KR101864088B1 - Apparatus for control fin of a projectile and control method thereof - Google Patents

Apparatus for control fin of a projectile and control method thereof Download PDF

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Publication number
KR101864088B1
KR101864088B1 KR1020170141395A KR20170141395A KR101864088B1 KR 101864088 B1 KR101864088 B1 KR 101864088B1 KR 1020170141395 A KR1020170141395 A KR 1020170141395A KR 20170141395 A KR20170141395 A KR 20170141395A KR 101864088 B1 KR101864088 B1 KR 101864088B1
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KR
South Korea
Prior art keywords
control
projectile
rotation
case
deployed
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Application number
KR1020170141395A
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Korean (ko)
Inventor
김용재
박민규
정수경
신승제
김재호
박장호
조창연
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국방과학연구소
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Priority to KR1020170141395A priority Critical patent/KR101864088B1/en
Application granted granted Critical
Publication of KR101864088B1 publication Critical patent/KR101864088B1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

Disclosed are a projectile control fin apparatus and a control method thereof. The projectile control fin apparatus comprises: a case coupled to one side of a main body of a projectile; a plurality of control fin units which are housed in a folded state in a casing and have a central rotary shaft coupled to the control fin and the control fin deployed after being fired; a plurality of gear box units connected to the central rotary shaft for rotationally driving the control fin about the central rotary shaft; and a control unit for controlling the plurality of gear box units.

Description

TECHNICAL FIELD [0001] The present invention relates to a control apparatus for a projectile,

The following description relates to a control blade of a projectile and a control method thereof.

The gun can be classified into a flat gun, a mortar, a howitzer, and a howitzer depending on the angle of the trajectory from which the shell is flying. Herein, the howitzer has a comparatively gentle curvature of the trajectory, and the length of the barrel is about 20 times as large as that of the caliper. Generally, the charge is not strong compared with the flatbed, and the weight of the cannel is relatively light.

The 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 howitzer has improved the precision of shooting by computerization of gunship, automatic heat dissipation, etc., and it is added by the development of high-tech shells such as mines shells and reconnaissance shells.

On the other hand, the projectile adopts various aerodynamic surfaces for the stability in forming the main body, and in order to reduce the volume of the projectile based on the way of loading and launching the projectile, the projectile has the components excluding the main body of the projectile, It is designed so that it can be expanded when necessary.

In order to reach the precise target point, the projectile needs to control the flight angle and flight distance of the projectile, and to control the flight attitude accordingly. In addition, when firing from a cannon using a concentric barrel, there is a problem that the barrel or wing is damaged due to the contact between the barrel and the folding wing, so development is required to prevent damage.

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 the present invention to provide a control apparatus and a control method for a control system that can control a precise attitude of a projectile by controlling a rise and a fall of a projectile by controlling the rotation of the projectile, And to provide a control blade of the projectile and a control method thereof.

It is another object of the present invention to provide a control device for a projectile of a projectile and a control method thereof, which can prevent the control blade from being damaged when the projectile is fired and the projectile being fired by the projectile.

A steering wing device for a projectile according to one embodiment will be described.

A control wing device of a projectile includes a case coupled to one side of a main body of a projectile, a plurality of control vanes having a control blade accommodated in the casing in a folded state and deployed after being fired and a central rotation shaft coupled to the control blade, A plurality of gear box parts connected to the central rotation shaft for rotationally driving the control vane about the central rotation axis, and a controller for controlling the plurality of gear box parts.

According to one aspect of the present invention, there is further provided a projectile rotation speed sensor for sensing a roll rotation speed of the projectile and a rotation axis angle sensor for sensing a rotation angle of the central rotation axis, The control unit controls the plurality of gear box units based on the information sensed by the rotation axis angle sensor to adjust the cant angle of the control wing in a direction to suppress the rotation of the projectile by the deployed control wing have.

According to one aspect of the present invention, the control unit can control the horizontal start of the projectile by independently driving each of the deployed control blades by controlling the plurality of gear box units.

According to one aspect, the plurality of gear box sections may include a worm wheel disposed along an outer circumferential surface of the central rotary shaft, and a worm gear module connected to the worm wheel to adjust a rotation angle of the central rotary shaft.

According to one aspect of the present invention, each of the plurality of control vanes may further include a vane rotation pin connecting the control vane and the central rotation axis in a hinge form.

According to one aspect of the present invention, the control vanes include two extending portions each extending from the one end portion and spaced from each other and fastened to both sides of the vane rotation pin, A fixing pin for fixing the control vane to the central rotation shaft, a pin groove formed in the center of one end in the longitudinal direction and receiving the fixing pin, and an elastic member for elastically supporting the fixing pin in the pin groove have.

According to one aspect of the present invention, the central rotation axis may include a control blade fixing groove formed to be recessed inward from a center of the one end and to which the fixing pin is coupled.

According to one aspect of the present invention, the projectile is arranged to surround the outer side of the control blade in a state that the projectile is launched from the concentric barrel and the control wing is housed in a folded state in the case, and the projectile is propelled in the concentric barrel And a protection cap for protecting the control blade from an impact caused by explosion of the propellant in the course of the operation.

According to one aspect, the control section can separate the protective cap from the case when the projectile is out of the barrel and reaches a set altitude.

According to one aspect, the protective cap may have a separation speed of 8 m / s to 20 m / s.

According to one aspect of the present invention, there is further provided a protective filler disposed between the control vane and the protection cap and being detached from the control vane when the protection cap is detached, in a state that the control vane is housed in the case in a folded state can do.

According to one aspect of the present invention, the case includes a case body, a plurality of control vane storage grooves radially recessed on an outer circumferential surface of the case body, and a plurality of control vane storage recesses formed in the case, And may include a gearbox receiving groove.

According to one aspect, the case may further include a module cover sealing the rear surface of the case body, a lock cap penetratingly coupled to the module cover, and a base hermetically sealing the front surface of the case body and coupled with the body of the projectile .

A control method of the steering wing apparatus according to one embodiment will be described.

A control method for a control wing apparatus includes a case, a projectile including a plurality of control blades housed in a folded state in the case, and a protective cap for preventing the plurality of control blades from being deployed, Separating the protective cap from the protective cap, developing the plurality of control vanes after the protective cap is detached, and controlling the rotation angle of the deployed plurality of control vanes.

According to one aspect of the present invention, the step of controlling the rotational angle of the deployed plurality of control vanes may include controlling the angle of rotation of the control vane by the deployed control vane in the direction of suppressing the rotation of the projectile, And damping the rotation of the rotor.

According to one aspect of the present invention, there may be included a step of independently driving the deployed control vanes after the step of attenuating the rotation of the projectile to control the horizontal start of the projectile.

According to one aspect of the present invention, the step of separating the protective cap may set a time for separating the protective cap so that the protective cap can be separated when the set time is reached after the launch of the projectile.

The control vanes of the projectile and the control method thereof according to the embodiment include control vanes independently operated at the lower portion of the projectile to suppress the rotation of the projectile and to control the rise and fall of the projectile during the flight, Attitude control can be performed.

In addition, by providing the projecting wing device of the projectile in the projectile, it is possible to perform a glide flight or a detour flight.

Further, the protective cap is provided to protect the control vane when the projectile is fired, and to prevent damage to the concentric barrel that fires the projectile.

1 is a perspective view showing a projectile according to an embodiment.
FIG. 2 is an exploded perspective view showing a control vane apparatus of a projectile according to an embodiment.
3 is an exploded perspective view showing a case according to an embodiment.
4 is a view showing an arrangement of the interior of a control unit of a projectile according to an embodiment.
5 is a perspective view showing a state of a control blade according to an embodiment.
FIG. 6 is a cross-sectional view showing a developed state of a control blade according to an embodiment. FIG.
FIG. 7 is a perspective view illustrating a gear box portion and a control blade according to an embodiment of the present invention. FIG.
FIG. 8 is a view illustrating an exemplary operation of a control unit of a projectile 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;

1 is a perspective view showing a projectile according to an embodiment.

Referring to FIG. 1, the projectile 1 may be launched from a gun having a concentric barrel such as a flat-screen gun, a mortar, a howitzer, and the like. Herein, the concentric barrel means barrel-shaped barrel. When the projectile 1 is fired by the concentric barrel, a high rotation may occur along the concentric circle, and it may be difficult to precisely hit the projectile 1 due to the rotation. In addition, the projectile 1 can be defined in terms of the range of angles according to the amount of propellant such as gun powder, fuel, etc. and the angle of emission of the concentric barrel.

Therefore, the projectile 1 of one embodiment includes the control blade unit 20 mounted on the flange of the main body 10 so as to suppress the rotation of the projectile 1 and control the rise and fall of the projectile 1, And it is possible to perform a glide flight or a detour flight of the projectile 1.

3 is an exploded perspective view showing a state of a case 300 according to an embodiment, and FIG. 4 is an exploded perspective view showing an embodiment of the control wing device 20 according to an embodiment FIG. 5 is a view showing an arrangement of the interior of the control blade apparatus 20 of the projectile according to FIG.

2 to 4, the control wing device 20 of the projectile includes a protective cap 100, a protective pillar 200, a case 300, a control wing 400, a gearbox 500, (600).

The protective cap 100 may be disposed so as to surround the outside of the control vane 400 in a state in which the control vane 400 is housed in the case 300 while being folded. For example, the protective cap 100 may have a cylindrical or frusto-conical shape with one surface being recessed. The protective cap 100 can be housed outside the case 300 on the inner circumferential surface thereof. The inner circumferential surface of the protective cap 100 may have the same shape as the outer circumferential surface of the case 300. The other surface of the protection cap 100 may be connected to one surface of the case 300 through the plurality of first engagement members 110.

The protective cap 100 can protect the control wing 400 from impacts caused by explosion of the propellant during the propulsion of the projectile 1 in the concentric barrel. In addition, the protective cap 100 can protect not only the control wing portion 400 but also the entire case 300. In addition, the protective cap 100 prevents the deployment of the control wing 400 in the concentric barrel, thereby preventing simultaneous barrel damage.

The protective cap 100 may be disengaged in the case 300 when the projectile 1 is out of the barrel and reaches a set altitude. For example, when the projectile 1 is out of the barrel and reaches the set altitude, the protective cap 100 may be provided with a plurality of second And can be separated in such a manner that the protective cap 100 is pushed out by cutting and pushing the engaging member 341. The detonator may be disposed on or adjacent to the plurality of second engaging members 341. The protective cap 100 may have a separation speed of 8 m / s to 20 m / s.

The protective pillar 200 can be disposed between the control blade 400 and the protective cap 100 in a state in which the control blade 400 is housed in the case 300 while being folded. For example, a plurality of the protective pillars 200 may be provided on the outer surface of the control wing 400, which is accommodated in a folded state. The protective pillar 200 is disposed so as to be inserted into the inside of the case 300 when the protective cap 100 is attached to the case 300 so as to be inserted into the inside of the case 300, Can be reduced.

The protective pillar 200 may be disposed so as not to be fixed to the outer surface of the control vane 400. However, the present invention is not limited thereto, and the protective pillar 200 may be adhered with a low strength and separated when a certain force is applied. For example, the protective pillar 200 may be brazed and coupled to the outer surface of the control vane 400. However, the protective filler 200 may be any adhesive means such as a low-strength adhesive, an adhesive tape or the like.

The protective pillar 200 may have a shape corresponding to the outer surface of the control vane 400 and a surface corresponding to the outer circumferential surface of the case 300. In addition, the protective pillar 200 may have a plurality of vent holes 210 passing through one side thereof. The plurality of ventilation holes 210 can reduce the weight of the protective pillar 200.

The protective pillar 200 may be detached from the control vane 410 when the protective cap 100 is detached. For example, when the protective pillar 200 is simply disposed on the control blade 410, the control pillar 410 can be pushed and separated by the control blade 410 when the control blade 300 is deployed. Further, after the protection cap 100 is separated, the protective pillar 200 can be separated by the centrifugal force due to the rotation of the projectile 1.

The case 300 may be coupled to one side of the main body 10 of the projectile 1. For example, the case 300 may be coupled to the rear of the main body 10 of the projectile 1. [ The case 300 may include a case body 310, a control blade storage groove 320, a gear box storage groove 330, a module cover 340, a lock cap 350, and a base 360.

The case body 310 may have a shape corresponding to the inside of the protective cap 100. For example, the case body 310 may have a cylindrical or frusto-conical shape and may have a shape corresponding to the inside of the protective cap 100.

A plurality of control wing receiving grooves 320 may be formed on the outer peripheral surface of the case body 310 in a radial manner. The control blade storage groove 320 may have a sufficient depth so that the surface exposed to the outside of the control blade 400 housed in the folded state is accommodated inside the outer circumferential surface of the case 300. [

The control vane storage groove 320 may include a central rotation axis fixing hole 321 connected to the gearbox receiving groove 330 for connection between the control vane 400 and the gear box portion 500. For example, the central rotation axis fixing hole 321 may receive a central rotation axis 420 of the control wing portion 400, which will be described later, by forming a circular hole in the inner side surface of the control blade accommodation groove 320. Further, the center shaft fixing hole 321 may be formed to communicate with the gear box receiving groove 330. The inner circumferential surface of the central rotation axis fixing hole 321 may be formed in a female screw shape.

The gearbox receiving groove 330 may be formed inside the case 300. For example, a plurality of gearbox receiving grooves 330 may be recessed inward from one end of the case body 310. The gear box receiving groove 330 may be in communication with the central rotating shaft fixing hole 321 and connected to the control blade receiving groove 320. The gearbox receiving groove 330 can receive the gear box portion 500. The gearbox portion 500 housed in the gearbox receiving groove 330 may be connected to a center rotational shaft 420 coupled to the center rotational shaft fixing hole 321 in a penetrating manner.

The module cover 340 may seal the rear surface of the case 300. The module cover 340 can seal the gearbox receiving groove 330 to protect the gear box portion 500 against impacts when the launch vehicle 1 is fired. The module cover 340 may be coupled to the rear surface of the case 300 by a plurality of second engagement members 341.

One end of the plurality of second engagement members 341 may be coupled through the module cover 340 and the case 300. The second coupling member 341 may have a hole to which the first coupling member 110 is coupled at the other end.

The lock cap 350 may be coupled to one surface of the module cover 340. The lock cap 350 may be coupled to the module cover 340 to seal one end of the case 300 together with the module cover 340.

The base 360 may seal the front surface of the case 300. The base 360 may be connected to the main body of the projectile 1 in such a manner that the surface thereof opposed to the surface coupled with the case 300 is connected.

FIG. 5 is a perspective view showing a state of the control wing 400 according to an embodiment, and FIG. 6 is a sectional view showing a developed state of the control wing 400 according to an embodiment.

5 to 6, the control vane 400 may include a control vane 410, a central rotation axis 420, and a vane rotation pin 430.

The control wings 410 are housed in a folded state in the case 300, and can be deployed after being fired. For example, the control blade (410) is stored in the control blade storage groove (320) in a folded state, and when the projectile (1) is fired and reaches the set height, the protective cap (100) .

The control wing 410 may be connected to the central rotation axis 420 in the form of a hinge. For example, the control wings 410 may include two extending portions 411 extending from the one end portion and spaced apart from each other and fastened to both sides of the wing rotation pin 430, respectively. The two extending portions 411 may be spaced apart. The control wing 410 may be rotated about the extension 411 to be deployed.

The control wing 410 may further include a fixing pin 412, a pin groove 413 and an elastic member 414 for fixing the longitudinal direction of the control wing 410 to the central rotation axis 420 during deployment.

The fixing pin 412 may be discharged in the longitudinal direction of the central rotary shaft 420 to fix the control blade 410 to the central rotary shaft 420 when the control blade 410 is deployed. For example, the fixing pin 412 can be disposed in the longitudinal direction of the control vane 410 at the center between the spaced apart portions formed by the two extensions 411.

The pin groove 413 may be recessed longitudinally at the center between the spaced apart portions of the extension 411. The pin groove 413 can be received by the fixing pin 412.

The elastic member 414 can elastically support the fixing pin 412 in the pin groove 413. For example, the elastic member 414 is disposed between the fixing pin 412 and the pin groove 413 so as to be elastically supported by the fixing pin 412. The elastic member 414 may be a spring. However, the present invention is not limited to this, and the elastic member 414 may be capable of all members capable of projecting the fixing pin 412 out of the pin groove 413 by the stretching force.

The central rotation axis 420 may be coupled to the control vane 410. For example, the center rotary shaft 420 may be disposed between the extended portions 411 of the control vanes 410, and may be coupled to the vane rotary pins 430 through the center rotary shaft 420.

The center rotational axis 420 may be fixed to the center rotational axis fixing hole 321. In addition, the central rotation axis 420 may be disposed perpendicularly to the outer circumferential surface of the case 300. The central rotation axis 420 may include a fixing member 421 having an outer circumferential surface formed in a male screw shape on one side of the outer circumferential surface.

The central rotation axis 420 may include a fixing groove 422 formed at one end thereof coupled with the control vane 400 and formed to be recessed inward. The fixed groove 422 receives the fixed pin 412 discharged from the deployed control vane 410 and the deployed control vane 410 can be coupled to the central rotary shaft 420. The fixing groove 422 may have a depth such that the discharged fixing pin 412 extends across the fixing groove 422 and the pin groove 413.

The wing rotation pin 430 can connect the control wing 410 and the central rotation axis 420 in a hinge form. For example, the wing rotation pin 430 may connect the extension 411 of the wing 410 and one end of the center rotation axis 420 in a hinge form. The wing rotation pins 430 may be disposed in pairs and spaced apart from each other. The wing rotation pin 430 may be an axis through which the control wing is deployed.

FIG. 7 is a perspective view showing a combined state of the gear box part 500 and the steering wing part 400 according to an embodiment.

Referring to FIG. 7, the gear box portion 500 is connected to the center rotational shaft 420, and rotatably drives the control vane 410 about the central rotational axis 420. The gear box part 500 may include a worm wheel 510 and a worm gear module 520.

The worm wheel 510 may be disposed along the outer circumferential surface of the center rotary shaft 420. For example, the worm wheel 510 may be coupled to an outer circumferential surface located inside the central rotation axis fixing hole 321 of the case of the central rotation axis 420. [

The worm wheel 510 alone can be coupled to the outer circumferential surface of the central rotary shaft 420 but the worm wheel 510 can be coupled through the connection shaft 511. [ The connecting shaft 511 may have a size such that the outer circumferential surface thereof corresponds to the inner circumferential surface of the worm wheel 510. The connection shaft 511 may have a size such that the inner circumferential surface thereof corresponds to the outer circumferential surface of the central rotational shaft 420. The worm wheel 510 having the inner circumferential surface that does not correspond to the outer circumferential surface of the central rotational shaft 420 can be coupled to the central rotational shaft 420 by having the connecting shaft 511. [

The worm gear module 520 is connected to the worm wheel 510 to adjust the rotation angle of the center rotary shaft 420. The worm gear module 520 may include a driving part 521, a reduction gear 522, and a worm 523. [

The driving unit 521 may be any means capable of rotating a plurality of reduction gears 522 such as a motor and a hydraulic motor. The driving unit 521 may be controlled through the control unit 600 to rotate the reduction gear 522.

The reduction gear 522 can transmit the rotation to the worm 523 by reducing the rotation of the driving unit 521. [ For example, a plurality of reduction gears may be provided to reduce the rotation of the driving unit 521 and transmit it to the worm 523.

The worm 523 can further reduce the rotation of the driving unit 521 transmitted through the reduction gear 522 and transmit the worm wheel 510 to the worm 523. The worm 523 rotates and can rotate the worm wheel 510 coupled to the outer peripheral surface of the shape of the thread.

The reduction gear 522 and the worm 523 can rotate the worm wheel 510 by reducing the rotation of the driving unit 521 so that the rotation angle of the central rotation axis 420 is adjusted .

The control unit 600 may generate an electrical signal for separating the protective cap 100. [ For example, the control unit 600 sets the separation time of the protection cap, and when it reaches the set time, it generates an electrical signal to separate the protection cap 100. The control unit 600 may adjust the set value of the separation time according to the firing angle of the barrel to set the altitude at which the protective cap 100 is separated.

The control unit 600 may control the plurality of gear box units 500. For example, the control unit 600 controls the plurality of gear box units 500 so that the swing angle of the control vane 410 in the direction of suppressing the roll direction rotation of the projectile 1 by the deployed control vane 410 (Cant angle) can be adjusted. The control unit 600 can control the gear box unit 500 to rotate the central rotation axis 420 and fix the yaw angle of the control wing 410 to attenuate the rotation of the launch vehicle 1 in the roll direction. The angle can be controlled within a certain range. For example, the gait angle can be adjusted within a range of -30 to 30 degrees with the control blade 410 initially deployed.

In addition, the control unit 600 can independently control the horizontal start of the projectile 1 by independently driving the deployed control vanes 410. For example, when the rotation of the projectile 1 in the roll direction is attenuated to a certain rpm or less, the control unit 600 can readjust the control blade 410 in the direction parallel to the longitudinal direction of the projectile 1. The control unit 600 can independently control the respective control vanes 410 to control the horizontal movement of the projectile 1. [

The control wing device 20 further includes a projectile rotation speed sensor (not shown) for sensing the roll rotation speed of the projectile 1 and a rotation axis angle sensor 700 for sensing the rotation angle of the central rotation axis 420 . The projectile rotation speed sensor may be disposed at any portion capable of sensing the roll rotation speed of the projectile 1 in the control blade unit 20. [ As shown in FIG. 4, the rotation axis angle sensor 700 may be disposed adjacent to the center rotation axis 420 to sense the rotation angle of the center rotation axis 420.

This control wing device 20 can attenuate the rotation of the projectile 1 in the roll direction to a constant rpm or less within several tens of seconds. For example, the control wing device 20 can reduce the rotation of the projectile 1 in the roll direction within 180 seconds to less than 180 rpm. The control wing device 20 can control the rise and fall of the projectile 1 by independently driving each control blade 410 after attenuating the high rotation of the projectile 1. In addition, the control wing device 20 can control precise attitude of the projectile 1 by independently driving the respective control vanes 410, and it is also possible to fly a glide flight or a bypass flight.

Hereinafter, a control method of the steering wing apparatus will be described.

The control method of the control wing device 20 includes a step of launching the projectile 1, a step of separating the protective cap from the fired projectile 1, a step of disengaging the plurality of control blades 410 after the protective cap 100 is separated, And controlling the angle of rotation of the plurality of deployed control vanes 410. [0050]

The step of launching the projectile 1 includes a plurality of control vanes 410 housed in the case 300 and the case 300 in a folded state and a protective cap 100 The launch vehicle 1 including the launch vehicle 1 may be launched. The step of launching the projectile 1 prevents the protective cap 100 from deploying the control vane 410 and can be launched through the concentric barrel.

FIG. 8 is a view illustrating an exemplary operation of a control unit of a projectile according to an embodiment.

8, the step of separating the protective cap 100 from the projectile 1 sets the time at which the protective cap 100 is separated, and when the set time is reached after the launching of the projectile 1, (100) can be separated. For example, in the step of separating the protective cap 100 from the projectile 1, the control unit 600 sets the time for detaching the protective cap 100 to disconnect the protective cap 100 when the set time is reached have. The control unit 600 may change the set time according to the firing angle so that the protective cap 100 is separated at a predetermined altitude. The control unit 600 can generate an electric signal for disconnecting the protection cap 100 and disconnect the protection cap 100 when the projectile 1 reaches the set time.

The step of deploying the plurality of control vanes 410 may include deploying the plurality of control vanes 410 after the protection cap 100 has been detached. For example, in the step of deploying the plurality of control vanes 410, after the protection cap 100 is separated from the control vanes 410, the plurality of control vanes 410 are rotated simultaneously with the rotational force and the centrifugal force of the projectile 1 And the control vane 410 can be deployed with the wing rotation pin 430 as an axis. The plurality of control vanes 410 can be deployed with the protective pillar 200 disposed on the outer side being detached. When the plurality of control vanes 410 are completely deployed, the fixing pins 412 are ejected to the elastic members 414 and partially inserted into the fixing grooves 422 so that the plurality of control vanes 410 are fixed to the central rotation axis 420 .

The step of controlling the rotation angle of the plurality of control vanes 410 can control the horizontal start of the projectile 1 by attenuating the rotation of the projectile 1 by adjusting the plurality of developed rotation angles. The step of controlling the rotation angle of the plurality of control vanes 410 may include damping the rotation of the projectile 1 and controlling the horizontal start of the projectile 1. [

The step of attenuating the rotation of the projectile 1 may be performed by adjusting the angle of rotation of the control blade 410 in the direction of suppressing the rotation of the projectile 1 by the deployed control blade 410, Can be attenuated. For example, in the step of attenuating the rotation of the projectile 1, the control unit 600 controls the gearbox unit 500 to return the central rotation axis 420 connected to the gearbox unit 500, The angle of the control vane 410 can be adjusted in a direction to suppress the rotation of the control vane 410. [ The gear box part 500 can fix the angle of inclination of the controlled vane 410 to attenuate the rotation of the projectile 1. The rotation of the projectile 1 can be attenuated to 180 rpm or less.

In the step of controlling the horizontal start of the projectile 1, the deployed control vanes 410 can be independently driven to control the horizontal start of the projectile 1. For example, in the step of controlling the horizontal start of the projectile 1, when the control unit 600 controls the gear box unit 500 to detect a high speed rotation of 180 rpm or less in the projectile body rotation speed detection sensor 700, It is possible to readjust the angle of the control vane 410 in the direction parallel to the longitudinal direction of the control vane 410. The control unit 600 may independently control the respective gearboxes 410 after the control vanes 410 are readjusted. The control unit 600 can independently control the respective control vanes 410 to perform precise attitude control such as ascending, descending, gliding, and detour flight of the projectile 1. [

The control device of the projectile wing device 20 and the control method thereof according to the embodiment includes a control vane 410 that is independently driven at a lower portion of the projectile 1 to suppress the rotation of the projectile 1, By controlling the rise and fall of the projectile 1, accurate attitude control of the projectile 1 can be achieved.

Further, by providing the projecting blade device 20 of the projectile on the projectile 1, it is possible to perform a glide flight or a bypass flight.

In addition, the protection cap 100 is provided to protect the control vanes 410 and prevent damage to the concentric barrel that fires the projectile 1 when the projectile 10 is fired.

Although the present invention has been described in connection with what is presently considered to be practical exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, And various modifications and changes may be made thereto without departing from the scope of the present invention. Accordingly, the spirit of the present invention should not be construed as being limited to the embodiments described, and all of the equivalents or equivalents of the claims, as well as the following claims, belong to the scope of the present invention .

Claims (15)

A case coupled to one side of the body of the projectile;
A plurality of control blades housed in the case in a folded state and having a control blade deployed after firing and a central rotation axis coupled to the control blade;
A plurality of gear box parts connected to the central rotation axis and rotationally driving the control vane about the central rotation axis;
A control unit for controlling the plurality of gear box units;
A projectile rotation speed sensor for sensing a roll rotation speed of the projectile; And
A rotation axis angle sensor for sensing a rotation angle of the central rotation axis;
Lt; / RTI >
Wherein,
Wherein the control unit controls the plurality of gear box units based on information sensed by the projectile rotation speed sensor and the rotation axis angle sensor so that the angle of inclination of the steering wing in the direction of suppressing the rotation of the projectile by the deployed steering wing The control unit controlling the cant angle of the launch vehicle.
delete The method according to claim 1,
Wherein,
And controls the plurality of gear box sections to independently drive the deployed control vanes to control the horizontal start of the projectile.
The method according to claim 1,
The plurality of gear box parts
A worm wheel disposed along an outer circumferential surface of the central rotation shaft; And
A worm gear module connected to the worm wheel and adjusting a rotation angle of the center rotary shaft;
The control device comprising:
A case coupled to one side of the body of the projectile;
A plurality of control blades housed in the case in a folded state and having a control blade deployed after firing and a central rotation axis coupled to the control blade;
A plurality of gear box parts connected to the central rotation axis and rotationally driving the control vane about the central rotation axis; And
And a control unit for controlling the plurality of gear box units,
Wherein each of the plurality of control vanes comprises:
A wing rotation pin connecting the control wing and the central rotation shaft in a hinge form;
Further comprising:
The control wing
Two extensions extending from the one end and spaced apart from each other and fastened to opposite sides of the wing rotation pin, respectively;
A fixing pin which is discharged in a longitudinal direction of the central rotary shaft and fixes the control blade to the central rotary shaft when the control blade is deployed;
A pin groove which is recessed in the longitudinal direction at the center of the one end and receives the fixing pin; And
An elastic member for elastically supporting the fixing pin in the pin groove;
And a control unit for controlling the operation of the control unit.
delete 6. The method of claim 5,
The center axis of rotation
A control blade fixing groove formed to be inwardly depressed from a center of the one end and to which the fixing pin is coupled;
The control device comprising:
The method according to claim 1,
The projectile is launched from a concentric barrel,
And a control unit that is disposed so as to surround the outside of the control vane unit in a state that the control vane unit is housed in a folded state in the casing so as to prevent the control vane unit from being impacted by explosion of the propellant during the propulsion of the projectile in the concentric barrel. A protective cap for protection;
And a control unit for controlling the operation of the control unit.
9. The method of claim 8,
Wherein,
And the protective cap is detached from the case when the projectile is out of the barrel and reaches a set altitude.
9. The method of claim 8,
A protective pillar disposed between the control blade and the protection cap and being detached from the control blade when the protection cap is detached in a state that the control blade is housed in the case while being folded;
And a control unit for controlling the operation of the control unit.
The method according to claim 1,
In this case,
A case body;
A plurality of control vane storage grooves formed on an outer peripheral surface of the case body so as to be radially recessed; And
A plurality of gearbox storage grooves formed in the case and communicating with the plurality of control blade storage grooves, respectively;
The control device comprising:
A step of launching a projectile including a case, a plurality of control vanes housed in the case in a folded state, and a protective cap for preventing the plurality of control vanes from being deployed;
Separating the protective cap from the fired launch vehicle;
Deploying the plurality of control vanes after the protective cap is detached; And
Controlling a rotation angle of the deployed plurality of control blades;
And a control device for controlling the control wing device.
13. The method of claim 12,
Wherein the step of controlling the rotation angles of the plurality of deployed control vanes comprises:
Attenuating the rotation of the projectile by adjusting a Cant angle of the control blade in a direction of suppressing rotation of the projectile by the deployed control blade;
And a control device for controlling the control wing device.
14. The method of claim 13,
After the step of attenuating the rotation of the projectile,
Controlling the horizontal start of the projectile by independently driving each of the deployed control blades;
And a control device for controlling the control wing device.
13. The method of claim 12,
The step of separating the protective cap comprises:
Wherein the control cap is separated when the set time is reached after the launch of the projectile.
KR1020170141395A 2017-10-27 2017-10-27 Apparatus for control fin of a projectile and control method thereof KR101864088B1 (en)

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KR102088240B1 (en) * 2018-11-14 2020-03-12 주식회사 경인테크 Maneuvering wing drive for guided cannon with easy storage and separation
KR102104259B1 (en) * 2018-12-21 2020-04-24 국방과학연구소 Canard deploying apparatus for guided missile and canard deploying method for guided missile using the same
KR20200055406A (en) * 2018-11-13 2020-05-21 국방과학연구소 The driving part air frame of the guided missile including the dissimilar materials
WO2021170484A1 (en) * 2020-02-27 2021-09-02 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile fin-folding device, missile, and method for operating a missile
CN116853481A (en) * 2023-07-10 2023-10-10 北京新风航天装备有限公司 Folding fixing device of air rudder

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20200055406A (en) * 2018-11-13 2020-05-21 국방과학연구소 The driving part air frame of the guided missile including the dissimilar materials
KR102116059B1 (en) * 2018-11-13 2020-05-27 국방과학연구소 The driving part air frame of the guided missile including the dissimilar materials
KR102088240B1 (en) * 2018-11-14 2020-03-12 주식회사 경인테크 Maneuvering wing drive for guided cannon with easy storage and separation
KR102104259B1 (en) * 2018-12-21 2020-04-24 국방과학연구소 Canard deploying apparatus for guided missile and canard deploying method for guided missile using the same
WO2021170484A1 (en) * 2020-02-27 2021-09-02 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile fin-folding device, missile, and method for operating a missile
DE102020105188B4 (en) 2020-02-27 2023-08-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile fin deployment device, missile and method of operating a missile
CN116853481A (en) * 2023-07-10 2023-10-10 北京新风航天装备有限公司 Folding fixing device of air rudder
CN116853481B (en) * 2023-07-10 2024-01-05 北京新风航天装备有限公司 Folding fixing device of air rudder

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