KR20100008135A - Apparatus for unlocking tin of missile - Google Patents

Apparatus for unlocking tin of missile Download PDF

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Publication number
KR20100008135A
KR20100008135A KR1020080068551A KR20080068551A KR20100008135A KR 20100008135 A KR20100008135 A KR 20100008135A KR 1020080068551 A KR1020080068551 A KR 1020080068551A KR 20080068551 A KR20080068551 A KR 20080068551A KR 20100008135 A KR20100008135 A KR 20100008135A
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KR
South Korea
Prior art keywords
missile
drive
coupled
blade
deployment device
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Application number
KR1020080068551A
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Korean (ko)
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KR100964987B1 (en
Inventor
이원영
Original Assignee
엘아이지넥스원 주식회사
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Application filed by 엘아이지넥스원 주식회사 filed Critical 엘아이지넥스원 주식회사
Priority to KR1020080068551A priority Critical patent/KR100964987B1/en
Publication of KR20100008135A publication Critical patent/KR20100008135A/en
Application granted granted Critical
Publication of KR100964987B1 publication Critical patent/KR100964987B1/en

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    • 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
    • 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

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

PURPOSE: A spreading device of a driving wing for a missile is provided to control the direction and location of the missile by spreading the driving wing at the moment of launching the missile. CONSTITUTION: A driving wing(10) is coupled to a missile body, and folded to the inner side of the missile body. A coupling pin(20) is coupled to the bottom end surface of the driving wing. A rod(30) is coupled to the top end of the coupling pin. A fixing bar is coupled to one side surface of the driving wing, and a piston(50) is coupled to the other side surface of the driving wing. An explosion bolt(60) is coupled to the piston. A second bushing(36) is formed between a first bushing(32) and a spring(34).

Description

Driveblade deployment device for guided missiles {Apparatus for unlocking tin of missile}

The present invention relates to a drive wing deployment device for guided missiles. More specifically, the present invention relates to a drive wing deployment device for guided missiles capable of rapidly deploying a drive vane for direction and position adjustment of a missile and not to be folded again after deployment.

In general, missiles are propelled by rockets or jet engines, and are guided weapons that are guided until the target is reached. The missile is a streamlined missile body and a missile that is formed in a streamline. It is divided into a fixed wing that serves to ensure the stability of the flight in the process of flying toward and a drive wing that is responsible for the direction and position control of the guided missile.

In particular, the drive wing is designed on the basis of aerodynamic considerations in order to enable the flight of guided missiles, the shape of which is mostly trapezoidal shape having a certain thickness.

Most missiles employ various aerodynamic surfaces for stability in shaping missiles, and components other than guided missiles, ie fixed wings and drives, to reduce the volume of missiles based on how missiles are loaded and fired. It is designed to be able to be deployed as needed when the wings are folded or folded inside the guided missile body.

In addition, guided missiles, which are generally mounted on the launching tubes and are fired toward the target, are fixed to the guided missiles and the driving wings are rapidly deployed immediately after the launching is made, and the guided missiles are supported. It must be delivered to the body.

Therefore, in order to minimize the aerodynamic drag of the high speed flying missile fixed wing, the deployment and fixing device for the missile drive blade should be installed in a narrow space inside the wing. It has been used as a motor or a hydraulic drive.

However, in the case of using a motor or a hydraulic drive device, the volume of the drive blade deployment device for guided missiles is large and the weight is also heavy, there is a problem that the transport and launch of guided missiles cannot be made efficiently.

In addition, the driving blades are not firmly fixed after being deployed, and the driving blades are folded again by an external force applied during the high-speed flight of the missiles, thereby causing a problem of flying obstacles of the missiles.

An object of the present invention is to provide a drive wing deployment device for guided missiles that can be developed to solve the problems as described above and to be able to quickly unfold after the deployment of the drive wing for adjusting the direction and position of the guided missile. It is done.

Drive wing deployment apparatus according to the present invention for achieving the above object is a drive wing deployment device for guided missile, drive blade coupled to the guided missile body and folded into the guided missile body; A coupling pin coupled to the bottom surface of the driving blade; A rod coupled to the distal end of the coupling pin; A fixed bar coupled to one side of the driving blade and preventing the driving blade from escaping to the outside of the missile body; A piston coupled to the other side of the drive vane; And an explosion bolt coupled to the piston.

In addition, the coupling pin may rotate to the outside of the missile body.

In addition, it may further include a spring coupled in a form surrounding the outer circumferential surface of the rod.

The apparatus may further include a first bushing coupled to one end of the rod and a second bushing coupled between the first bushing and the spring.

In addition, the rod has a first insertion groove is formed in the longitudinal direction, the line end of the coupling pin may be inserted into the first insertion groove.

In addition, the fixing bar has a second insertion groove is formed in the height direction, one side of the drive blade may be inserted into the second insertion groove.

In addition, the piston has a third insertion groove is formed in the longitudinal direction, the other side of the drive blade may be inserted into the third insertion groove.

According to the present invention, it is possible to reduce the weight of the missile using the explosive bolt as a driving device for the deployment of the drive blade, compared to the conventional motor or hydraulic drive device, so that the process of carrying and launching the missile is efficiently performed. Has an effect.

In addition, since the spring and the bushing prevent the drive blade from being folded back by the external force after the drive blade is deployed, the deployment state of the drive blade can be stably maintained.

In addition, since the driving blade is deployed at the moment when the guided missile mounted in the launch tube is released while the driving wing is folded, the guide blade is adjusted to the direction and position of the missile, so that the guided missile can accurately fly to the target.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. First of all, in adding reference numerals to the components of each drawing, it should be noted that the same reference numerals have the same reference numerals as much as possible even if displayed on different drawings. In addition, in describing the present invention, when it is determined that the detailed description of the related well-known configuration or function may obscure the gist of the present invention, the detailed description thereof will be omitted. In addition, preferred embodiments of the present invention will be described below, but the technical idea of the present invention may be implemented by those skilled in the art without being limited or limited thereto.

Figure 1a is a perspective view of a drive wing deployment device for a guided missile according to a preferred embodiment of the present invention, and Figure 1b is a partial perspective view of a drive wing deployment device for a guided missile according to a preferred embodiment of the present invention. As shown in Figure 1a and 1b drive blade deployment device 1 for a guided missile according to a preferred embodiment of the present invention 1 drive blade 10, coupling pin 20, rod 30, fixed bar 40 , Piston 50, and explosion bolt 60.

The drive blade 10 is restrained by the fixed bar 40 before the guided missile is fired toward the target, folded inside the base part B and the frame part F, and the base part when the guided missile is fired toward the target. (B) and the outside of the frame portion (F) is deployed to control the direction and position of the missile.

Coupling pin 20 is coupled to the lower surface of the drive blade 10 and the distal end of the coupling pin 20 is coupled to the rod 30 so that the drive blade 10 of the base portion (B) and the frame portion (F) In the process of developing to the outside, the base part B and the frame part F are rotated to the outside so that the driving blade 10 is developed to the outside of the base part B and the frame part F.

The rod 30 is coupled to the front end of the frame portion F and the coupling pin 20, and at one end of the rod 30, the driving blade 10 extends to the outside of the base portion B and the frame portion F. The first bushing 32 is then coupled to reduce the friction generated when rotating to adjust the direction and position of the missile.

In addition, the rod 30 is coupled to the spring 34 of the shape surrounding the outer circumferential surface of the rod 30, the spring 34 is the frame frame by the coupling pin 20 when the drive blade 10 is not in a deployed state Compressed to the inside of the portion (F), when the drive blade 10 is deployed to the outside of the base portion (B) and the frame portion (F) is restored to its original state by the elastic restoring force and the driven wing 10 ) Can be prevented from being folded inside the base portion B and the frame portion F by an external force received by the high-speed flight of the missile.

In addition, a second bushing 36 is coupled between the first bushing 32 and the spring 34 so that the driving blade 10 is extended to the outside of the base part B and the frame part F. 34) The restoring range is limited so that the drive blade 10 is deployed to a designated point, and the base blade B and the frame part F are developed by the external force received by the high-speed flight of the guided bomb. Can be prevented from being folded inward.

At this time, the coupling between the coupling pin 20 and the rod 30 may be made by the coupling pin 20 is inserted into the first insertion groove 38 formed in the longitudinal direction of the rod (30).

The fixed bar 40 is coupled to one side of the drive blade 10 and the drive blade 10 is fixed to the drive blade 10 is folded inward to the base portion (B) and the frame portion (F) drive blades for guided missiles. It is prevented from developing out of the base part B and the frame part F by the impact applied externally regardless of the operation | movement of the deployment apparatus 1.

At this time, the coupling between the fixed bar 40 and the drive blade 10 is made by inserting and coupling one side surface of the drive blade 10 to the second insertion groove 42 formed in the height direction of the fixed bar 40, Bar 40 is coupled to the shear pin 44, one side is coupled to the frame portion (F) is constrained to the frame portion (F).

The piston 50 is located inside the base portion B and is coupled to the other side of the drive blade 10. The drive blade deployment device 1 for guided missiles operates to drive the drive blade 10 to the base portion B and the frame portion ( When it is deployed to the outside of the F) by operating to the outside of the base portion (B) by pressing the fixed bar 40 by separating the fixed bar 40 from the drive wing deployment device 1 for guided missiles driving blade 10 Is developed to the outside of the base portion (B) and the frame portion (F).

At this time, the coupling between the piston 50 and the drive blade 10 may be made by inserting the drive blade 10 is inserted into the third insertion groove 52 formed in the longitudinal direction of the piston 50.

In addition, the third insertion groove 52 is formed longer than the side length of the drive blade 10 so that the piston 50 is fixed bar 40 when the drive blade 10 is deployed to the outside of the missile body (B). In the process of pressurizing the), it is possible to prevent damage to the drive blade 10.

The explosion bolt 60 is located inside the base portion B, and is coupled to the piston 50, and the drive blade deployment device 1 for the missile is operated so that the drive blade 10 is the base portion B and the frame portion F. When it is deployed to the outside of the instantaneous operation to increase the pressure inside the base portion (B) to operate the piston 50 to the outside of the base portion (B), the operated piston 50 is fixed bar 40 As a result of hitting the shear pin 42 is broken and the coupling between the fixed bar 40 and the frame portion (F) is dismantled, the binding force of the fixed bar 40 is lost, thereby compressing the inside of the frame portion (F) The spring 34 is operated to develop the drive vane 10.

Here, the explosion bolt 60 is a structure having a direction of the explosion and after inserting the gunpowder into the inside of the bolt to have a weak structure to have a directional direction on one side and the structure that combines the ignition line on the other side and when the ignition line is ignited inside The piston is operated by generating a gas of high temperature and high pressure in a direction having a weak structure by the explosion of the gunpowder inserted into it. Such explosion bolts are used for various purposes with different internal structures, and the emergency escape system of the fighter is an example using explosion bolts.

Figure 2 is a perspective view of a state in which the drive blade deployed by operating the drive blade deployment device for guided missile according to a preferred embodiment of the present invention.

The operation process of the drive wing deployment device 1 for guided missile according to the preferred embodiment of the present invention is as follows.

First, when the drive wing deployment device 1 for guided missiles operates, the explosion bolt 60 is exploded. When the explosion bolt 60 is exploded, the piston 50 coupled to the base portion B hits the fixed bar 40 by the explosive force, thereby fixing the fixed bar 40 to the frame portion F. The shear pin 44 that has been removed is separated from the frame portion F. FIG.

When the fixing bar 40 is separated from the frame portion F, the coupling pin 20 is rotated to the outside of the frame portion F, and accordingly, the coupling pin 20 is pressed into the guided coal body B by the coupling pin 20. Spring 34 was restored to the outside of the missile body (B) by the elastic restoring force so that the driving blade 10 folded inward of the base portion (B) and the frame portion (F) is rotated the coupling pin (20) It rotates to the outer side of the base part B and the frame part F coaxially.

When the rotation of the coupling pin 20 is completed and the drive blade 10 is deployed to the outside of the base portion (B) and the frame portion (F), the second is coupled between the first bushing 32 and the spring 34 The bushing 36 limits the restoring range of the spring 34 such that the drive vane 10 is deployed by a predetermined position and is driven by external force while the guided missile is flying towards the target by the spring 34 and the second bushing 36. The phenomenon in which the driving blade 10 is folded inside the base portion B and the frame portion F is prevented, so that the deployment state of the driving blade 10 can be continuously maintained.

In the drive wing deployment device 1 for guided missile of the present invention, the drive wing 10 is folded into the base part B and the frame part F and restrained by the fixing bar 40 before the missile is launched. In the launch pad.

When the guided missile is fired toward the target, the drive wing deployment device 1 for the guided missile operates, and the explosion bolt 60 explodes to operate the piston 50 to move the fixed bar 40 to the base part B and the frame part F. The coupling pin 20 is rotated to the outside of the frame portion (F) so that the drive blade 10 is deployed out of the base portion (B) and the frame portion (F).

Therefore, after the guided missile is fired, the driving wing 10 is rapidly deployed, so that the direction and position of the guided missile can be adjusted, so that the guided missile can be accurately flying to the target.

In addition, since the explosion bolt 60 is used as the driving device for the deployment of the driving blade 10, the weight of the missile can be reduced compared to the conventional use of the motor or the hydraulic driving device, thereby efficiently transporting and launching the missile. It has the effect possible to be achieved.

In addition, after the driving blade 10 of the spring 34 and the second bushing 36 coupled to the rod 30 are deployed, the driving blade 10 is again driven by the external force to the base portion B and the frame. Since the folding of the part F is prevented, the deployment state of the driving blade 10 can be stably maintained during the flight of the missile.

The above description is merely illustrative of the technical idea of the present invention, and various modifications, changes, and substitutions may be made by those skilled in the art without departing from the essential characteristics of the present invention. It will be possible. Accordingly, the embodiments disclosed in the present invention and the accompanying drawings are not intended to limit the technical spirit of the present invention but to describe the present invention, and the scope of the technical idea of the present invention is not limited by the embodiments and the accompanying drawings. . The protection scope of the present invention should be interpreted by the following claims, and all technical ideas within the scope equivalent thereto should be construed as being included in the scope of the present invention.

According to the present invention, since the explosive bolt is used as the driving device for the development of the driving blade, it is possible to reduce the weight of the missile, so that the transport and launching process of the missile is efficient, so that the conventional driving blade deployment device for the missile may be utilized.

Figure 1a is a perspective view of a drive wing deployment device for guided missile according to a preferred embodiment of the present invention,

Figure 1b is a partial perspective view of the drive blade deployment device for guided missile according to a preferred embodiment of the present invention, and

Figure 2 is a partial perspective view of a state in which the driving blade deployed by operating the drive blade deployment device for guided missile according to a preferred embodiment of the present invention.

<Brief description of the main parts of the drawings>

(1): drive wing deployment device for guided missile 10: drive wing

(20): coupling pin (30): rod

(32): first bushing (34): spring

(36): second bushing (38): first insertion groove

(40): fixing bar (42): second insertion groove

(44): shear pin 50: piston

(52): third insertion groove

Claims (7)

In the drive blade deployment device for guided missiles, A drive wing coupled to the missile body and folded into the missile body; A coupling pin coupled to the bottom surface of the driving blade; A rod coupled to the distal end of the coupling pin; A fixed bar coupled to one side of the driving blade and preventing the driving blade from escaping to the outside of the missile body; A piston coupled to the other side of the drive vane; And Drive blade deployment device for missiles, characterized in that it comprises an explosion bolt coupled to the piston. The method of claim 1, The coupling pin, Drive blade deployment device for guided missiles, characterized in that rotated to the outside of the guided missile body. The method of claim 1, Drive wing deployment device for a missile, characterized in that it further comprises a spring coupled in a form surrounding the outer circumferential surface of the rod. The method of claim 3, wherein And a first bushing coupled to one end of the rod, and a second bushing coupled between the first bushing and the spring. The method of claim 1, The rod is, The first insertion groove is formed in the longitudinal direction, the driving blade deployment device for guided missiles, characterized in that the front end portion of the coupling pin is inserted into the first insertion groove. The method of claim 1, The fixing bar, The second insertion groove is formed in the height direction, one side of the drive blade is inserted into the second insertion groove drive blade deployment device for a missile. The method of claim 1, The piston, The third insertion groove is formed in the longitudinal direction, the other side of the drive blade is inserted into the third insertion groove drive vane deployment device for the missile.
KR1020080068551A 2008-07-15 2008-07-15 Apparatus for unlocking tin of missile KR100964987B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020080068551A KR100964987B1 (en) 2008-07-15 2008-07-15 Apparatus for unlocking tin of missile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020080068551A KR100964987B1 (en) 2008-07-15 2008-07-15 Apparatus for unlocking tin of missile

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KR20100008135A true KR20100008135A (en) 2010-01-25
KR100964987B1 KR100964987B1 (en) 2010-06-21

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Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6446906B1 (en) * 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system
US6880780B1 (en) * 2003-03-17 2005-04-19 General Dynamics Ordnance And Tactical Systems, Inc. Cover ejection and fin deployment system for a gun-launched projectile
US7475846B2 (en) * 2005-10-05 2009-01-13 General Dynamics Ordnance And Tactical Systems, Inc. Fin retention and deployment mechanism

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