problem to be achieved by the present invention is to maintain the appearance of the projectile, and equipped with a gliding wing storage deployment device inside the projectile by deploying the gliding wing after reaching the target altitude gliding wing that can launch the gliding flight with minimal energy It is an object to provide a storage deployment apparatus.

In addition, another technical problem to be achieved by the present invention, by providing a link structure for deployment and a wing coupling pin for preventing malfunction in the stacking deployment wing portion gliding wing storage that can stably deploy the gliding wings after reaching the target altitude. The purpose is to provide a deployment device.

The object of the present invention is not limited to the above-mentioned object, and other objects not mentioned will be clearly understood by those skilled in the art from the following description.

In order to solve the above problems, the present invention is a sliding wing storage deployment apparatus inserted into the projectile, the body is provided with a storage space is divided into the interior based on the partition wall located in the center, the body is in communication with the body A case part including a wing hole symmetrically formed at both sides of the; And a first wing sequentially stacked on the partition wall and having a link moving groove on one side thereof, a second wing stacked on one side of the first wing, and one end of the link moving groove and the second wing. And a wing deployment driving part including a link assembly vertically coupled between one end of the wing, wherein the first wing protrudes through the wing hole and the link moving groove moves horizontally, and the link moving groove The link assembly is rotated at the other end of the first wing and the second wing may provide a sliding wing storage deployment device, characterized in that the horizontal coupling.

The first wing has a wing coupling hole therein, the second wing has a wing coupling pin therein, the link assembly is rotated so that the wing coupling pin is inserted into the wing coupling hole to the first wing And the second wing may be horizontally coupled.

The link assembly includes a link body, a link pin provided at one end of the link body and coupled to one end of the link moving groove, and provided at the other end of the link body and coupled to one end of the second wing. It may include a link axis of rotation.

The link rotation shaft has wing coupling pin stoppers at both ends, and one end of the wing coupling pin is positioned in contact with the wing coupling pin stopper so that the wing coupling pin can be released by rotation of the link rotation shaft.

The first wing and the second wing may be inclined on the coupling surface.

The deployment wing unit may have a center of gravity at a position different from the center of gravity of the projectile.

The center of gravity of the first wing is formed at a position different from the center of gravity of the projectile, it may be formed by moving the center of gravity to the opposite side of the wing hole with respect to the center of the projectile.

The first wing or the second wing may be provided with a transfer rack on one surface so as to be parallel to the deployment direction.

The deployable glide wing apparatus may include a deployment drive unit having a transport shaft in which a pinion is formed to rotate in engagement with the transport rack and sequentially horizontally moving the first wing or the second wing.

The deployment driving unit may include a spring panel that contacts a surface of the second wing and applies a force in a vertical direction to an inner surface of the body portion.

The second wing may be formed with an angle adjusting groove engaged with the pinion in the other end region.

The gliding wing accommodating device according to an embodiment of the present invention maintains the appearance of the projectile and includes a gliding wing accommodating device inside the projectile to deploy the gliding wing after reaching the target altitude so that the projectile can glide with minimal energy. There is an advantage to it.

In addition, by having a link structure for deployment and a wing coupling pin for preventing malfunction, the gliding wing can be stably deployed after reaching the target altitude.

1 is a perspective view showing a part of the projectile, the gliding wings are deployed according to an embodiment of the present invention,
Figure 2 is an exploded perspective view showing a gliding wing storage deployment apparatus according to an embodiment of the present invention,
3 is a cross-sectional view showing a gliding wing storage deployment apparatus according to an embodiment of the present invention,
Figure 4 is a perspective view showing the storage state of the deployment wing portion of the gliding wing storage deployment apparatus according to an embodiment of the present invention,
5 is a perspective view showing a coupling state of the deployment wing portion of the gliding wing storage deployment apparatus according to an embodiment of the present invention,
6 is a front view showing a link assembly of a gliding wing storage deployment apparatus according to an embodiment of the present invention,
7 is a cross-sectional view showing a development process of the deployment wing unit according to an embodiment of the present invention;
8 is a cross-sectional view showing the alignment and fixation of the wing wing portion according to an embodiment of the present invention;
9 is a perspective view showing a wing portion and a filler according to an embodiment of the present invention;
10 is a flowchart illustrating a gliding flight step of a projectile having a gliding wing accommodating device according to an embodiment of the present invention.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. The embodiments described below are provided as examples to fully convey the spirit of the present invention to those skilled in the art. Accordingly, the invention is not limited to the embodiments described below and may be embodied in other forms. In the drawings, lengths, thicknesses, and the like of layers and regions may be exaggerated for convenience. Like numbers refer to like elements throughout the specification.

1 is a perspective view showing a part of the projectile is a gliding wing deployment according to an embodiment of the present invention, Figure 2 is an exploded perspective view showing a gliding wing storage deployment apparatus according to an embodiment of the present invention, Figure 3 is an embodiment of the present invention 4 is a cross-sectional view showing a gliding wing storage deployment device according to the embodiment of the present invention, Figure 4 is a perspective view showing a state of deployment of the wing portion of the gliding wing storage deployment device according to an embodiment of the present invention, Figure 5 is a gliding wing storage deployment according to an embodiment of the present invention 6 is a perspective view showing a coupling state of the deployment wing portion of the device, Figure 6 is a front view showing a link assembly of the gliding wing storage deployment device according to an embodiment of the present invention, Figure 7 is a development process of the deployment wing portion according to an embodiment of the present invention 8 is a cross-sectional view showing the wing alignment and fixation of the blade portion according to an embodiment of the present invention, Figure 9 is a perspective view showing the blade portion and the filler according to the embodiment of the present invention 10 is a flowchart illustrating a gliding flight step of a projectile having a gliding wing accommodating device according to an embodiment of the present invention.

1 to 10, in the gliding wing storage deployment device is inserted into the projectile 10 according to an embodiment of the present invention, the gliding wing storage deployment device is a case portion 100, deployment wing 200 It may be provided with, and may include a deployment driving unit (300).

The case part 100 has a body 120 having a storage space (A and B of FIG. 8) divided therein with respect to the partition wall 110 positioned at the center thereof, and communicates with the storage space, but both sides of the body. Each wing hole (130A, 130B) formed symmetrically to may include. In addition, both ends of the body 120 may have a first plug 140A and a second plug 140B for sealing the receiving spaces A and B.

The deployment wing unit 200 is the first wing 210 and the second wing 220 are sequentially stacked on the partition wall 110 may be provided in each of the storage space (A, B), The pair of deployment wings may be symmetrically received based on the partition wall 110. Although it may be described on the basis of any one of the pair of deployment wings in the description described below, this is the same as describing the respective deployment wings 200 together. In addition, the deployment wing unit 200 may further include other wings on the second wing 220 according to the length of the deployed sliding wing or the size of the storage space inside the projectile.

The first wing 210 may have a link moving groove 212 on one side thereof, and the second wing 220 may be stacked on one side of the first wing 210. The link assembly 230 may be vertically coupled between one end of the link moving groove 212 and one end of the second wing 220.

 When the projectile reaches the altitude input to the flight control device located inside the projectile 10, the projectile is attenuated in rotation. After the rotational and centrifugal forces disappear, the launch vehicle can perform horizontal maneuver control by the flight control device.

The deployment wing unit 200 may be provided with a center of gravity at a position different from the center of gravity (C1) of the projectile (10). In addition, the center of gravity (C2) of the first wing is formed at a position different from the center of gravity (C1) of the projectile, to the opposite side of the wing hole (130A, 130B) on the basis of the center of gravity of the projectile (10) The center of gravity may be formed by moving. For example, one end portion and the other end portion at which the first wing 210 protrudes for the first time may be formed of materials having different densities to move the center of gravity of the wings, and the first wing 210 or the second wing ( 220 is positioned so as to be deflected to one side from the center of the inside of the storage space to move the center of gravity of the wing relative to the center of gravity of the projectile.

Therefore, until the projectile 10 reaches the input altitude, the deployment wing unit 200 is fixed in the storage space so that the deployment wing unit 200 does not escape to the outside even when the projectile is rotated without a separate fixing device or external force. Can be located. In addition, as the rotational force of the projectile 10 is weakened at the time of deployment of the wing, the centrifugal force acting on the first wing 210 is also reduced, so that the wing can be deployed even with the driving force of the motor provided in the deployment driver 300. have.

After the horizontal start control of the projectile 10, the first wing 210 protrudes through the wing hole, and thus the link moving groove 212 formed in the first wing 210 may move horizontally toward the outside of the projectile. . That is, the link assembly 230 may move from one end of the link moving groove 212 to the other end when the link moving groove 212 is moved horizontally. Thereafter, the link assembly 230 rotates at the other end of the link moving groove 212 so that the first wing 210 and the second wing 220 are horizontally coupled and the second wing 220 protrudes and develops. Gliding wing may be formed, it may be deployed to the outside of the projectile (10).

The first wing 210 has a wing coupling hole 214 therein, the second wing 220 has a wing coupling pin 224 at a position corresponding to the wing coupling hole 214 therein. When the link assembly 230 rotates, the wing coupling pin 224 is inserted into the wing coupling hole 214 so that the first wing 210 and the second wing 220 are horizontally coupled to the gliding wing. Can be formed. The wing coupling pin 214 and the wing coupling hole 224 may be adjusted in number depending on the wing cross-sectional shape and the thickness of the wing. Areas with relatively thick wings may increase the number of wing coupling pins to improve the bond strength and rigidity of the wings.

Further, the link assembly 230 is provided with a link body 236, a link pin 234 provided at one end of the link body 236 and coupled to one end of the link moving groove 212, and the link. It is provided on the other end of the body 236 may include a link rotating shaft 232 coupled to one end of the second wing (220).

In addition, the link rotation shaft 232 is provided with a wing coupling pin stopper 232A at both ends, one end of the wing coupling pin 224 is located in contact with the wing coupling pin stopper 232A to the link rotation shaft 232 Rotation of the wing coupling pin 224 can be released.

In detail, after the horizontal start control of the projectile 10, as shown in FIG. 7, the first wing 210 may be horizontally moved to the outside of the wing hole and protruded.

In this case, the first wing 210 or the second wing 220 may be provided with a transport rack parallel to the deployment direction on one surface, the deployment drive unit 300 is engaged with the transport rack to rotate the pinion (310) It is provided with a feed shaft 320, it is possible to sequentially horizontally move the first blade 210 or the second blade 220 by the rotation of the feed shaft 320. The deployment driving unit 300 may further include a motor and a rack gear connected to the feed shaft 320.

That is, the pinion 310 rotates due to the rotation of the feed shaft 320 connected to the motor and the recreation gear, and the pinion 310 meshes with the feed rack 216 formed on one surface of the first wing 210. The transport rack 216 is horizontally moved by the rotation of the 310 so that the first wing 210 may protrude outwardly from the projectile 10.

While the first wing 210 is horizontally deployed, the link moving groove 212 formed in the first wing 210 may also be horizontally moved to protrude outwardly of the projectile 10, thereby linking the structure 230. The link pin 234 of the link moving groove 212 is moved horizontally along the groove (212h) located on the side so that the link structure 230 can move from one end of the link moving groove 212 to the other end. .

A link pin fixing groove 213 may be located at the other end of the link moving groove 212, and the link pin 234 is fixed to the link pin when the link structure 230 reaches the other end of the link moving groove 212. May be coupled to the groove 213. Thereafter, the link structure 230 rotates the link body 236 about the link rotation shaft 232, and wing coupling pin stoppers 232A formed at both ends of the link rotation shaft 232 are rotated so that the wing coupling pins are rotated. 224 may be unlocked. That is, the wing coupling pins 224 released at the same time as the lowering of the second wing 220 is inserted into the wing fixing groove 214 of the first wing 210 and the first wing 210 and the second wing 220. Can be combined. The other end of the wing coupling pin 224 may be coupled to the spring, the wing coupling pin 224 may be inserted into the wing fixing groove 214 by the elasticity of the spring after release.

In addition, the first wing 210 and the second wing 220 to minimize the interference between the coupling end (210A, 220A) of each wing when the first wing 210 and the second wing 220 is coupled. May have a slope formed on the coupling surface.

The deployment driving unit 300 may include a spring panel 330 that contacts the one surface of the second wing 220 on the inner surface of the body 120 to apply a force in a vertical direction. Therefore, the spring panel 330 exerts a force in the vertical direction toward the empty space after the projecting deployment of the first wing 210 and the second wing 220 moves vertically to the space where the first wing 210 is located. Can be. Thus, the engaging sections 210A, 220A can slide and abut along the inclined surfaces of each of the vanes, and interference between the engaging sections can be minimized during rotation of the link structure 230.

Further, the first stopper 140A and the second stopper 140B positioned at both end portions of the body 120 may be transport grooves 142 for fixing both ends of the feed shaft 320 or moving the feed shaft 320. ) May be provided.

Referring to FIG. 8, after the first wing 210 and the second wing 220 are coupled, the pinion 310 is engaged by the transfer rack 226 and the pinion 310 formed on one surface of the second wing 220. The rotation rack of the second blade (226) is horizontally moved by the rotation of the second blade 220 can be protruded out of the projectile (10). In addition, the second wing 220 may have an angle adjusting groove 228 that is engaged with the pinion 310 in the other end region. Therefore, after completion of the protruding development of the second wing 220, the gliding wing is formed by the combination of the first wing 210 and the second wing 220, the pinion 310 and the angle adjusting groove 228 is engaged with each other by a certain angle. Rotation in the range may be possible. Therefore, it is possible to adjust the combined angle of the transport wheel 320 and the angle adjustment groove 228 and to adjust the horizontal angle of the gliding wing for the projectile 10 according to the atmosphere environment and the gliding flight distance during gliding. Furthermore, the body portion 120 may include a guide groove 122 corresponding to the horizontal angle of the gliding blade at the inner side of the wing hole.

Therefore, the gliding wing accommodating device according to an embodiment of the present invention maintains the appearance of the projectile and includes a gliding wing accommodating device inside the projectile to deploy the gliding wing after reaching the target altitude so that the projectile glides with minimal energy. There is an advantage to flying. In addition, the stack structure deployment wing unit 200 is provided with a link structure 230 for deployment and the wing coupling pin 224 for preventing malfunction, there is an advantage that can reliably deploy the gliding wings after reaching the target altitude.

Further, the deployment wing unit 200 may include a filler 250 attached to each upper side or each lower side of the first wing 210 or the second wing 220 for protection of the wing and ease of stacking. The transfer racks 216 and 226 may be formed on one outer surface of the filler 250. Furthermore, the filler 250 may be removed after the horizontal coupling and the coupling of the first wing 210 and the second wing 220.

Referring to Figure 10 describes the gliding flight process of the projectile with a gliding wing storage deployment device according to an embodiment of the present invention, the projectile 10 with a gliding wing storage deployment device as shown in Figures 1 to 9 launch In operation S110, when the rotation of the projectile is attenuated at an altitude input to the flight control device and the rotational force and the centrifugal force disappear, the projectile 10 performs horizontal start control by the flight control device provided in the projectile (S120).

Thereafter, the first wing is deployed in the wing hole symmetrically formed on the side of the projectile by the deployment driving unit 200 of the gliding wing storage deployment device (S130). That is, the pinion 310 formed on the transport wheel 320 is engaged with the transport rack 216 of the first wing so that the first wing 210 protrudes out of the projectile 10 by the rotation of the transport wheel 320. Therefore, the link moving groove 212 is deployed to the outside so that the link structure 230 moves from one end of the link moving groove 212 to the other end.

Since the first wing and the second wing is combined (S140). That is, when the link structure 230 is positioned at the other end of the link moving groove 212 by the deployment of the first blade 210, the lowering of the second blade 220 due to the vertical pressure of the spring panel 330 and The blade coupling pin 224 is released by the rotation of the link rotating shaft 232 and inserted into the blade fixing groove 214 of the first blade 210, thereby coupling the first blade 210 and the second blade 220 to each other. .

Thereafter, the second blade 220 is developed by the pinion 310 and the transfer rack 226 of the second blade (S150). Therefore, a gliding wing is formed by the combination of the first wing 210 and the second wing 220 to protrude outward of the projectile.

Next, horizontal alignment of the gliding blade is performed (S160). That is, due to the angle adjusting groove 228 formed at the other end of the second wing 220 and the guide groove 122 formed at the inner side of the wing hole, the gliding wing may be horizontally adjusted to complete the gliding of the gliding wing.

Next, the projectile performs a gliding flight by horizontally aligned gliding wings and strikes a target (S170). Due to the angle adjusting groove formed in the second wing 220, it is possible to adjust the horizontal angle of the gliding wing according to the atmospheric environment and the gliding flight distance during gliding and improve the accuracy of hitting the target after gliding.

Although described above with reference to a preferred embodiment of the present invention, those skilled in the art will be variously modified and changed within the scope of the invention without departing from the spirit and scope of the invention described in the claims below I can understand that you can.

10: projectile, 100; Case,
110; Bulkhead, 120; Body
200; Deployment wing unit 210; First Wing,
212; Link moving groove, 214; Wing Coupling Hole,
220; Second wing, 224; Wing Coupling Pin,
228; Angle adjusting groove, 230; Link Structure,
232; Link axis of rotation, 232 A; Wing coupling pin stopper,
234; Link pins, 300; Deployment drive unit,
310; Pinion, 320; Feed axis,
330; Spring panel

Claims (11)

In the gliding wing storage deployment apparatus inserted into the projectile,
A case part including a body having a storage space divided therein based on a partition wall positioned at the center, and a wing hole communicating with the storage space and symmetrically formed at both sides of the body; And
A first wing that is sequentially stacked on the partition wall and has a link moving groove on one side, a second wing that is stacked on one side of the first wing, and one end of the link moving groove and the second wing; Includes; deploying wing comprising a link assembly vertically coupled between one end of the,
The first wing protrudes through the wing hole and the link moving groove moves horizontally, and the link assembly rotates at the other end of the link moving groove so that the first wing and the second wing are horizontally coupled. ,
The first wing has a wing coupling hole therein, the second wing has a wing coupling pin therein, the link assembly is rotated so that the wing coupling pin is inserted into the wing coupling hole to the first wing And the second wing is horizontally coupled to the gliding wing storage deployment device.
delete The method of claim 1,
The link assembly includes a link body, a link pin provided at one end of the link body and coupled to one end of the link moving groove, and provided at the other end of the link body and coupled to one end of the second wing. Gliding wing storage deployment device characterized in that it comprises a link axis of rotation.
The method of claim 3, wherein
The link rotating shaft has wing coupling pin stoppers at both ends, and one end of the wing coupling pin is located in contact with the wing coupling pin stopper so that the wing coupling pin is released by the rotation of the link rotation shaft is gliding wing Storage deployment device.
The method of claim 1,
The first wing and the second wing, gliding wing storage deployment device, characterized in that the inclined surface formed.
The method of claim 1,
The deployment wing unit, the gliding wing storage deployment device characterized in that it comprises a center of gravity at a position different from the center of gravity of the projectile.
The method of claim 1,
The center of gravity of the first wing is formed in a position different from the center of gravity of the projectile, gliding wing storage deployment device, characterized in that formed by moving the center of gravity to the opposite side of the wing hole with respect to the center of the projectile.
The method of claim 1,
The first wing or the second wing, the sliding wing storage deployment device characterized in that it comprises a feed rack parallel to the deployment direction on one surface.
The method of claim 8,
The gliding wing storage deployment device, the gliding wing storage deployment device having a feed shaft formed with a pinion to rotate in engagement with the transfer rack and comprises a deployment drive for sequentially moving the first wing or the second wing. .
The method of claim 9,
The deployment driving unit, the sliding wing storage deployment device characterized in that it comprises a spring panel for applying a force in the vertical direction in contact with the one surface of the second wing on the body of the case.
The method of claim 9,
And the second wing has an angle adjusting groove formed at the other end thereof in engagement with the pinion.

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