KR102081885B1 - Unfolding wings apparatus of folding blade - Google Patents

Abstract

A drive module having a worm wheel gear; A wing module connected to the worm wheel gear and having a first wing rotatably deployed or fixed, and a second wing hinged to the first wing; And a case accommodating the driving module and the wing module, wherein a slit-shaped wing hole is inserted into the projectile body symmetrically formed on the side surface, wherein the wing module has the first wing and the second wing folded vertically. The wing module of the pair provides a foldable wing deployment device characterized in that it is accommodated in a symmetrical structure.

Description

Unfolding wings apparatus of folding blade

The present invention relates to a foldable wing deployment device applicable to projectiles having a limited diameter.

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

The latest artillery has long guns, fast gun speed, long range, etc., and the accuracy of the shooting is improved by computerization of guns and automatic heat radiation. It is also adding power to the development of high-tech shells such as precision guided shells, mineslide shells, and scout shells.

In addition, there is a demand for precise control of the artillery's flight control, as well as how the projectile can fly with minimal energy to reach the long-range accurate target. Skill development is needed.

Korean Registered Patent No. 10-1356554 (Registration Date: 2014. 01. 22) Korean Patent Registration No. 10-0796706 (Registration Date: 2008. 01. 15)

The technical problem to be achieved by the present invention is to provide a foldable wing deployment apparatus of a projectile that can be accommodated inside the projectile for a limited size and conditions of the projectile, and furthermore a foldable wing deployment apparatus applicable to a projectile having a limited diameter The purpose is to provide.

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.

The present invention to solve the above problem is a drive module having a worm wheel gear; A wing module connected to the worm wheel gear and having a first wing rotatably deployed or fixed, and a second wing hinged to the first wing; And a case accommodating the driving module and the wing module, wherein a slit-shaped wing hole is inserted into the projectile body symmetrically formed on the side surface, wherein the wing module has the first wing and the second wing folded vertically. The wing module of the pair can be provided with a foldable wings deployment device characterized in that the storage in a symmetrical structure.

The vane module may include a vane rotating shaft which is vertically connected between the worm wheel gear and the first vane and performs rotation or fixing of the vane module.

The wing module may have a first wing horizontally rotated about the wing rotation axis to protrude to the outside of the projectile body through the wing hole, and with it, the second wing may be unfolded and spread out horizontally.

The case may include a guide structure for spreading wings in a region for receiving the second wings.

The first wing may have a protrusion to limit the unfolding angle range of the second wing at the end hinged to the second wing.

Foldable wing deployment device of the projectile according to an embodiment of the present invention can be accommodated inside the projectile for the limited size and conditions of the projectile, the wings can be deployed at a minimum altitude or a constant centrifugal force to enable the projectile to fly with minimal energy There is an advantage.

1 is a perspective view showing a projectile that deploys the wings of the folding wing deployment apparatus according to an embodiment of the present invention,
2 is a perspective view showing a folding wing deployment apparatus according to an embodiment of the present invention,
3 and 4 is an exploded perspective view of FIG.
5 is an exploded perspective view showing a drive module 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 projecting body deploying the wings of the foldable wings deployment apparatus according to an embodiment of the present invention, Figure 2 is a perspective view showing a foldable wings deployment apparatus according to an embodiment of the present invention, Figures 3 and 4 are 5 is an exploded perspective view of a driving module according to an embodiment of the present invention.

1 to 5, the projectile according to the embodiment of the present invention has a wing hole (H) formed symmetrically on the side of the body (10), and the foldable wing deployment device 30 protruding from the wing hole (H) It is provided. The length of the wing hole H may correspond to the total length L of the deployed wing. The steering wing 20 is located in the lanceal part of the projectile, the rotation and flight direction of the projectile can be controlled.

In order to increase the range of the projectile, wing shape and deployment point can be determined first according to the results of aerodynamic analysis and M & S. Through this, the size and shape of the wing that can achieve the target performance can be determined first. That is, the wing module deployment device 30 may be stored in a space defined for the size of the projectile.

The wing module deployment device 30 is connected to the drive module 33 for the deployment and fixing of the wing module 31, the drive module 33 may be provided with a worm wheel gear (33g). The worm wheel gear 33g rotates the worm 33w connected to the motor 33m, and the side threaded surface of the worm 33w and the side teeth of the worm wheel 33h come into contact with each other so that the worm wheel 33h rotates so that the worm wheel gear 33g is rotated. ) Can work. That is, the rotation axis of the worm 33w and the rotation axis of the worm wheel 33h may be perpendicular to each other.

The wing module 31 has a first wing 31a connected to the worm wheel gear 33g and rotated or deployed, and a second wing 31b hinged to the first wing 31a. In addition, the wing module 31 may include a wing rotation shaft 37 which is vertically connected between the worm wheel gear 33g and the first wing 31a and performs rotation or fixing of the wing module 31.

For example, the blade rotation shaft 37 is coupled through the center of the worm wheel 33h, the worm wheel gear (33g) connected to the motor 33m by operating the wing rotation shaft 37 is coupled through the worm wheel 33h is It can rotate in the same direction as the worm wheel 33h. Therefore, by inputting the operating time of the motor 33m or the number of revolutions of the worm wheel 33h into the flight control device, it is possible to accurately control the horizontal rotation angle of the wing when the blade is deployed, and to increase the reduction ratio of the worm wheel gear 33g to increase the torque. Can increase.

Furthermore, since the worm wheel 33h is driven only by the motor 33m, when the wing rotation shaft 37 is fixed after the wing deployment is completed, the worm wheel 33h is moved by the strong force of the motor 33m and the worm wheel gear 33g. It can be fixed firmly. Therefore, by providing the worm wheel gear 33g can be easy to secure the wings after the deployment and deployment of the wing module 31, it is possible to simplify the components provided for rotation deployment and fixing of the wing module 31 as one.

The motor 33m may be mounted to the drive module 33 in the same direction as the launching direction of the projectile to prevent damage due to the launching shock, and the rotational direction and the rotational rotational direction of the mounted motor may be the same. .

The case 35 accommodating the driving module 33 and the wing module 31 is inserted into the projectile body 10 in which a slit wing hole H is symmetrically formed on a side surface thereof. In this case, the wing module 31 may have a first wing 31a and a second wing 31b folded vertically to each other to receive a pair of wing modules in a symmetrical structure.

The case 35 may include a first case 35a and a second case 35b in which the second vane 31b is positioned to contact one side surface of the first vane 31a. The first case 35a is provided with an assembly protrusion 35a-1 on the outer surface of the first case 35a in contact with the inner surface of the projectile body 10, and an assembly groove provided in the inner surface of the body 10. 11). In addition, the first case 35a may include a driving module accommodating groove 35a-2 for accommodating the driving module 33.

The case 35 may include a guide structure 35b-1 for spreading the vane in an area for accommodating the second vane 31b, and furthermore, the guide structure 35b-1 is a second case 35b. It may be provided on the inner surface of the). The guide structure 35b-1 may be made of aluminum and may have a dry friction structure. That is, the second blade 31b is unfolded by the guide structure 35b-1 without the external driving force when the second blade 31b hinged around the first blade and the hinge axis X is unfolded. It can be deployed to protrude outward with the wing 31a.

The wing module 31 is protruded outwardly of the projectile body 10 through the wing hole (H) by the first wing 31a is horizontally rotated around the wing rotation shaft 37, the guide structure (35b-1) Due to the second wing 31b is unfolded and can be horizontally deployed to the outside with the first wing (31a).

The first wing 31a may have a protrusion 31a-1 at the end connected to the second wing 31b to limit the unfolding angle range of the second wing 31b. In addition, since the wing hole 11 overlaps the wing unfolded by the thickness of the body 10, the unfolded wing can be kept horizontal without being folded or folded by an external force.

A projectile having a foldable wing deployment device 30 as shown in FIGS. 1 to 5 may input a flight scenario to a flight control device located inside the projectile before launching. In order to increase the range, wing shape and deployment point can be determined first according to aerodynamic analysis and M & S results. Through this, the size and shape of the wing that can achieve the target performance can be determined first.

When the flight control device detects that the control blade is deployed at the time or altitude input to the flight control device after the launch of the projectile and the centrifugal force of the projectile is reduced by the control wing within the range of 100 to 250 rpm, the signal provided from the flight control device Due to the worm wheel gear (33g) of the foldable wings 30 drive module 33 starts to operate.

As the wing rotation shaft 37 connected to the worm wheel gear 33g rotates, the first wing 31a of the wing module 31 rotates horizontally and protrudes outside the projectile body 10 through the wing hole H. In addition, the second wing 31b hinged to the first wing 31a has an area folded vertically with the first wing 31a due to the guide structure 35b-1 of the case 35, and is horizontally deployed outside the projectile. do. When the horizontal development of the first blade 31a and the second blade 31b is completed due to the operating time of the motor 33m or the rotation speed of the worm wheel 33h previously inputted to the flight control device, the driving module 33 The operation of the motor 33m is stopped and the blade rotation shaft 37 is fixed by stopping the rotation of the worm wheel gear 33g connected thereto.

When the deployment of the wing is completed by the above process, it is possible to gliding toward the target point through satellite navigation and INS-based flight control.

If the deployment of the wing cannot be performed according to the input scenario or if a malfunction occurs during the deployment of the wing, the flight command may be repeated by the flight control device. At this time, when the projectile is directed to a place different from the target point because the foldable wing deployment device is not deployed, the flight control device may issue a suicide command to prevent damage.

Therefore, the foldable wing deployment apparatus according to the embodiment of the present invention can be accommodated inside the projectile for the limited size and condition of the projectile, and can be deployed at a target altitude or centrifugal force, and the projectile can be minimized by deploying the wing at a target altitude or a constant centrifugal force. There is an advantage to fly with the energy of.

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.

H; Wing hole, 30; Wing module deployment device,
31; Wing module, 33; Drive module,
35; Case, 35b-1; Guide Structure,
37; Wing shaft

Claims (5)

A drive module having a worm wheel gear;
A wing module having a first wing connected to the worm wheel gear and being rotated or fixed, and a second wing hinged to the first wing; And
A case including the driving module and the wing module, the case having a guide structure for spreading the wing in a region accommodating the second wing,
Slit-shaped wing hole is inserted into the projectile body formed symmetrically on the side, the wing module is characterized in that the first wing and the second wing is folded vertically to each other a pair of wing modules are accommodated in a symmetrical structure Foldable wing deployment device. The method of claim 1,
Wherein the wing module, the vertical wing is connected between the worm wheel gear and the first wing foldable wings, characterized in that it comprises a wing axis for rotating or fixing the wing module. The method of claim 2,
The wing module is foldable, characterized in that the first wing is rotated horizontally around the wing rotation axis to protrude out of the projectile body through the wing hole, and with it the second wing is unfolded and horizontally deployed to the outside. Wing deployment. delete The method of claim 1,
The first wing foldable wings, characterized in that provided with a protrusion for limiting the unfolding angle range of the second wing at the end hinged with the second wing.

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