KR101863004B1 - Unfolded gilde wings apparatus and missile comprising same - Google Patents

Abstract

The present invention relates to an unfolding glide wing apparatus and a projectile having the same. The unfolding glide wing module according to one embodiment comprises: a wing case having a storage space and an internal wing hole communicating with the storage space; a glide wing module including a plurality of wing cartridges housed in the storage space and stacked in the vertical direction; and an unfolding device which unfolds wing cartridges adjacent to the wing hole among the wing cartridges toward the outside of the internal wing hole by horizontally sliding the wing cartridges outward.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a spreading glide-

The following description relates to a deployable gliding apparatus and a projectile containing the same.

The gun is divided into a flat gun, a mortar, and a howitzer, depending on the angle of the balloon through which the balloon is flying.

The howitzer has a comparatively gentle curvature of the trajectory, and the length of the gun is about 20 times the diameter of the caliper. Generally, it uses the charge that is not strong compared to the flatbed and the weight of the gun is comparatively light.

The latest howitzer has a range that is comparable to a flatbed, due to the application of a long barrel that absorbs the advantages of flatbed, In addition, the accuracy of shooting has been improved by computerization of gunship and automatic heat radiation, and it is added to the development of high-tech shells such as precision guided shells, mine shell shells and reconnaissance shells.

In addition, for reaching the precise target point over long distances, it is required to have a precise flight control of the projectile as well as a method of flying the projectile with minimum energy.

The background art described above is possessed or acquired by the inventor in the derivation process of the present invention, and can not be said to be a known art disclosed in general public before application of the present invention.

It is an object of one embodiment to provide a projectile having a deployable glide wing device and a deployable glide wing device.

According to an embodiment of the present invention, there is provided a deployable glide wing module comprising: a wing case having a storage space and an internal wing hole communicating with the storage space; A glide blade module including a plurality of blade cartridges housed in the storage space and stacked in a vertical direction; And a deployment device for horizontally sliding the wing cartridges adjacent to the wing holes out of the plurality of wing cartridges to the outside of the inner wing holes sequentially.

The plurality of wing cartridges each having an inner wing having a wired shape; And a pillar having at least one surface of the inner wing and having a transporting rack formed thereon, wherein the expansion device is rotatably installed in the wing case, and the transporting rack The stitch may include a transport wheel having a transport pinion.

The filler can be dropped when it is deployed outside the wing case by the transfer wheel.

Wherein the expansion device includes a plurality of blade cartridges installed in the storage space on each side of the plurality of blade cartridges and applying pressure to the plurality of blade cartridges in a direction perpendicular to a developing direction in which the plurality of blade cartridges are deployed May further include a torsion spring.

The expansion device may further include a leaf spring installed on an upper side or a lower side of the storage space and applying pressure in a direction perpendicular to the developing direction in contact with the plurality of blade cartridges.

Wherein each of the plurality of wing cartridges comprises a wing cartridge disposed in an inner passage formed in the inner wing and capable of engaging wing cartridges deployed through the inner wing holes and wing cartridges located within the storage space, As shown in FIG.

The vane coupling includes: a fixture fixed to the internal passage; A plate slider slidable in a direction in which the plurality of blade cartridges are deployed; And an elastic body disposed between the fixture and the plate slider.

The fixture may include an engaging groove recessed in a direction perpendicular to a direction in which the plurality of blade cartridges are deployed, and the plate slider may be formed in an engagement groove of a fastener of a vane coupling provided in another adjacent vane cartridge And can include a fastening hook portion.

The plurality of wing cartridges may further include a wing adjustment cartridge that is finally deployed among the plurality of wing cartridges to adjust the angle of the glide wing module.

The storage space may include a pair of blade adjustment holes formed in the front and rear surfaces facing each other in a direction perpendicular to a direction in which the plurality of blade cartridges are deployed, A wing adjusting shaft which is provided inside the wing adjusting protrusion so as to be protruded in both forward and backward directions and which protrudes toward the pair of wing adjusting holes in contact with the pair of wing adjusting holes when the wing adjusting cartridge is deployed to the outside; And a wing adjustment gear formed along the periphery of one end of the wing adjustment cartridge and meshing with the transport pinion of the transport wheel, and as the transport wheel rotates, the angle of the wing adjustment cartridge is adjusted .

The deployment device may further include a departure prevention device for preventing the glide wing module stored in the wing case from being released to the outside of the inner wing hole.

Wherein the separation preventing device includes a shielding member rotatably installed at a portion of the vane case adjacent to the vane hole and capable of shielding at least a portion of the vane hole; A torsional elastic body applying torque in a direction deviating from a position at which the shielding member shields at least a part of the vane hole; And a separation prevention pin for preventing rotation of the shielding member. When the separation prevention pin is separated from the shielding member, the shielding member rotates to start the deployment of the glide wing module.

According to an embodiment of the present invention, the deployable glide wing device may further include a partition wall partitioning the storage space into a first storage space and a second storage space, And a second inner wing hole communicating with the second receiving space, wherein the glide wing module includes: an inner wing hole having a first inner wing hole and a second inner wing hole communicating with the second receiving space, And a second glide wing module stacked on the second storage space and being expanded through the second internal wing hole, wherein the first glide hole, the first glide hole, and the first glide hole The wing module may have a shape symmetrical to the second receiving space, the second wing hole, and the second wing wing module with respect to the center point of the receiving space.

The projectile having the deploying type glide wing device according to the embodiment can perform gliding flight with only a small energy consumption by developing the glide wing module after reaching the target altitude.

According to the embodiment, the plurality of wing cartridges are vertically stacked in the direction in which the wing cartridges are deployed, and are compactly accommodated in the upper and lower sides respectively inside the wing case. Therefore, the volume of the wing wing module The ratio can be set large.

According to the wing adjustment cartridge according to the embodiment, the horizontal angle of the glide blades can be adjusted according to the atmospheric environment and the glide flight distance during flight of the projectile.

According to the deployable glide wing device according to the embodiment, since the expansion of the wing cartridge and the angle adjustment of the glide wing module can be performed only by the rotation of the conveying wheel, the operation configuration is simple and the volume of the drive system can be reduced.

According to the filler according to the embodiment, since the deployment of the glide-wing module can be guided and can be removed after the glide-wing module is deployed, the weight of the projectile can be reduced when the projectile glides over, It is possible to reduce the drag in the wing module and increase the lift.

According to the wing fitting according to the embodiment, the wing blade module is separated before deployment and can be automatically engaged while performing the deployment.

1 is a perspective view of a projectile including a glide wing module according to one embodiment.
Figure 2 is a perspective view of a glide wing device according to one embodiment shown cut along II and II-II.
3 is an exploded perspective view of a projectile according to one embodiment.
4 is a front view of a wing case according to an embodiment.
5A is a perspective view of a glide wing module according to an embodiment.
5B is an exploded perspective view of a wing cartridge according to an embodiment.
6 is a front view of a glide-and-landing apparatus according to an embodiment.
7 is a front view of a glide-and-landing apparatus according to an embodiment.
8 is a perspective view of a wing adjustment cartridge according to an embodiment.
9 is a block diagram of a glider according to an embodiment.
10 is a plan view of a wing coupling according to an embodiment.
11 is a plan view showing a state in which a wing coupling according to an embodiment is coupled.
FIG. 12 is a perspective view showing a deployed glide wing module according to an embodiment. FIG.
FIG. 13 is a diagram illustrating a flight process of a projectile having a glide-and-landing device according to an embodiment.

Hereinafter, embodiments will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments, detailed description of known functions and configurations incorporated herein will be omitted when it may make the best of an understanding clear.

In describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected," "coupled," or "connected. &Quot;

The components included in any one embodiment and the components including common functions will be described using the same names in other embodiments. Unless otherwise stated, the description of any one embodiment may be applied to other embodiments, and a detailed description thereof will be omitted in the overlapping scope.

FIG. 1 is a perspective view of a projectile including a glider according to an embodiment, FIG. 2 is a perspective view of a glide blade device according to an embodiment cut along the section II and II-II, FIG. 3 is an exploded perspective view of a glide-and-landing apparatus according to an embodiment.

1 to 3, a projectile 2 according to an embodiment is configured such that after reaching a target altitude through a deployable glide-and-landing apparatus 100 provided therein, a glide blade module 1 is deployed at least The energy of the fly can fly.

For example, the projectile 2 includes a bullet-proof portion having a peak shape as a front portion of the projectile 2, a body portion 21 forming a body extending elongated from the bulletproof portion, (23).

For example, the body portion 21 may have a circular cross-section, and a cylindrical internal space may be formed therein. For example, the body portion 21 may include an outer wing hole 24 formed on both sides of the body portion 21 and a deployable glide wing device 100 accommodated in the inner space of the body portion 21 .

For example, the two outer wing holes 24 disposed on both sides of the body portion 21 may be formed symmetrically with respect to the center point of the circular cross section of the body portion 21.

For example, an outer wing hole 24 (i.e., an outer wing hole 24 formed in the negative y-axis direction) located on the right side in the traveling direction of the projectile 2 among the two outer wing holes 24 An outer wing hole 24 formed in the right side in the traveling direction of the projectile 2, that is, an outer wing hole 24 formed in the positive y-axis direction, which can be referred to as a first outer wing hole 24a, 2 outer wing hole 24b.

For example, the deployable glide wing device 100 may be disposed in the interior space of the body portion 21. The glide wing module 1 provided in the deploying glide wing device 100 may be deployed to the outside through the outer wing hole 24 when gliding flight of the projectile 2 is performed.

For example, the glide wing module 1 may be vertically provided in the inner space of the deploying glide wing device 100 and may be deployed horizontally through the outer wing holes 24 on both sides of the projectile 2 . The specific configuration of the deploying glide vane apparatus 100 will be described later with reference to Figs. 4 to 9.

The tail portion 23 may be provided with a plurality of adjustable blades capable of adjusting the rotation and the flying direction of the projectile 2.

FIG. 4 is a front view of a wing case according to an embodiment, FIG. 5A is a perspective view of a glide wing module according to an embodiment, FIG. 5B is an exploded perspective view of a wing cartridge according to an embodiment, FIG. 7 is a front view of a glide wing device according to an embodiment, FIG. 8 is a perspective view of a wing adjustment cartridge according to an embodiment, and FIG. 9 is a front view of a glide wing device according to an embodiment. Fig.

Referring to FIGS. 4 to 9, the specific configuration of the deploying type glide blade apparatus 100 can be confirmed.

The deployable glide wing device 100 according to one embodiment may include a wing case 4, a gliding wing module 1, a deployment device 3, and a control unit 18.

The wing case 4 may be a case that accommodates the glide wing module 1, the expansion device 3, and the control unit 18 in the internal space. For example, the wing case 4 may be formed in a cylindrical shape along the inner space of the body portion 21 of the projected body 2 formed into a cylindrical shape.

For example, the wing case 4 may include a receiving space 41, a partition wall 43, an inner wing hole 42, a conveying wheel rotating hole 45, and a wing adjusting hole 44.

The storage space 41 may be a space formed inside the blade case 4 and can accommodate the glide blade module 1. [ For example, the storage space 41 can be partitioned into two storage spaces 41 in the vertical direction. For example, the storage space 41 formed on the upper side can be referred to as a first storage space 41a, and the storage space 41 formed on the lower side can be referred to as a second storage space 41b. For example, the first accommodating space 41a and the second accommodating space 41b are symmetrical up and down and left and right with respect to the center point when the vane case 4 is viewed from the front (x-axis direction) As shown in FIG.

For example, the glide wing module 1 housed in the first receiving space 41a has a first outer wing hole 24a formed in the right side (negative y-axis direction) with respect to the traveling direction of the projectile 2 And the second glide wing module 1 accommodated in the second accommodation space 41b can be horizontally deployed to the outside through the second outer wing hole 41b formed in the left side portion (positive y-axis direction) with respect to the traveling direction of the projectile 2, And can be expanded horizontally to the outside through the opening 24b.

Hereinafter, the storage space 41 will be described with reference to the second storage space 41b for the sake of explanation and understanding. In the present specification, the description of the storage space 41 and the features disclosed in the drawings are made in the first storage space 41a and the second accommodating space 41b, respectively.

The partition wall 43 may be formed to cross the inner space of the vane case 4 and divide the space formed therein into the first storage space 41a and the second storage space 41b. For example, the partition wall 43 may be arranged to horizontally cross the center of the inner space of the wing case 4. [

The inner wing holes 42 are communicating with the storage space 41 and the outer wing holes 24 formed on both sides of the body portion 21 as holes formed symmetrically to both sides of the wing case 4. The two glide wing modules 1 accommodated in the storage space 41 can be expanded horizontally to the outside of the projectile 2 through the inner wing hole 42 and the outer wing hole 24.

For example, the first inner wing hole 42a and the second inner wing hole 42b may be formed symmetrically with respect to the center point of the wing case 4.

For example, the inner wing hole 42 may be referred to as a first inner wing hole 42a, and an inner wing hole 42 formed in the right side (negative y-axis direction) with respect to the traveling direction of the projectile 2 And the inner wing hole 42 formed in the left portion (positive y-axis direction) can be referred to as a second inner wing hole 42b.

The wing adjustment hole 44 may be a hole formed in the inner wall of the accommodation space 41 of the wing case 4 in the front-rear direction of the projectile 2. For example, when the wing adjustment cartridge 114 is opened, the wing adjustment hole 44 is closed by the blade adjustment shaft 1141, which is compressed inside the wing adjustment cartridge 114, It can be inserted in a protruding manner.

The glide wing module 1 can be stacked and accommodated in the vertical direction in the storage space 41. The glide wing module 1 can be received and projected through the inner wing hole 42 and the outer wing hole 24 2) can be horizontally expanded outward.

For example, the glide wing module 1 can be accommodated in the first accommodating space 41a and the second accommodating space 41b, respectively. For example, the glide wing module 1 accommodated in the first storage space 41a can be referred to as a first glide wing module 1a and the glide wing module 1 accommodated in the second storage space 41b can be referred to as a first glide wing module 1a. Can be referred to as a second glide wing module 1b.

For example, the first glide wing module 1a may be deployed from the right side of the projectile 2 through the first inner wing hole 42a and the first outer wing hole 24a, The wing module 1b may be deployed from the left side of the projectile 2 through the second inner wing hole 42b and the second outer wing hole 24b. For example, the first glide wing module 1a and the second glide wing module 1b may be simultaneously deployed in the same order.

For example, the first glide wing module 1a and the second glide wing module 1b may be formed symmetrically with respect to the center point of the cylindrical wing case 4. In this case, the first glide wing module 1a and the second glide wing module 1b may have the same configuration, and the operating directions of the first glide wing module 1a and the second glide wing module 1b may be cylindrical May be symmetrical with respect to the center of the wing case (4).

Description will be given of the glide wing module 1, the storage space 41, the inner wing hole 42 and the outer wing hole 24 based on the configuration and position of the second glide wing module 1b for the convenience of the description of the present invention and for convenience of illustration. And the description of the glide wing module 1 and the features described in the drawings will be applied to the first glide wing module 1a and the second glide wing module 1b in the present specification .

For example, the glide wing module 1 may include a plurality of wing cartridges 11.

For example, the plurality of wing cartridges 11 may be stacked and arranged in a plurality of layers in the storage space 41. For example, the plurality of wing cartridges 11 may be arranged in the inner wing holes (not shown) of the plurality of wing cartridges 11 by the rotation of the conveying wheel 31 of the deploying device 3, 42 in succession from the wing cartridges 111 in the "deployment direction ".

Here, the expansion direction may mean a direction in which each of the glide wing modules 1a and 1b protrudes and unfolds to the outside of the projectile 2, respectively.

Although the number of the plurality of blade cartridges 11 is assumed to be four as shown in FIGS. 5A to 7, the number of the plurality of blade cartridges 11 is not limited thereto, and the number of the plurality of blade cartridges 11 ) May be composed of any number.

For example, the plurality of wing cartridges 11 may include a first wing cartridge 111, a second wing cartridge 112, a third wing cartridge 113, and a fourth wing cartridge 114.

The first wing cartridge 111 is a wing cartridge 111 that is disposed closest to the center of the wing case 4 and the inner wing hole 42 in the storage space 41 of the plurality of wing cartridges 11 have. The first wing cartridge 111 can also be deployed first among the plurality of wing cartridges 11 when the glide wing module 1 is deployed by the transport wheel 31.

For example, the first wing cartridge 111 may be longer in the horizontal direction than the remaining wing cartridges 112, 113, 114. 6, the first wing cartridge 111 can be positioned in contact with the conveying wheel 31 even if the conveying wheel 31 is positioned apart from the remaining wing cartridges 112, 113, 114 in the unfolding direction So that development by the conveying wheel 31 is possible.

The second wing cartridge 112 and the third wing cartridge 113 may be sequentially stacked from the first wing cartridge 111 and the second wing cartridge 112 may be sequentially stacked on the conveying wheel 31 The second wing cartridge 112 can be moved to the " deployed position " according to the stacking order, and then the third wing cartridge 113 can be moved to the deployed position and deployed.

Here, the "deployed position" may be a position that is aligned with the inner wing hole 42 in the horizontal direction immediately before the glide wing module 1 is deployed. In other words, the deployed position is such that the wing cartridge 11 closest to the center of the wing case 4 in the accommodating space 41, in order to deploy one wing cartridge 11 of the plurality of wing cartridges 11 to the outside of the projectile 2 That is, a position that is disposed to abut the partition wall 43. [

For example, the second wing cartridge 112 and the third wing cartridge 113, i.e., the first wing cartridge 111 and the last deployed wing cartridge 114, which are initially deployed among the plurality of wing cartridges 11, The wing cartridges 112 and 113 disposed and deployed in the middle can be referred to as "intermediate wing cartridges ".

The fourth wing cartridge 114 may be a wing cartridge 114 that is spaced farthest from the center of the wing case 4 of the plurality of wing cartridges 11, .

For example, the fourth wing cartridge 114, that is, the blade cartridge 114 finally deployed among the plurality of wing cartridges 11, may be referred to as a "wing adjustment cartridge 114 ".

For example, after the deployment of the glide wing module 1 is completed and the development of the fourth wing cartridge 114 is completed, at least a part of the fourth wing cartridge 114 is inserted into the interior of the wing case 4, And the horizontal angle of the glide wing module 1 can be adjusted by being disposed rotatably with respect to the wing case 4.

For example, the wing adjustment cartridge 114 may include a wing adjustment shaft 1141 and a wing adjustment gear 1142.

The wing adjustment shaft 1141 can be accommodated in the wing adjustment cartridge 114 and can be protruded to the outside of the wing adjustment cartridge 114 by the pressure of a spring provided inside the wing adjustment cartridge 114 A rotary shaft or a shaft. For example, the wing adjustment shaft 1141 may be provided at the opposite end of the wing adjustment cartridge 114 in the direction of deployment, and the direction of movement (x-axis direction) of the projectile 2 at the end of the wing adjustment cartridge 114, As shown in FIG.

For example, the length in the front-rear direction of the wing cartridge 11 may be equal to the length between the inner walls in the front-rear direction of the storage space 41. [ The wing adjustment shaft 1141 is inserted into the wing adjustment cartridge 114 by the inner wall of the storage space 41 before the wing adjustment cartridge 114 is deployed to compress the spring provided therein In this case, the wing adjustment shaft 1141 can be pressurized by the spring in the outward direction of the wing adjustment cartridge 114.

For example, the wing adjustment shaft 1141 may be inserted into the wing adjustment hole 44 formed symmetrically on both sides of the wing case 4 after the wing adjustment cartridge 114 is deployed. When the wing adjustment cartridge 114 is moved to the deployed position, the wing adjustment shaft 1141 compressed in the wing adjustment cartridge 114 is guided by the wing adjustment holes 44 formed in the front and rear inner walls of the accommodation space 41, It can be inserted into the blade adjusting hole 44 by the restoring force of the spring. In this case, the wing adjustment cartridge 114 can be rotatably fixed to the wing case 4 on the wing adjustment shaft 1141 inserted into the wing adjustment hole 44.

The wing adjustment gear 1142 may be formed on the surface of the end portion which is rounded opposite to the developing direction of the wing adjustment cartridge 114. For example, the wing adjustment gear 1142 can be engaged with the feed pinion 311 of the feed wheel 31 after the wing adjustment cartridge 114 is moved to the deployed position, and the feed wheel 31 is rotated The wing adjustment cartridge 114 can be rotated about the wing adjustment shaft 1141. [

According to the wing adjustment cartridge 114, the horizontal angle of the glide blade module 1 can be adjusted according to the atmospheric environment during flight of the projectile 2 and the glide flight distance.

For example, the plurality of wing cartridges 11 may each include an inner wing 12, a pillar 15, and a wing coupling 16.

The inner wing 12 may be a wing for which the projectile 2 actually performs flight in flight. For example, the inner wing 12 may be formed in a streamlined outer surface to reduce drag during flight soar of the projectile 2 and increase lifting force.

For example, the inner wing 121 of the first wing cartridge 111 can be referred to as a first inner wing 121, and similarly, the inner wing 12 of the second to fourth wing cartridges 112, 113, ) It is also possible to refer to the second to fourth inner vanes 122, 123 and 124.

For example, the inner vane 12 may include an inner passageway 13 formed along the deployment direction, and the inner passageway 13 may be provided with a vane coupling port 16. [

For example, one of the wing cartridges 11 of the plurality of wing cartridges 11 is deployed, and the wing cartridge 11 to be developed next moves to the deployed position in the accommodating space 41, 11 are in face-to-face contact with each other in the face facing the direction of deployment, the respective internal passages 13 can communicate with each other.

For example, the inner passage 13 may be formed in a bent state so as to coincide with the curved outer shape of the vane coupling member 16, and a part of the vane coupling member 16 is fixed on the inner passage 13 . The specific configuration of the vane coupling member 16 will be described later with reference to FIGS. 10 to 12. FIG.

The filler 15 may be formed so as to surround at least one surface of the outer surface of each inner vane 12. For example, the filler 15 may be engaged with the inner wing 12 to guide horizontal movement of the inner wing 12 in the unfolding direction.

For example, the filler 15 may be attached and fixed to the inner wing 12 before the plurality of wing cartridges 11 are deployed, but the plurality of wing cartridges 11 may be deployed to the outside of the projectile 2 , It can be separated during flight by the drag force of air generated during flight.

For example, the filler 15 may be formed of two members covering the upper side and the lower side of the inner vane 12 in the direction perpendicular to the direction of deployment of the plurality of vane cartridges 11. In this case, the upper member can be referred to as an upper filler 15a, and the lower fan can be referred to as a lower filler 15b. At least one side of the upper pillar 15a and the lower side pillar 15b may be in contact with each other, and a tooth structure 152 may be formed on one side to be engaged with each other in a developing direction.

According to the above structure, when the wing cartridges 11 are moved and developed in the unfolding direction or the horizontal direction, the upper and lower pillars 15a and 15b are separated by the sawtooth structure 152 engaged with each other in the unfolding direction And since the direction of the drag force of the air applied to the two pillars 15 after the wing cartridge 11 is developed is perpendicular to the developing direction, the two pillars 15 can be separated during flight.

For example, the filler 15 can form an outer shape of a wing cartridge 11 having a hexahedron shape by covering the inner wing 12 whose outer surface is formed in a streamlined shape.

For example, the filler 15 may be removably attachable to the inner wing 12. Specifically, when the glide wing module 1 is accommodated in the storage space 41, the filler 15 is fixed to the inner wing 12, and the wing cartridge 11, including the inner wing 12, Can be performed. After the wing cartridge 11 is deployed outside the projectile 2, the filler 15 may be removed from the inner wing 12 by the drag of the glide wing module 1 and separated from the air.

For example, the coupling between the filler 15 and the inner wing 12 can be achieved by a combination of protrusions and grooves 17 formed in the faces facing each other. For example, one of the protrusions 17b and the groove 17a may be formed on one surface of the filler 15, and the other surface of the inner blade 12 contacting the filler 15 may be compactly formed And the remaining one of the projection 17b and the groove 17a may be formed. 5b, grooves 17a and protrusions 17b are formed between the inner vane 12 and the lower pillar 15b. Alternatively, the positions of the grooves 17a and the protrusions 17b may be reversed And grooves 17a and protrusions 17b may be formed between the inner wings 12 and the upper filler 15a.

For example, the shapes of the protrusions 17b and the grooves 17a formed in the pillars 15 and the inner wings 12 may be formed by vertically bending at least a part of each of the one faces facing the expansion direction And one surface of the side opposite to the traveling direction of the projectile 2 may be formed to be inclined in the traveling direction of the projectile 2.

According to the above structure, when the wing cartridge 11 is moved in the unfolding direction by the conveying wheel 31, the projections 17b and the grooves 17a formed in the inner wings 12 and the pillars 15, The internal wings 12 and the pillars 15 may not be separated from each other.

The projections 17b and the grooves 17a formed in the inner wings 12 and the pillars 15 are formed by the drag force in the direction perpendicular to the deploying direction to the pillars 15 after the wing cartridges 11 are deployed. By the sloped surfaces in each, the filler 15 can be slipped in the inner wing 12 and separated from the inner wing 12 and dropped off.

The pillars 15 may include a conveyance rack 151 formed on the outer surface. For example, the feed rack 151 may be a gear portion formed on one surface of the pillar 15. [ For example, the conveyance rack 151 may be elongated along the expansion direction on the surface of the pillar 15 facing the center of the blade case 4. For example, the conveyance racks 151 may be formed on one side of the pillars 15 in pairs at both side edge portions of the pillars 15 along the developing direction.

For example, the feed rack 151 can be engaged with the gear portion of the feed pinion 311 of the feed wheel 31, which will be described later. Accordingly, as the feed wheel 31 rotates, the wing cartridges 11 including the pillars 15 can be moved horizontally by a rack and pinion method.

For example, the filler 15 may be detached from the inner vane 12 due to the drag force of air generated when the glide flight module 1 is deployed, and may be separated from the air after the deployment of the glide module 1. In this case, A plurality of inner wings 12 having a shape can be exposed to the outside to perform glide flight.

The weight of the projectile 2 can be reduced and at the same time the streamlined inner wing 12 is exposed to the outside so that the flying around the wing wing module 1 The drag force by the air of the projectile 2 can be reduced and the lift force can be increased, so that the flight ability of the projectile 2 can be improved.

The wing coupling 16 may be disposed in the inner passage 13 of the inner wing 12. For example, the wing coupling 16 may be provided in each of the plurality of wing cartridges 11 so that when a plurality of wing cartridges 11 are deployed in the horizontal direction, a plurality of wing cartridges 11 or a plurality of As the inner wings 12 can be coupled to each other, the horizontal connection between the plurality of inner wings 12 can be supported and fixed.

The specific configuration of the vane coupling member 16 will be described later with reference to FIGS. 10 to 12. FIG.

The expansion device 3 can expand the glide-wing module 1 to the outside. Specifically, the expansion device 3 can sequentially expand the plurality of wing cartridges 11 stacked in the vertical direction through the inner wing hole 42 and the outer wing hole 24.

For example, the deployment device 3 may include a transfer wheel 31, a torsion spring 32, a leaf spring 33, and an escape prevention device 34.

The feed wheel 31 may be a circular shaft rotatably provided in the housing space 41 with respect to the wing case 4. [ For example, the conveying wheel 31 can perform the horizontal development of the glide wing module 1 by moving the wing cartridge 11 in the developing direction.

For example, the conveying wheel 31 may be a rotary shaft rotatably connected to the front and rear inner walls of the receiving space 41 in accordance with the traveling direction of the projectile 2. For example, the conveying wheel 31 may be rotatably installed in a conveying wheel rotating hole 45 formed symmetrically to the inner and outer walls of the receiving space 41, as shown in Fig.

For example, the conveying wheel 31 may be positioned adjacent to the inner wing hole 42. [ For example, the conveying wheel 31 can be disposed inside a space formed in one surface of the partition wall 43 so that when the blade cartridge 11 and the partition wall 43 are moved to the extended position where they are in surface contact with each other, The gear portion of the conveyance rack 151 of the wing cartridge 11 and the gear portion of the conveyance pinion 311 of the conveyance wheel 31 may be placed on the same vertical position with respect to each other.

For example, the conveying wheel 31 may include a conveying pinion 311. The feed pinion 311 may be a gear portion formed along the periphery of the feed wheel 31. The feed wheel 31 can be engaged with the feed rack 151 formed on the outer surface of the pillar 15 and as the feed wheel 31 rotates, the feed pinion 311 rotates to rotate the feed rack 151 horizontally Direction.

According to the above structure, by the rotation of the conveying wheel 31, the wing cartridge 11 can be moved to the outside of the projectile 2 through the inner wing hole 42 and the outer wing hole 24, have.

For example, the rotation of the feed wheel 31 can be performed through a prime mover such as a motor provided inside the wing case 4, and the rotational operation can be controlled by the control unit 18, which will be described later.

For example, the feed wheel 31 may engage with the wing adjustment gear 1142 of the wing adjustment cartridge 114 to rotate the wing adjustment cartridge 114. [ For example, after the third wing cartridge 113 has been deployed, that is, after the wing cartridge 113 that has been stacked against the wing adjustment cartridge 114 has been deployed first, the wing adjustment cartridge 114 is moved to the deployed position And after the wing adjusting cartridge 114 and the wing fittings 16 of the third wing cartridge 113 are connected to each other, the feeding wheel 31 is rotated to start the deployment of the wing adjusting cartridge 114 have.

As the feed wheel 31 rotates, the wing adjustment cartridge 114 moves in the horizontal direction and the wing adjustment shaft 1141, which is accommodated and compressed at both sides of one end of the wing adjustment cartridge 114, The blade adjusting shaft 1141 can be inserted into the blade adjusting hole 44 while the blade adjusting gear 1142 can be engaged with the feeding pinion 311. [

According to the above structure, the wing adjustment cartridge 114 can be rotatably fixed about the wing adjustment shaft 1141 and the angle of the wing adjustment cartridge 114 can be adjusted through the rotation of the feed wheel 31 .

The torsion spring 32 is installed in a plurality of sections on the side of the inner wall of the storage space 41 and applies a vertical pressure to the wing case 4 in the direction toward the partition wall 43 to the wing cartridges 11 . For example, the torsion spring 32 may be installed on the side wall of the receiving space 41 corresponding to the height of each of the plurality of wing cartridges 11 stacked.

For example, the torsion springs 32 are provided on a pair of opposing side walls of the storage space 41 to grip both sides of the wing cartridge 11 so as to press the wing cartridges 11 in the direction toward the deploying position .

According to the torsion spring 32, after the wing cartridge 11 in the deployed position is moved in the horizontal direction by the conveying wheel 31, the vertical pressure Can be applied.

The leaf spring 33 may be installed on the inner wall of the inner space of the storage space 41, facing the partition wall 43. For example, the leaf spring 33 can be brought into contact with the storage space 41 with the glide wing module 1, and more specifically, with the fourth blade cartridge 114, that is, on one surface of the blade adjustment cartridge 114 A vertical pressure can be applied so that the plurality of wing cartridges 11 can move to the deployed position.

The separation preventing device 34 is installed in the inner wing hole 42 of the wing case 4 to prevent the wing blade module 1 from being deployed. For example, the escape prevention device 34 may include a shielding member 341 and an escape prevention pin 342.

The shielding member 341 may be rotatably installed at a portion adjacent to the inner wing hole 42 and may contact the end of the first wing cartridge 111 to fix the first wing cartridge 111. For example, the shielding member 341 may have a torsional elastic body, such as a torsion spring, which exerts a torque in a direction deviating from the position of shielding at least part of the inner wing hole 42, that is, in an outward direction.

The release preventing pin 342 is provided adjacent to the shielding member 341 in the inner wing hole 42 so that the shielding member 341 can be fixed at a position where it shields a part of the inner wing hole 42. [ And may be a pin-shaped member formed to penetrate a part of the member 341.

When the separation preventing pin 342 is separated from the shielding member 341, the shielding member 341 is rotated in the outward direction by the torsion elastic body, so that the fixing of the first wing cartridge 111 can be released, The development of the wing module 1 can be started. For example, the departure prevention pin 342 may include a solenoid device capable of fixing and releasing the shielding member 341 through an electrical signal.

According to the departure prevention device 34, the glide wing module 1 is released to the outside of the projectile 2 by the impact due to the backward inertia force generated when the projectile 2 is fired and the centrifugal force due to the rotation of the projectile 2 And the deployment of the glide wing module 1 can be started by separating the departure prevention pin 342 at a time when the rotation of the projectile 2 is stopped and the glide flight is required.

For example, the expansion device 3 including the transfer wheel 31, the torsion spring 32, and the leaf spring 33 is disposed in the first storage space 41a and the second storage space 41b, respectively, , And may be installed at positions symmetrical to each other with respect to the center point of the wing case (4).

According to the above structure, since the first conveying blade module 1a and the second conveying blade module 1b can be deployed at the same time while the two conveying wheels 31 are rotated in opposite directions to each other, 31 can be offset from each other.

The first glide wing module 1a and the second glide wing module 1b are provided by the torsion spring 32 and the leaf spring 33 disposed in the first storage space 41a and the second storage space 41b. In the process of developing the glide wing module 1, since the force and the torque due to the impact generated when the wing cartridges 11 of the wing cartridges 11 move to the opposite directions, that is, to the respective deployed positions, Unnecessary force and torque can be prevented from being generated inside the projectile 2.

The control unit 18 can determine the point at which the glide flight should be performed by sensing the movement and the altitude of the projectile 2 measured by the sensor unit 19 provided inside the glide blade module 1. [ For example, the sensor unit 19 may include an altitude sensing sensor 191 capable of sensing the flight altitude and a rotation sensing sensor 192 capable of sensing the rotation of the launch vehicle 2.

For example, when the control unit 18 reaches the target altitude at which the rotation of the projectile 2 is canceled and the glide flight is to be performed, the control unit 18 controls the release prevention pin 342 to the shielding member 341 to release the fixing of the first wing cartridge 111. [

The controller 18 controls the prime mover to rotate the conveyance wheel 31 to rotate the conveyance wheel 31 so that the plurality of wing cartridges 11 are rotated to the outside of the projectile 2 After the wing cartridges 11 are completely deployed, the rotation speed and direction of the conveying wheel 31 are controlled to rotate the wing adjustment cartridge 114 so as to rotate the wing hole 24, The angle of the wing module 1 can be adjusted.

FIG. 10 is a plan view of a wing coupling according to an embodiment of the present invention, FIG. 11 is a plan view showing a coupling of a wing coupling according to an embodiment, and FIG. 12 is a view FIG.

10 to 12, a wing coupling 16 according to an embodiment is accommodated in the inner passage 13 of the plurality of wing cartridges 11, and when the wing cartridges 11 are deployed, The horizontal connection between the plurality of wing cartridges 11 can be fastened.

For example, the vane coupling member 16 may include a fixture 163, a coupling guide bar 161, a plate slider 162, and an elastic body 164.

The fixture 163 can be disposed in the inner passage 13 and can be located adjacent to the inlet portion of the portion opposite the deployment direction on the inner passage 13. [ For example, the fixture 163 may include an engagement groove 1631. [

The engaging groove 1631 may be a recess formed in a direction perpendicular to the developing direction. For example, the engaging groove 1631 can be engaged with the plate slider 162 provided in the wing cartridge 11, which is developed in the following order of the wing cartridge 11 having the corresponding engaging groove 1631.

For example, the wing coupling 16 provided in the fourth wing cartridge 114, i.e., the wing cartridge 114 that is finally deployed, may not include the fastener 163.

The coupling guide bar 161 may be a pair of guide members extending from the internal passage 13 along the direction of deployment. For example, the engaging guide bar 161 may be connected from the fixture 163 and extend in the unfolding direction. On the other hand, one end of the coupling guide bar 161 can be fixed to the inner wall of the inner passage 13.

The plate slider 162 may be a plate member connected to the coupling guide bar 161 and capable of sliding along the expansion direction. For example, the plate slider 162 may include a hook portion 1621.

The hook portion 1621 may be a hook-shaped end protruding from the plate slider 162 in the extending direction. For example, the hook portion 1621 can be coupled to the coupling groove 1631 provided in the wing cartridge 11 developed before the wing cartridge 11 having the hook portion 1621.

For example, when the plate slider 162 is moved to the end of the engagement guide bar 161 in the unfolding direction, at least a part of the hook portion 1621 can protrude outside the inner wing 12. In other words, the hook portion 1621 can be inserted into the internal passage 13 of the previously developed wing cartridge 11.

For example, the wing coupling 16 provided in the first wing cartridge 111, that is, the wing cartridge 111 that performs the first deployment, may not include the plate slider 162.

The elastic body 164 is disposed between the fixture 163 and the plate slider 162 and can be compressed when the plate slider 162 is housed in the inner passage 13, The restoring force can be applied.

For example, the elastic body 164 may be a spring arranged in pairs in accordance with the coupling guide bar 161. [ For example, one end of the elastic body 164 may be fixed to one side of the coupling guide bar 161, and the other end may be fixed to the end of the plate slider 162. On the other hand, one end of the elastic body 164 may be fixed to the inner wall of the inner passage 13.

For example, the shape of the inner passage 13 may be formed by bending the outer shape of the vane fixture 163 to conform to the curved shape as shown in Figs. 8 and 9. [ For example, the outer shape and the cross-sectional area of the inner passage 13 can be formed identically at both end portions of the inner passage 13 where the fixture 163 and the plate slider 162 are disposed, The cross-sectional area of the inner passage 13 at the portion where the coupling guide bar 161 connected between the sliders 162 is disposed can be made small. According to the above structure, the wing fixture 163 may not rotate and move in any direction except the expansion direction, and may be arranged compactly inside the inner wing 12.

Referring to FIG. 8, the coupling structure of the blade coupling member 16 can be confirmed. Although the coupling structure of the vane coupling 16 is illustrated through the first inner vane 121 and the second inner vane 122 for convenience of illustration, it may be applied to any inner vane 12 in common It should be understood.

For example, the length of the width in the developing direction in the wing cartridges 11 and the inner wings 12 may be set to be shorter than the length of the accommodating space 41 in the developing direction of the accommodating space 41, It may be the same as the distance between the inner walls.

According to the above structure, when the wing cartridge 11 is accommodated in the accommodating space 41 before the wing cartridge 11 is deployed, the plate slider 162 is protruded to the outside of the wing cartridge 11 by the inner wall of the accommodating space 41 And may be accommodated in the inner passage 13. In this case, the elastic body 164 is compressed and can apply a restoring force to the plate slider 162 in the unfolding direction.

For example, when the first wing cartridge 111 is horizontally moved by the transporting wheel 31 at the unfolding position and then a space is formed through which the second wing cartridge 112 can move on the unfolding position, 2 wing cartridge 112 can be moved to the deployed position by torsion spring 32 and leaf spring 33. [

The inner passage 13 of the second inner wing 122 is communicated with the inner passage 13 of the previously developed first inner wing 121 So that at least a portion of the plate slider 162, i.e., at least a portion of the hook portion 1621, is inserted into the inner passage 13 of the second inner wing 122, And can be fastened to the coupling groove 1631.

9 and 10, a plurality of wing cartridges 11 are sequentially deployed out of the projectile 2 in the horizontal direction, and at the same time, the respective wing cartridges 11, The respective vane engagement portions 16 provided in the inner rotor 12 are also coupled to each other in a sequential and cascade manner to thereby provide a fastening between the plurality of inner vanes 12

FIG. 13 is a diagram illustrating a flight process of a projectile having a glide-and-landing device according to an embodiment.

13, a projectile 2 including a deployable glide-and-landing apparatus 100 according to an embodiment is launched by the launching device 5, and the control unit 18 controls the rotation of the projectile at a predetermined set altitude When the rotational force and the centrifugal force are attenuated to disappear, the horizontal launch control of the projectile 2 can be performed (a).

When the escape prevention device 34 releases the securing of the glide wing module 1, the glide wing module 1 can be deployed through the external wing hole 24 formed symmetrically to the side of the projectile. (B) .

Thereafter, the projectile 2 can perform a glide flight by minimizing energy consumption by the glide wing module 1 that has been developed, (c)

Finally, after the gliding flight, the target 6 can be hit accurately (d).

Although the preferred embodiments of the present invention have been disclosed for illustrative purposes, those skilled in the art will appreciate that various modifications, additions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. For example, it is contemplated that the techniques described may be performed in a different order than the described methods, and / or that components of the described structures, devices, and the like may be combined or combined in other ways than the described methods, Appropriate results can be achieved even if they are replaced or replaced.

Therefore, other implementations, other embodiments and equivalents to the claims are within the scope of the following claims.

Claims (13)

A wing case having an accommodating space and an internal wing hole communicating with the accommodating space;
A glide blade module including a plurality of blade cartridges housed in the storage space and stacked in a vertical direction; And
And a deploying device for horizontally sliding the wing cartridges adjacent to the wing holes out of the plurality of wing cartridges to the outside of the inner wing holes sequentially,
Each of the plurality of blade cartridges comprising:
Inner wing with wired shape; And
And a filler having at least one surface of the inner wing and a feed rack formed thereon,
Wherein the expansion device comprises:
And a transfer wheel rotatably installed in the wing case, the transfer wheel having a transfer pinion engaged with the transfer rack for developing the plurality of wing cartridges.
delete The method according to claim 1,
Wherein the filler can be removed when the feed wheel is deployed out of the vane case.
The method according to claim 1,
Wherein the expansion device comprises:
Further comprising a plurality of torsion springs installed in the receiving space on each side of the plurality of blade cartridges and applying pressure to the plurality of blade cartridges in a direction perpendicular to a developing direction in which the plurality of blade cartridges are deployed A deployable glide wing device.
5. The method of claim 4,
Wherein the expansion device comprises:
Further comprising a leaf spring installed on an inner wall of the inner space facing the vertical direction of the inner space of the accommodating space and applying pressure in a direction perpendicular to the expanding direction in contact with the plurality of blade cartridges.

The method according to claim 1,
Each of the plurality of blade cartridges comprising:
Further comprising a wing coupling disposed in an inner passage formed in the inner wing and capable of coupling wing cartridges deployed through the inner wing holes and wing cartridges located within the storage space, .
The method according to claim 6,
The wing-
A fixture fixed to the internal passage;
A plate slider slidable in a direction in which the plurality of blade cartridges are deployed; And
And an elastic body disposed between the fixture and the plate slider.
8. The method of claim 7,
The fixture includes:
And an engaging groove recessed in a direction perpendicular to a direction in which the plurality of blade cartridges are deployed,
The plate slider
And a hook portion engageable with an engaging groove of a fastener of a wing fastener provided in another adjacent wing cartridge.
The method according to claim 1,
Wherein the plurality of blade cartridges
Further comprising a wing adjustment cartridge which is finally deployed among the plurality of wing cartridges to adjust the angle of the glide wing module.
10. The method of claim 9,
The storage space
And a pair of blade adjusting holes formed in the front and rear surfaces facing each other in a direction perpendicular to a direction in which the plurality of blade cartridges are deployed,
Wherein the wing-
Wherein the wing adjustment cartridge is provided inside the wing adjustment cartridge and protrudes in both forward and backward directions, and when the wing adjustment cartridge is deployed to the outside, the wing adjusting cartridge is in contact with the pair of wing adjusting holes and protrudes toward the pair of wing adjusting holes Wing adjustment shaft; And
And a wing adjustment gear formed around the one end of the wing adjustment cartridge and meshing with the feeding pinion of the feeding wheel,
Wherein the angle of the blade adjustment cartridge is adjusted as the conveying wheel rotates.
The method according to claim 1,
Wherein the expansion device comprises:
Further comprising a departure prevention device for preventing the glide wing module stored in the wing case from being released to the outside of the inner wing hole.
12. The method of claim 11,
The departure-
A shielding member rotatably installed at a portion of the vane case adjacent to the vane hole and capable of shielding at least a part of the vane hole;
A torsional elastic body applying torque in a direction deviating from a position at which the shielding member shields at least a part of the vane hole; And
And a release preventing pin for preventing rotation of the shielding member,
Wherein when the separation prevention pin is separated from the shielding member, the shielding member rotates to start the deployment of the glide wing module.
A wing case having an accommodating space and an internal wing hole communicating with the accommodating space;
A glide blade module including a plurality of blade cartridges housed in the storage space and stacked in a vertical direction; And
And a deploying device for horizontally sliding the wing cartridges adjacent to the wing holes out of the plurality of wing cartridges to the outside of the inner wing holes sequentially,
Further comprising a partition wall partitioning the storage space into a first storage space and a second storage space,
Wherein the inner wing hole includes a first inner wing hole communicating with the first storage space and a second inner wing hole communicating with the second storage space,
The glide wing module includes a first glide wing module stacked in the first storage space and developed through the first internal wing hole, and a second glide wing module stacked in the second storage space and expanded through the second internal wing hole 2 < / RTI > glide wing module,
The first accommodating space, the first wing hole, and the first glide wing module may have a shape symmetrical with the second accommodating space, the second wing hole, and the second glide wing module with respect to the center point of the accommodating space, A spreading glide wing device.

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