KR102104259B1 - Canard deploying apparatus for guided missile and canard deploying method for guided missile using the same - Google Patents

Abstract

The present invention relates to an apparatus of deploying a control fin for a guided weapon, which comprises: a bullet body on which a slot type opening unit for deploying a fin is disposed; a control fin disposed in the bullet body to rotate, elastically supported by an elastic body, and deployed by elasticity of the elastic body; and a fin stopper unit supporting the control fin to be disposed in the bullet body in a folded state, and allowing the control fin to be deployed after a guided weapon is launched. Accordingly, the apparatus of deploying a control fin for a guided weapon prevents accidental deployment of the control fin, and enables the control fin to be deployed only when the guided weapon is actually operated. Therefore, the apparatus of deploying a control fin for a guided weapon can prevent disuse of the entire complete bullet due to a deployment of the control fin, thereby preventing unnecessary consumption of the guided weapon and significantly increasing operation efficiency of the guided weapon.

Description

Guided wing deployment device for guided weapons and method of deploying guided wing for guided weapons using the same {CANARD DEPLOYING APPARATUS FOR GUIDED MISSILE AND CANARD DEPLOYING METHOD FOR GUIDED MISSILE USING THE SAME}

The present invention relates to a method for deploying a control wing for a guided weapon and a method for deploying a control wing for a guided weapon using the same, and more specifically, a control wing deployment device for a guided weapon capable of preventing an accident in which a control wing is deployed in an unintended situation. And a method for deploying a steering wing for a guided weapon using the same.

Guided weapons are guided bombs or guided shells that are made to reach and explode accurately at the target by the induction of radar or infrared rays. Guided weapons are launched and propelled by jet engines or rockets and are detonated after impact on the target.

The guided weapon consists of a fuselage in appearance, a warhead is assembled at the tip of the fuselage, a steering wing is provided, and a nozzle and a fixed wing are assembled at the rear end.

In general, guided weapons control the flight direction and posture using a steering wing.

In the case of a guided rocket using a cylindrical launcher and a guided shell using a gun, among the guided weapons, the steering wing must be stored inside the shot before firing, and the steering wing is deployed at the control point after firing.

To this end, in the case of a conventional guided weapon, a groove is formed in a slot shape at a position where the steering wing is stored and deployed, and through this groove, the steering wing is accommodated inside the bullet and can be deployed outside the shot at the time of deployment.

However, in the case of the method of deploying the steering wings after being aligned to the deployed position, if the steering wings are aligned to the deployed position due to an unintentional accident, the steering wings may be unfolded and the entire complete bullet may be unusable.

Therefore, additional software is required to check the alignment position of the steering blade when checking the finished bullet.

However, even if the alignment position of the steering wing is checked by software for checking the alignment position of the steering wing, there is a problem that the accident in which the steering wing is deployed due to an external environment such as external impact cannot be completely prevented.

Patent Document 1: Korean Patent Registration Publication No. 1984-0001056 (announced on July 27, 1984) Patent Document 2: Korean Registered Patent Publication No. 1522212 (2015.05.15 announcement)

The object of the present invention is to prevent the accidental deployment of the steering wing, and to control the guided weapon to prevent accidents in which the whole of the finished bullet is insoluble by the development of the control wing by allowing the steering wing to be deployed only during actual operation of the guided weapon. The object of the present invention is to provide a wing deployment device and a method of deploying a control wing for a guided weapon using the same.

Another object of the present invention is to prevent the accidental deployment of the control wing, and the control wing deployment device for a guided weapon that enables the guided weapon to accurately strike the target by allowing the control wing to be deployed accurately at the time of control of the guided weapon and It is to provide a method for deploying a control blade for a guided weapon using the same.

In order to achieve the above object of the present invention, an embodiment of a steering wing deployment device for a guided weapon according to the present invention is a bullet body in which a slot-shaped blade deployment opening is located, rotatably located in the bullet body and in an elastic body It characterized in that it comprises a wing stopper that is elastically supported by the steering blade and is deployed by the elastic force of the elastic body, the steering blade is supported to be positioned in a folded state within the bullet body, and the steering blade is deployed after the launch of the guided weapon. do.

In the present invention, a wing support member to which the steering blade is rotatably coupled may be located inside the burnt body.

In the present invention, the steering wing is folded in the compressed state by being caught by the wing stopper part within the burnt body, and the wing stopper part is positioned on the inner surface of the opening for spreading the wings and hangs and supports the steering wing. It may include a stopper protrusion.

In the present invention, the wing stopper portion is positioned so that the steering blade is twisted in the deployed position so that the steering wing is caught in the stopper protrusion, and the steering wing is aligned to the deployed position to release the jamming of the steering wing. It may further include a wing position adjustment unit.

In the present invention, the blade position adjustment unit may include a rotating motor, an electric gear member positioned on the shaft of the rotating motor, and a blade alignment member rotated by receiving rotational force from the electric gear member to align the steering blades to the deployed position. .

In the present invention, the wing position adjusting unit may further include a power transmission body for transmitting the rotational force of the electric gear member to the blade alignment member.

In the present invention, the power transmission body includes a spur gear member that is rotated in engagement with the electric gear member, and a worm gear member that is connected to a rotation shaft of the spur gear member and receives rotational force from the spur gear member to rotate. The alignment member may be a worm wheel gear having gear teeth rotated in engagement with the worm gear member positioned on an outer circumferential surface.

In the present invention, the wing position adjustment unit may further include a wing position detection unit for detecting the twisted position of the steering blade.

In the present invention, the wing position detection unit detects the twisted angle of the steering blade and transmits it to a control unit that controls the operation of the rotating motor, and the control unit receives the twisted angle of the steering blade from the wing position detection unit. With the operation of the rotating motor, the operation of the rotating motor can be controlled so that the steering blades are erected and aligned to the deployed position.

In the present invention, the wing stopper portion may further include a wing deployment prevention portion supporting a side surface of the steering blade to maintain the twisted position of the steering blade.

In the present invention, the wing deployment prevention unit may be positioned in a state in which the steering wing is hung by the stopper protrusion by supporting the side of the steering wing while the steering wing is twisted and supported by the stopper protrusion.

In the present invention, the wing deployment prevention unit may release the locking state of the steering blade while retracting by the reverse inertia force generated after the launch of the guided weapon.

In the present invention, the wing deployment prevention unit supports a side of the stopper housing, the side of the control blade which protrudes from the stopper housing, and is retracted by a reverse inertia force and inserted into the stopper housing, and the side support pin member and the side support pin member. It may include a first spring member for elastic support.

In the present invention, the wing deployment prevention unit further includes a pin stopper member positioned to support a side surface of the side support pin member in the stopper housing and a second spring member elastically supporting the pin stopper member, and the pin stopper member When the side support pin member is inserted into the stopper housing member, it moves to the elastic restoring force of the second spring member to prevent a pin hole through which the side support pin member penetrates in the stopper housing.

In the present invention, the stopper housing includes a first housing portion in which the side support pin member is inserted and movable, and a second housing portion positioned in a vertical direction with the first housing portion and in which the pin stopper member is movable. It can contain.

In order to achieve the above object of the present invention, an embodiment of a method for deploying a steering blade for a guided weapon according to the present invention is positioned in a folded state supported by a stopper protrusion in a twisted position based on a deployed position in a bullet body, and elasticity of the elastic body It is a method of deploying a steering wing that is deployed with resilience, and a guided weapon launching step, a deployment command receiving step of receiving a command to deploy a control wing at a control point after the guided weapon is launched, and a control wing with a deployment command received in the step of receiving the deployment command. Steering blade alignment step of releasing the steering blade from the stopper projection by engaging the position to the deployed position; And a wing deployment step in which the control wing is released from the stopper protrusion engaging in the alignment of the control wing and the control wing is deployed with the elastic restoring force of the elastic body.

An embodiment of a method for deploying a steering wing for a guided weapon according to the present invention is a wing side restraint release step for releasing the restraint of a wing deployment preventing part that walks and supports the side of the steering wing before the deployment command reception step after the guided weapon launching step It may further include.

In the present invention, the wing side restraining step retracts the side support pin member supporting the side of the steering wing by retracting and supporting the side of the steering wing by the reverse inertia force generated by the launch of the guided weapon. can do.

The present invention prevents the accidental deployment of a control wing and prevents accidents in which the whole of the finished bullet is insoluble due to the development of the control wing by allowing the control wing to be deployed only when the guided weapon is actually operated. It has the effect of preventing and greatly improving the operational efficiency of the guided weapon.

The present invention prevents the accidental deployment of a control wing, and allows the control wing to be deployed accurately at the time of control of the guided weapon, so that the guided weapon can strike the target accurately, greatly improving the accuracy of the guided weapon, and Reliability can be secured during operation

In addition, the present invention has the effect of securing the operational reliability of the wing deployment prevention unit and maximizing the space utilization in the bullet body by operating the wing deployment prevention unit using the reverse inertia force generated when the guided weapon is fired without an additional power device.

1 is a perspective view showing an embodiment of a control wing deployment device for a guided weapon according to the present invention.
Figure 2 is a perspective view that can confirm the internal configuration of the bullet body by cutting a part of the bullet body in one embodiment of the steering wing deployment device for a guided weapon according to the present invention.
Figure 3 is a view showing a wing deployment prevention unit in one embodiment of the steering wing deployment device for a guided weapon according to the present invention.
4 and 5 are views showing an operation example of the wing deployment prevention unit in one embodiment of the steering wing deployment device for a guided weapon according to the present invention.
6 and 7 are views illustrating a state in which a steering blade is arranged to be deployed in one embodiment of a steering blade deployment device for a guided weapon according to the present invention.
8 is a view showing an example in which a steering wing is deployed in an embodiment of a steering wing deployment device for a guided weapon according to the present invention.
Figure 9 is a flow chart showing an embodiment of a method of deploying a steering wing for guided weapons according to the present invention.

The present invention will be described in more detail.

If described in detail by the accompanying drawings, preferred embodiments of the present invention. Prior to the detailed description of the present invention, terms or words used in the present specification and claims described below should not be interpreted as being limited to a conventional or dictionary meaning. Therefore, the configuration shown in the embodiments and drawings described in this specification is only one of the most preferred embodiments of the present invention and does not represent all of the technical spirit of the present invention. It should be understood that there may be equivalents and variations.

1 and 2, a guided weapon to which a steering wing deployment device for a guided weapon according to the present invention is applied may be a guided shell, and a bullet body formed with a slot-shaped opening 110 for wing deployment ( 100).

The bullet body 100 corresponds to the head of a guided weapon and has an ogive shape in consideration of flight speed, required volume, and radar wave refraction.

The slot-shaped blade opening portion 110 is an open portion for the steering blade 200 to be deployed, and is formed in a long hole shape in the length direction of the bullet body 100.

The steering wing 200 is rotatably positioned inside the burnt body 100 and is stored in a folded state.

The steering wing 200 adjusts the posture of the guided weapon, and in particular, adjusts the posture of the guided weapon so that it can follow and hit the target, thereby enabling flight. The steering wing 200 may vary from a trapezoid to a rectangular shape according to the flight speed.

In this embodiment, as an example, the steering wing 200 is formed in a rectangle.

Since the amount of lift generated increases as the area becomes wider, a rectangular wing is selected to secure the maximum area for efficiency and make the most of the space.

As an example, the steering wing 200 is positioned at a plurality of bullet bodies 100 and deployed at the same time.

That is, although not shown, the opening 110 for wing deployment may be spaced apart in the circumferential direction on the outer circumferential surface of the bullet body 100, and each steering wing 200 may be positioned correspondingly.

For example, the steering wing 200 is provided inside the burnt body 100 to be disposed in a cross shape when viewed from the front and can be simultaneously deployed.

The steering wing 200 is deployed by rotating around the blade rotation shaft 420, and the wing hinge portion 210 through which the blade rotation shaft 420 is penetrated is positioned at the upper end of the steering blade 200.

The wing support member 400 to which the steering wing 200 is rotatably coupled is located inside the burnt body 100, and the wing hinge part located at the upper end of the steering wing 200 is located in the wing support member 400 ( 210) is inserted into the hinge insertion portion 410 is inserted.

And, in the hinge insertion portion 410 is located in the horizontal direction, the blade rotation shaft 420 penetrating the wing hinge portion 210 is positioned.

The steering wing 200 is deployed and positioned in the longitudinal direction of the opening 110 for wing deployment so that it can be deployed and unfolded to the outside of the burnt body 100 through the opening 110 for wing deployment.

The wing rotation shaft 420 is positioned in a direction perpendicular to the longitudinal direction of the opening 110 for wing deployment, and the steering blade 200 is centered around the wing rotation shaft 420 in a state where it is folded and positioned within the burnt body 100. It can be rotated and unfolded and drawn out of the burnt body 100 through the opening 110 for wing deployment.

The steering wing 200 is folded and elastically supported by the elastic body in a state located within the burnt body 100, and has a structure that is developed by the elastic restoring force of the elastic body.

The steering wing 200 is supported by the wing stopper part 300 and is positioned in a state in which the elastic body is compressed in a folded state within the burnt body 100.

The steering wing 200 is elastically supported by an elastic body having an elastic force in the deployment direction and is deployed as the elastic body is restored.

The elastic body is a deployment spring disposed at the rear of the steering blade 200 close to the rotation axis of the steering blade 200 so as to provide elastic force in the direction in which the steering blade 200 is deployed.

For example, the deployment spring is a 'a' shaped leaf spring, and when it is restored with an '∩' shape in an elastically deformed state, it is brought into a 'a' shape and the steering blade 200 is the central axis of the burnt body 100 So that it can be developed at right angles.

In addition to the plate spring, various examples may be employed as long as the shape of the elastic body provides elastic force in the direction in which the steering wing 200 is deployed to serve to unfold the steering wing 200.

That is, the elastic body can be positioned in a variety of well-known structures that are compressed by the steering blade 200 in a state where the steering blade 200 is folded and absorbed or accumulated energy, and according to the structure, the coil spring and plate It turns out that it can be carried out with various known springs, such as springs and return springs installed on shafts.

The steering wing 200 is hung by the wing stopper part 300 within the burnt body 100 and folded in a compressed state, and the wing stopper part 300 is an inner surface of the wing opening 110 It includes a stopper protrusion 310 which is located on and supports the steering wing 200 by hanging.

In addition, the wing stopper unit 300 further includes a wing position adjusting unit 500 that positions the steering wing 200 so that the steering wing 200 is positioned in a twisted state, and aligns the steering wing 200 to a deployed position. do.

The steering wing 200 is positioned to be caught by the stopper protrusion 310 in a twisted state by the wing position adjusting unit 500, and is aligned to the deployed position by the wing position adjusting unit 500 after the guided weapon is fired.

The stopper protrusion 310 restrains the deployment of the steering wing 200 by supporting the front blade of the folded steering wing 200.

The wing position adjustment unit 500 is rotated by receiving rotational force from the rotating motor 510, the electric gear member 520 positioned on the shaft of the rotating motor 510, and the electric gear member 520 to develop the steering wing 200 It includes a blade alignment member 530 to align the position.

The wing position adjustment unit 500 further includes a power transmission body that transmits the rotational force of the electric gear member 520 to the wing alignment member 530.

The power transmission body 540 is connected to the rotating shafts of the spur gear member 541 and the spur gear member 541 that are rotated by being engaged with the electric gear member 520 and is rotated by receiving rotational force from the spur gear member 541 As an example, a worm gear member 542 is included, and the blade alignment member 530 is a worm wheel gear positioned on an outer circumferential surface by a gear tooth rotated by the worm gear member 542.

On the front surface of the wing alignment member 530, the wing support member 400 is positioned to be rotated to both sides of the erected wing 200.

And, although not shown on the front surface of the wing alignment member 530, the rear of the wing support member 400 is supported to be positioned in a deployed position so that the aligned steering blade 200 is twisted to be caught by the stopper protrusion 310, and the wing When the alignment member 530 is rotated, a cam structure is positioned so that the steering wing 200 is erected back to the deployed position.

The cam structure inclines the steering wing 200 erected to the deployed position to be caught by the stopper protrusion 310, and when the wing alignment member 530 rotates, the steering wing 200 is again erected to the deployed position to align the stopper protrusion. It will be noted that a more detailed description is omitted as it may be carried out by using a variety of known cam structures that can be positioned so as not to be caught in the 310.

The wing position adjustment unit 500 may further include a wing position detection unit 550 that detects the twisted position of the steering wing 200.

The wing position detection unit 550 is variously modified to a known angle detection sensor capable of detecting the angle at which the steering wing 200 is twisted based on the reference position, that is, the erected position of the steering wing 200. It is noted that further detailed descriptions that may be practiced are omitted.

The wing position detection unit 550 detects the twisted angle of the steering wing 200 and transmits it to a control unit that controls the operation of the rotary motor 510, and the control unit controls the steering wing 200 from the wing position detection unit 550 The operation of the rotating motor 510 is controlled by the operation of the rotating motor 510 by receiving the twisted angle of the steering wheel 200 so that the steering wing 200 can be accurately aligned with the deployed position.

That is, the steering blade 200 can be accurately rearranged to the deployed position by the operation of the rotating motor 510 in a twisted state.

Meanwhile, the wing stopper part 300 may further include a wing deployment preventing part 320 that supports a side surface of the steering wing 200 to maintain the twisted position of the steering wing 200.

The wing deployment prevention unit 320 is supported by the control wing 200 by twisting the side of the steering wing 200 material in a state where the steering wing 200 is twisted and caught by the stopper protrusion 310 so that the steering wing 200 is driven by the stopper protrusion 310. Make sure that it is firmly positioned in the suspended state.

The wing deployment prevention unit 320 limits the alignment of the steering wing 200 to the deployment position by supporting the position of the twisted steering wing 200, and the steering wing 200 is hung by the stopper protrusion 310 By allowing the deployment to be maintained in a prevented state in the dark state, the steering blade 200 can be prevented from being unintentionally aligned to the deployed position without being caught by the stopper protrusion 310.

The wing deployment prevention unit 320 releases the locking state of the steering wing 200 while retracting by the reverse inertia force generated after the launch of the guided weapon.

3 is a view showing the wing deployment preventing unit 320 in one embodiment of the apparatus for deploying a steering wing 200 for a guided weapon according to the present invention. Referring to FIG. 3, the wing deployment preventing unit 320 is a stopper housing ( 321), a side support pin member 322 protruding from the stopper housing 321 and supporting a side of the twisted steering blade 200 and being retracted by a reverse inertia force and inserted into the stopper housing 321, a side support pin member ( 322) may include a first spring member 323 that elastically supports.

The side support pin member 322 is elastically supported by the first spring member 323 and positioned to protrude outward of the stopper housing 321, so that the protruding portion is twisted to support the side of the control blade 200 positioned. .

Then, the side support pin member 322 is retracted by the reverse inertia force generated when the guided weapon is fired, and is compressed into the pin support spring while being inserted into the stopper housing 321 to release the side jam of the steering wing 200. do.

When the guided weapon is released, a reverse inertia force is generated as a resistance to the rapid acceleration zone of the guided weapon, and the side support pin member 322 moves in the direction of the reverse inertia force generated by the reverse inertia force, that is, retracts.

In addition, the wing deployment prevention unit 320 is a second stopper member 324, the second stopper elastically supporting the pin stopper member 324 is positioned to support the side of the side support pin member 322 within the stopper housing 321 A spring member 325 may be further included.

Then, the pin stopper member 324 is moved to the elastic restoring force of the second spring member 325 when the side support pin member 322 is inserted into the stopper housing 321, the side support pin member in the stopper housing 321 The pin hole 321c through which the 322 passes is blocked.

The stopper housing 321 is positioned in the vertical direction with the first housing part 321a, the first housing part 321a in which the side support pin member 322 is inserted and movable, and the pin stopper member 324 moves It includes a second housing portion 321b that is positioned as possible.

The first housing part 321a has an outer surface of the side support pin member 322 supported on an inner surface to guide linear movement of the side support pin member 322, and the second housing part 321b has a pin stopper member ( The outer surface of 324) is supported on the inner surface to guide the linear movement of the pin stopper member 324.

4 and 5 is a view showing an example of operation of the wing deployment prevention unit 320 in one embodiment of the deployment apparatus for a control blade 200 for a guided weapon according to the present invention.

4 shows an example in which the side support pin member 322 is retracted and inserted into the stopper housing 321 by a reverse inertia force after the launch of the guided weapon.

Figure 5 is a pin stopper member 324 is a pin hole 321c of the stopper housing 321 in the state in which the side support pin member 322 is retracted and inserted into the stopper housing 321 by the reverse inertia force after the launch of the guided weapon. It shows an example that is positioned to block.

The side support pin member 322 protrudes through the pin hole 321c of the stopper housing 321 and supports the side of the steering blade 200 positioned to be twisted and twisted.

That is, referring to FIGS. 4 and 5, the side support pin member 322 releases the jamming of the steering blade 200 while being inserted into the first housing portion 321a by the reverse inertia force after the launch of the guided weapon, The pin stopper member 324 moves along the second housing portion 321b by the elastic restoring force of the second spring member 325 after the side support pin member 322 is inserted into the first housing portion 321a. The pin hole 321c of the housing 321 is closed.

At this time, the side support pin member 322 is supported so that the end portion pushes and supports the lower surface of the pin stopper member 324 and is restricted by movement by the pin stopper member 324 so as not to protrude again into the pin hole 321c. 1 is bound within the housing.

As a result, the side support pin member 322 protrudes through the pin hole 321c so that it does not return to the position where the steering wing 200 is restrained.

On the other hand, Figures 6 and 7 is a view illustrating a state in which the steering blade 200 is arranged to be deployed in one embodiment of the apparatus for deploying a steering blade 200 for a guided weapon according to the present invention, and FIG. 8 is the present invention. It is a diagram showing an example in which the steering wing 200 is deployed in one embodiment of the deployment device of the steering wing 200 for a guided weapon according to the present invention.

6 shows an example in which the side support pin member 322 is inserted into the stopper housing 321 by the reverse inertia force after the launch of the guided weapon, and the jamming on the side of the steering wing 200 is released.

7 shows an example in which the steering blade 200 is erected and arranged in the deployed position by the operation of the wing position adjusting unit 500.

That is, referring to FIGS. 6 and 7, as the side support pin member 322 is inserted into the stopper housing 321 by the reverse inertia force after the launch of the guided weapon, the jamming on the side of the steering wing 200 is released, and the wing The steering wing 200 is erected and aligned to the deployed position by the position adjusting unit 500.

And, as shown in FIG. 7, when the steering wing 200 is finally arranged and arranged in the deployed position, the body 100 is burned through the opening 110 for wing deployment by being rotated and deployed as in FIG. 8 with the elastic restoring force of the elastic body. Will protrude to the outside.

On the other hand, Figure 9 is a flow chart showing an embodiment of a method of deploying a steering wing 200 for a guided weapon according to the present invention, and referring to Figures 2, 3, 6 to 9 for a guided weapon according to the present invention One embodiment of the method of deploying the steering wing will be described in detail below.

One embodiment of the method of deploying a steering blade for a guided weapon according to the present invention is twisted based on the deployed position in the bullet body 100, is supported by the stopper protrusion 310, is positioned in a folded state, and is deployed with elastic restoring force of the elastic body It is a deployment method of the steering wing 200, a guided weapon launching step (S100), a deployment command receiving step (S300), and a deployment command receiving step receiving a deployment command of the control wing 200 at a control point after the guided weapon is launched (S300) S300) with the deployment command received by positioning the steering blade 200 to the deployed position, the steering blade alignment step (S400) for releasing the steering blade 200 from the stopper protrusion 310 hanging from the stopper protrusion 310 and the elastic blade's elastic restoring force It includes a wing deployment step (S500) to which the 200 is deployed.

In addition, the method of deploying a steering wing for a guided weapon is a wing side restraint release step (S200) of releasing the restraint of the wing deployment prevention unit 320 supporting the side of the control wing 200 by supporting the deployment command after the launching of the guided weapon. ) May be further included.

The wing side restraint step (S200) retracts the side surface of the control wing 200 by retracting the side support pin member 322 supporting the side of the control wing 200 by the reverse inertia force generated by the launch of the guided weapon. Release the restraint.

That is, the steering blade 200 is supported by the stopper protrusion 310 while the front blade is hung in the deployed position in a folded state within the burnt body 100, and the side supports the side of the wing deployment preventing part 320 It is hung and supported by the pin member 322.

The side support pin member 322 of the wing deployment preventing part 320 supports the side of the steering blade 200 positioned twisted in the deployed position to constrain the twisted position of the steering wing 200, and to launch a guided weapon. It is retracted by the reverse inertia force generated due to being inserted into the stopper housing 321 to release the restraint on the twisted position of the steering wing 200, and the steering wing 200 is twisted by the operation of the wing position adjusting unit 500 In the upright position, it can be aligned.

Then, when the steering blade 200 is erected and aligned to the deployed position by the operation of the wing position adjusting unit 500, the restraint by the stopper protrusion 310 is automatically released, and the steering wing 200 is deployed by the elastic restoring force of the elastic body. do.

The present invention prevents the accidental deployment of the steering wing 200, and allows the steering wing 200 to be deployed only when the guided weapon is actually operated. By preventing the unnecessary consumption of guided weapons, it has the effect of significantly improving the operational efficiency of guided weapons.

The present invention prevents the accidental deployment of the steering wing 200 and allows the steering wing 200 to be accurately deployed at the time of maneuvering the guided weapon, so that the guided weapon can strike the target accurately, greatly increasing the accuracy of the guided weapon. And improve reliability when operating guided weapons.

In addition, the present invention secures the operational reliability of the wing deployment prevention unit 320 by operating the wing deployment prevention unit 320 by using the reverse inertia force generated when the guided weapon is fired without an additional power device, and within the bullet body 100 It has the effect of maximizing space utilization.

The present invention is not limited to the above-described embodiments, but can be implemented by variously changing within a range not departing from the gist of the present invention, and it is revealed that it is included in the configuration of the present invention.

100: bullet body 110: wing opening for deployment
200: steering wing 210: wing hinge
300: wing stopper portion 310: stopper protrusion
320: wing development prevention portion 321: stopper housing
321a: 1st housing part 321b: 2nd housing part
321c: pin hole 322: side support pin member
323: first spring member 324: pin stopper member
325: second spring member 400: wing support member
410: hinge inserting part 420: blade rotation shaft
500: wing position adjustment unit 510: rotary motor
520: electric gear member 530: wing alignment member
540: power transmission body 541: spur gear member
542: worm gear member 550: wing position detection unit

Claims (18)

A bullet body in which a slot-shaped blade opening is located;
A steering blade rotatably positioned in the bullet body, elastically supported by an elastic body, and deployed by an elastic force of the elastic body; And
It includes a wing stopper portion to support the steering wing to be positioned in a folded state within the bullet body and to deploy the steering wing after the launch of the guided weapon,
A wing support member to which the steering blade is rotatably coupled is located inside the bullet body,
The steering wing is positioned in the state of being folded in a compressed state by being caught by the wing stopper in the burnt body,
The wing stopper portion includes a stopper protrusion that is located on an inner surface of the opening for spreading the wings and supports a steering wing.
The wing stopper portion further comprises a wing deployment prevention portion supporting a side surface of the steering blade to maintain the twisted position of the steering blade,
The wing deployment preventing portion is supported by hanging the side of the steering blade in a state where the steering blade is twisted and caught by the stopper protrusion, so that the steering blade is positioned in a suspended state by the stopper protrusion,
The wing deployment prevention unit is a retracting inertial force generated after the launch of the guided weapon, while retracting by the inertia force, the control wing deployment device for guided weapons characterized in that it releases the locked state.
delete delete The method according to claim 1,
The wing stopper portion is positioned so that the steering blade is twisted in the deployed position so that the control wing is caught by the stopper protrusion, and the steering wing is aligned to the deployed position to release the jamming of the steering wing. Steering wing deployment device for a guided weapon further comprising a position adjustment unit.
The method according to claim 4,
The wing position adjustment unit,
Rotating motor;
An electric gear member positioned on the shaft of the rotating motor; And
And a blade alignment member which receives rotational force from the electric gear member and is rotated to align the steering wing to the deployed position.
The method according to claim 5,
The blade position adjustment unit further comprises a power transmission body for transmitting the rotational force of the electric gear member to the blade alignment member steering wing deployment device for a guided weapon.
The method according to claim 6,
The power transmission body,
A spur gear member rotated in engagement with the electric gear member;
It comprises a worm gear member is connected to the rotating shaft of the spur gear member is rotated by receiving the rotational force from the spur gear member,
The blade alignment member is a worm gear member is rotated gear teeth that are engaged with the worm gear member is a worm wheel gear deployment device for a guided weapon, characterized in that located on the outer peripheral surface.
The method according to claim 5,
The wing position adjustment unit further comprises a wing position detection unit for detecting the twisted position of the steering wing steering wing deployment device for a guided weapon.
The method according to claim 8,
The wing position detection unit senses the twist angle of the steering blade and transmits it to a control unit that controls the operation of the rotary motor, and the control unit receives the twist angle of the steering wing from the wing position detection unit and receives the twist angle. A control wing deployment device for a guided weapon, characterized in that to control the operation of the rotary motor so that the control wing is erected to the deployment position.
delete delete delete The method according to claim 1,
The wing deployment prevention unit,
Stopper housing;
A side support pin member protruding from the stopper housing and supporting a twisted side surface of the steering blade and being retracted by a reverse inertia force and inserted into the stopper housing; And
And a first spring member elastically supporting the side support pin member.
The method according to claim 13,
The wing deployment prevention unit,
A pin stopper member positioned to support a side surface of the side support pin member in the stopper housing;
Further comprising a second spring member elastically supporting the pin stopper member,
When the side support pin member is inserted into the stopper housing member, the pin stopper member moves to an elastic restoring force of the second spring member to block a pin hole through which the side support pin member penetrates in the stopper housing. Control wing deployment device for guided weapons.
The method according to claim 14,
The stopper housing,
A first housing part in which the side support pin member is inserted and movably positioned; And
And a second housing portion positioned vertically to the first housing portion and movably positioned with the pin stopper member.
It is a deployment method of a steering blade that is twisted relative to the deployment position within the burnt body, supported by the stopper protrusion and folded, and deployed with the elastic restoring force of the elastic body,
A guided weapon firing step;
A deployment command receiving step of receiving a command to deploy a steering wing at a control point after the guided weapon is launched;
A steering wing alignment step of releasing the steering wing from the stopper protrusion by placing the steering wing into the deployed position with the deployment command received in the deployment command receiving step; And
Includes a wing deployment stage in which the steering wing is deployed with the elastic restoring force of the elastic body,
After the guided weapon launching step further comprises a wing side restraining step of releasing the restraint of the wing deployment preventing part by hanging and supporting the side surface of the steering blade before the deploying command receiving step,
The wing side restraining step is characterized in that the side support pin member supporting the side of the steering wing is retracted by the reverse inertia force generated by the firing of the guided weapon to release the restraint of supporting the side of the steering wing. The development method of the steering wing made with. delete delete

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