KR102135717B1 - Holding apparatus for inspection of guided missile - Google Patents

Abstract

The present invention relates to a fixing device for inspecting a guided missile, a first guided grenade fixing part to which one side of the guided grenade is seated and fixed, and a second guided grenade fixed to be spaced apart from the first guided grenade fixing part and fixed to the other side of the guided grenade Including the first launcher fixed portion is fixed to one side of the launcher where the assembled missile is charged and fixed, the second launcher fixed portion is located spaced apart from the first launcher fixed portion and the other side of the launcher is seated and fixed During the assembly of guided missiles, each of the modified shapes of guided missiles can be fixed, so it is possible to smoothly inspect guided missiles during the guided missile assembly process, thereby reducing the time required to inspect guided missiles and reducing the number of personnel required. In addition to increasing safety and convenience, it is possible to position the mechanical positions of components in the same position during the inspection work at each assembly stage of guided missiles, providing an advantageous environment for checking the mechanical characteristics, making and manufacturing inspection software. It can increase the convenience of operation.

Description

Fixed device for checking missiles {HOLDING APPARATUS FOR INSPECTION OF GUIDED MISSILE}

The present invention relates to a fixing device for inspecting a guided missile, and more particularly, to a fixing device for inspecting a guided missile that can be fixed by mounting a guided missile to enable inspection of a guided missile during each assembly process during assembly of a guided missile.

In general, the guided grenade is manufactured in a large form with three pieces of equipment, which is a ratio of the length to the cross-sectional area, and the divided plurality of guided munition bodies are placed in a line on the guided grenade assembly table and then assembled by moving the plurality of divided bodies in a straight line.

That is, the conventional guided grenade assembly supports a plurality of divided guided grenade bodies and has a plurality of guided grenade supports that can be reciprocated in a straight line and moveable up and down on the assembly base, and each guided grenade body is placed and aligned on the guided grenade support. Afterwards, the divided guide grenade body is moved and assembled.

As a prior patent related to the present invention, Korean Patent Registration No. 1708001'Guide Weapons Assembly Device' has been proposed.

Korean Patent Registration No. 1708001'Guide Weapons Assembly Device' is an invention including a slider which is installed to penetrate the fuselage arranged on the assembly table and inserts an internal part by pushing it into another fuselage.

In the assembly process, the parts of the missile, whether the missile is normally assembled, and the operation of the missile are checked according to the assembly stage.

However, the Korean Patent Registration No. 1708001'Guide Weapons Assembly Device' mounts and assembles each part for assembly, but it can fix guided missiles of various shapes that occur depending on the degree of assembly during the guided missile inspection procedure at each assembly stage of guided missiles. There was no problem.

In addition, when assembling the missile, each existing fixed-shaped jig caused a problem that physical elements such as the length and outer diameter of each missile could not be changed.

To this end, a separate fixing device for inspection of guided missiles was prepared according to the shape of guided missiles in each assembly step for inspection of guided missiles in each assembly step, but the entire fixing device was repeatedly changed and installed according to the shape of guided missiles changed by the inspection procedure. Had to.

However, due to the size of the missile, the size of the fixing device for the inspection of the missile increased, causing safety problems due to installation and dismantling work and management problems of a large number of fixing devices.

In addition, the relative position of the components compared to the inspection table that occurred while manufacturing the dedicated guide missile inspection fixtures according to each shape in the assembly stage of the missile is continuously changed to improve the relative position of the components according to each fixture in the SW of the inspection equipment. Added the task of changing and inputting, and it is difficult to manage these numbers separately.

The difficulty and complexity of installing and dismantling the fixed equipment for the inspection of the guided missiles caused delays in the guided missile inspection process due to the increased time and human resource consumption caused by the repeated replacement of the fixtures as the number of inspected missiles increased. Did.

This caused a problem that the efficiency of the missile inspection was reduced and the efficiency of the production of the missile was deteriorated.

0001) Korea Patent Registration No. 1708001'Guide weapon assembly device' (2017.02.13. registration)

An object of the present invention is to provide a fixing device for inspecting a guided missile that can smoothly conduct a guided missile inspection in the process of assembling guided missiles because each of the modified shapes of the guided missiles can be fixed during assembly of the guided missile.

Another object of the present invention is to provide a favorable environment for inspection to grasp the mechanical characteristics by positioning the mechanical position of the components at the same time during the inspection operation at each assembly step of the guided munition, and the production and operation of inspection software It is to provide a fixing device for inspecting a guided missile that increases convenience.

In order to achieve the above object of the present invention, an embodiment of the fixing device for inspecting guided missiles according to the present invention is positioned to be spaced apart from a first guided grenade fixing part fixed to one side of a guided grenade and fixed. A second guided grenade fixing part on which the other side of the guided grenade is seated and fixed, a first launcher fixed portion on which one side of the launcher where the assembled guided grenade is loaded and fixed, is spaced apart from the first launcher fixed portion and positioned on the other side of the launcher It characterized in that it comprises a second launcher fixed to be seated and fixed.

In the present invention, the first guide grenade fixing part is a first guide grenade clamping member in which a first guide grenade insert that surrounds a part of the body of the guided grenade is located, and a second guide grenade insert that wraps the rest of the body of the guide grenade is located and clamping the first guide grenade A second guided grenade clamping member is detachably coupled to the member, and the second guided grenade fixing part surrounds a third guided grenade clamping member and a guided grenade fuselage body in which a third guided grenade insert is wrapped around a portion of the body of the guided grenade A fourth guided grenade clamping member may be provided, wherein a fourth guided grenade insert is positioned and detachably coupled to the third guided grenade clamping member.

In the present invention, the first blasting tube fixing part is a first blasting tube clamping member in which a first blasting tube inserting part surrounding a part of the blasting tube and a second blasting tube inserting part surrounding the rest of the blasting tube are positioned and detachably detachable from the first blasting tube clamping member A second launcher clamping member is coupled, and the second launcher clamping part is positioned at a third launcher clamping member surrounding a portion of the launcher, and a fourth launcher insertion section surrounding the rest of the launcher, and the second It may include a fourth launching tube clamping member detachably coupled to the three launching tube clamping member.

An embodiment of the fixing device for inspecting guided missiles according to the present invention is fixed by being equipped with a first base part fixed with the first guided grenade fixed portion and a first launcher fixed portion and a second grenade fixed portion and a second launcher fixed portion mounted with a fixed It may further include a second base portion.

In the present invention, in the first base portion, the first guided grenade fixing portion is positioned to be movable up and down, and in the second base portion, the second guided grenade fixing portion is positioned to be movable up and down, and the first launcher fixed portion is located. It can be fixed by mounting the launch tube to the second launch tube fixing portion.

An embodiment of the fixing device for inspecting guided missiles according to the present invention is equipped with a first base part fixed with the first guided grenade fixed part and the first launcher fixed part, and a second guided grenade fixed part and the second launcher fixed part mounted It further comprises a second base portion to be fixed, the first base portion is located on both sides of the first guided grenade clamping member through the first guided grenade clamping member to guide the movement of the first guided grenade clamping member up and down A first elevating guide bar member is provided, and the second base portion is positioned on both sides of the third guided grenade clamping member to penetrate the third guided grenade clamping member to move up and down of the third guided grenade clamping member. A second elevating guide bar member for guiding may be provided.

In the present invention, a first clamping stopper portion to which movement of the first guided ammunition clamping member is restricted is located at an upper end of the first descending guide bar member, and the first guided ball clamping is provided at a lower end of the first descending guide bar member. A first clamping support portion to which a member is seated is located, and a second clamping stopper portion to which movement of the third guided bullet clamping member is restricted is located at an upper portion of the second elevating guide rod member, and the second elevating guide rod A second clamping support portion to which the third guided bullet clamping member is seated may be located at a lower portion of the member.

An embodiment of the fixing device for inspecting guided missiles according to the present invention is equipped with a first base part fixed with the first guided grenade fixed part and the first launcher fixed part, and a second guided grenade fixed part and the second launcher fixed part mounted It further comprises a second base portion to be fixed, the first guided grenade clamping member is a first movable body positioned to be movable up and down on the first base portion and movable up and down on the upper portion of the first movable body And a second moving body in which a first guided grenade insert is positioned to move up and down by a first elevating unit and surrounds a portion of the body of the guided grenade, wherein the third guided grenade clamping member is placed on the second base. Inserting a third guided grenade that is positioned to be movable downward and upward, and to be moved up and down on the upper portion of the third movable body and is moved up and down by a second elevating unit and surrounding a part of the fuselage's fuselage It may include a fourth movable body positioned additionally.

In the present invention, the first elevating unit is positioned on the first movable body to be rotatably positioned and screwed to the second movable body to rotate and rotate to rotate the first movable body according to the direction of rotation. It includes a descending screw, the second elevating portion is rotatably positioned on the third movable body and is screwed to the fourth movable body to rotate and rotate the fourth movable body according to the direction of rotation. It may include a two clamping lifting screw.

In the present invention, the first elevating unit further includes a first elevating operation member that is rotatably positioned on the first movable body and protrudes outward and generates rotational force to operate the first clamping elevating screw. , The second elevating portion may further include a second elevating operation member that is rotatably positioned on the third movable body and protrudes outward and generates a rotational force to operate the second clamping elevating screw. .

In the present invention, the first elevating unit further includes a first elevating and rotating motor that operates by receiving electrical power to rotate the first clamping elevating screw, and the second elevating unit is operated by receiving electrical power. The second clamping lowering and rotating motor for rotating the lifting screw may further include.

An embodiment of the fixing device for inspecting guided missiles according to the present invention includes a first linear moving part that enables left and right movement of the first base part and a second linear motion that enables left and right movement of the second base part. It may further include wealth.

In the present invention, the first linear moving portion includes a first linear moving guide rail member that is movably coupled to the first base portion and is positioned in a circumferential direction of a guided missile or projectile to guide linear movement of the first base portion, wherein the The second linear moving portion may include a second linear moving guide rail member that is movably coupled to the second base portion and is positioned in a circumferential direction of a guided missile or projectile to guide linear movement of the second base portion.

One embodiment of the fixing device for inspecting guided missiles according to the present invention may further include a longitudinal linear moving part that enables front and rear movement of the first base part and the second base part.

One embodiment of the fixing device for inspecting guided missiles according to the present invention further includes a longitudinal linear moving part enabling front and rear movement of the first base part and the second base part, wherein the longitudinal straight moving part comprises the first A rail connecting member connecting the 1 linear moving guide rail member and the second linear moving guide rail member and the rail connecting member are movably coupled and positioned in the longitudinal direction of a guided missile or projectile to guide the linear movement of the rail connecting member It may include a longitudinal movement guide rail member.

One embodiment of the fixing device for inspecting guided missiles according to the present invention is one end detachably coupled to the first blasting tube fixing part, the other end detachably coupled to the second blasting tube fixing part, and inserted and mounted inside the guided bullet It may further include a component support that can be mounted to seat the internal parts of the guided missile.

One embodiment of the fixing device for inspecting guided missiles according to the present invention is one end detachably coupled to the first blasting tube fixing part, the other end detachably coupled to the second blasting tube fixing part, and inserted and mounted inside the guided bullet It further includes a component support portion that can be mounted to seat the internal parts of the guided missile, the component support portion is located on the one side of the component support member, the component support member provided with a component insertion space of the open top type A first fuselage coupling member that is detachably coupled to the first blasting tube clamping member and capable of coupling a separated body of guided ammunition, is located on the other end side of the component supporting member, and is detachably coupled to a third blasting tube clamping member, A second fuselage coupling member capable of coupling the separated fuselage of the guided missile may be included.

In the present invention, both sides of the first fuselage coupling member are seated on the first blasting tube clamping member, and a first seating portion to be bolted is located, and on both sides of the second fuselage coupling member are seated on the third blasting tube clamping member. A second seating portion to be fastened may be located.

In the present invention, the component supporting member may have a component insertion space having a semi-circular cross section therein.

In the present invention, the first fuselage coupling member and the second fuselage coupling member are formed in a ring shape surrounding a portion of the fuselage but at least more than half of the fuselage so that the fuselage can be inserted and mounted therein.

In the present invention, the first guided grenade fixing part is a first guided grenade clamping member in which a first guided grenade insert that surrounds a portion of the body of the guided grenade is located, a second guided grenade insert that wraps the rest of the body of the guided grenade, and the first guided grenade clamping member A second guided grenade clamping member detachably coupled to the second guided grenade clamping member, a third guided grenade clamping member surrounding a portion of the fuselage of the guided grenade and a third guided grenade clamping member and a guided grenade fuselage A fourth guided grenade clamping member is provided with a fourth guided grenade insert and detachably coupled to the third guided grenade clamping member. The second auxiliary support is inserted and seated in the second guide grenade inserting portion of the second guided grenade clamping member on the outer side of the second fuselage coupling member. The part can be positioned to protrude.

In the present invention, the first auxiliary support portion has a curved surface having a curvature corresponding to the curvature of the first guided bullet inserting portion, and is seated in the first guided bullet inserting portion, and the second auxiliary support portion corresponds to the curvature of the second guided bullet inserting portion. It may have a curved surface having a curvature to be seated in the second guided grenade insert.

The present invention can be fixed to each of the deformed shape of the missile during the assembly of the missile, it is possible to smoothly inspect the missile during the assembly process of the missile, reducing the time required to inspect the missile and reducing the required workforce. This has the effect of increasing the safety and convenience of the inspection work.

The present invention provides a favorable environment for inspection to grasp the mechanical characteristics by increasing the mechanical position of components during the inspection operation at each assembly step of the guided missile, and increases the convenience of manufacturing and operating inspection software It is effective.

1 is a perspective view showing an embodiment of a fixing device for checking guided missiles according to the present invention.
2 and 3 is a perspective view showing an example of use for the fixing device for inspecting guided missiles according to the present invention.
Figure 4 is a perspective view showing an embodiment of a part receiving part in the fixing device for inspecting guided missiles according to the present invention.
Figure 5 is a perspective view showing an example of the use of the part support in the fixing device for inspecting guided missiles 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 construed as being limited to conventional or dictionary meanings. Therefore, the configuration shown in the embodiments and the drawings described in this specification are only the most preferred embodiments of the present invention and do not represent all of the technical spirit of the present invention, and thus can replace them at the time of application. It should be understood that there may be equivalents and variations.

1 is a perspective view showing an embodiment of a fixing device for inspecting a missile according to the present invention, and referring to FIG. 1, a fixing device for inspecting a guided missile according to the present invention is a first guided ball fixing part on which one side of a guided missile is seated and fixed It includes a second guided grenade fixed portion 200 which is spaced apart from the first guided grenade fixed portion 100 and the other side of the assembled guided missile seated and fixed.

For example, the first guided grenade fixing unit 100 and the second guided grenade fixing unit 200 have a structure capable of holding and fixing the body of the guided missile.

The first guided grenade fixing part 100 is a first guided grenade clamping member 110 in which a first guided grenade insert that surrounds a part of the body of the guided grenade is located, a second guided grenade insert that wraps the rest of the body of the guided grenade, and a first guided grenade And a second guided bullet clamping member 120 that is detachably coupled to the clamping member 110.

For example, the first guided grenade insert is formed in a semicircular shape surrounding half of the body of the guided missile, and the second guided grenade insert is formed in a semicircular shape surrounding the other half of the guided missile body.

In addition, the second guided grenade clamping member 120 is a semi-circular ring body, and the first flange portion 121 which is seated on the first guided grenade clamping member 110 on both sides and detachably coupled by bolt fastening is positioned, respectively.

The second guided grenade clamping member 120 is separated from the first guided grenade clamping member 110 by the first clamping fixing bolt 121a which penetrates the first flange portion 121 and is fastened to the first guided grenade clamping member 110. Possibly combined.

In addition, the second guided grenade fixing part 200 is a third guided grenade clamping member 210 in which a third guided grenade insert that surrounds a portion of the body of the guided grenade is located, and a fourth guided grenade insert that wraps the rest of the body of the guided grenade is located and is And a fourth guided grenade clamping member 220 detachably coupled to the third guided grenade clamping member 210.

For example, the third guided grenade insert is formed in a semicircular shape surrounding half of the body of the guided missile, and the fourth guided grenade insert is formed in a semicircular shape surrounding the other half of the guided missile body.

In addition, the fourth guided grenade clamping member 220 is a semi-circular ring body, the second guide portion 221 is seated on the third guided grenade clamping member 210 on both sides and detachably coupled by bolting.

The fourth guided grenade clamping member 220 penetrates the second flange portion 221 and is separated from the third guided grenade clamping member 210 by the second clamping fixing bolt 221a which is fastened to the third guided grenade clamping member 210. Possibly combined.

The guided ammunition is clamped between the first guided bullet clamping member 110 and the second guided bullet clamping member 120 on one side of the fuselage, and the position of the fuselage is fixed, and the other side of the fuselage has a third guided bullet clamping member 210 and a fourth guided bullet. It is clamped between the clamping members 220 so that its position is fixed.

And, on one side or the other side of the first guided grenade fixing unit 100 is located a first launcher fixed portion 300 is fixed to one side of the launch tube is loaded with the assembled guided missile.

In addition, a second launcher fixed portion 400 is located on one side or the other side of the second guided grenade fixing portion 200, the other side of the launcher is seated and fixed.

The first launcher fixation part 300 is located on the other side of the first grenade fixation part 100, and the second launcher fixation part 400 is located on one side of the second grenade fixation part 200 and the first grenade fixation part For example, it is located between the (100) and the second guided grenade 200.

As an example, the first launch tube fixing part 300 and the second launch tube fixing part 400 have a structure capable of holding and fixing the launch tube.

The first blast tube fixing part 300 includes a first blast tube clamping member 310 in which a first blast tube insertion part surrounding a part of the launcher tube is located, a second blast tube insertion part surrounding the rest of the launcher tube, and a first blast tube clamping member 310 It includes a second launch tube clamping member 320 that is detachably coupled to ).

As an example, the first injection tube inserting portion is formed in a semicircular shape surrounding half of the launching tube, and the second injection tube inserting portion is formed in a semicircular shape surrounding the other half of the launching tube body.

In addition, the second launching tube clamping member 320 is a semi-circular ring body, and a third flange portion 321 is mounted on both sides of the first launching tube clamping member 310 and detachably coupled by bolting.

The second launching tube clamping member 320 is separated from the first launching tube clamping member 310 by a third clamping fixing bolt 321a which penetrates through the first flange part 121 and is fastened to the first launching tube clamping member 310. Possibly combined.

In addition, the second launching tube fixing part 400 is a third launching tube clamping member 410 in which a third launching tube inserting part surrounding a part of the launching tube is located, and a fourth launching tube inserting part surrounding the rest of the launching tube is located and a third launching tube clamping member And a fourth launch tube clamping member 420 detachably coupled to the 410.

For example, the third injection tube inserting portion is formed in a semicircular shape surrounding half of the launch tube, and the fourth injection tube insertion portion is formed in a semicircular shape surrounding the other half of the fuselage tube.

In addition, the fourth launching tube clamping member 420 is a semi-circular ring body, the fourth flange portion 421 is seated on the third launching tube clamping member 410 on both sides and detachably coupled by bolt fastening, respectively.

The fourth launching tube clamping member 420 is separated from the third launching tube clamping member 410 by a fourth clamping fixing bolt 421a that penetrates through the second flange portion 221 and is fastened to the third launching tube clamping member 410. Possibly combined.

The launch tube is clamped between the first launch tube clamping member 310 and the second launch tube clamping member 320, and the position is fixed, and the other side of the fuselage has a third launch tube clamping member 410 and a fourth launch tube. The position is fixed by clamping between the clamping members 420.

The apparatus for checking guided missiles according to the present invention includes a first base unit 500 and a second guided grenade fixing unit 200 to which a first guided grenade fixing unit 100 and a first launcher fixing unit 300 are mounted and fixed. A second base part 600 to which the two launch tube fixing parts 400 are mounted and fixed may be further included.

The first guided grenade fixing part 100 and the first blasting tube fixing part 300 may be positioned to coincide with each other, and the second grenade fixing part 200 and the second blasting tube fixing part 400 coincide with each other. It can be positioned as much as possible.

The first blast tube fixing part 300 is positioned in close contact with the other side of the first grenade fixing part 100, and the second blast tube fixing part 400 is positioned in close contact with one side of the second grenade fixing part 200 Take that as an example.

In the first base portion 500, the first guided grenade fixing portion 100 is positioned to be movable up and down, and in the second base portion 600, the second guided grenade fixing portion 200 is positioned to be moved up and down. do.

In the first base portion 500, the first guided grenade clamping member 110 is positioned to be movable up and down, and in the second base portion 600, the third guided grenade clamping member 210 is positioned to be moved up and down. The first grenade clamping member 110 and the second grenade clamping member 120 are lowered when the launcher having a diameter larger than that of the body of the guided missile is fixed with the first blasting tube fixing part 300 and the second blasting tube fixing part 400 It can be placed in a position not caught by the launch tube.

The first base portion 500 is located on both sides of the first guided grenade clamping member 110 and is positioned to penetrate the first guided grenade clamping member 110 to guide the up and down movement of the first guided grenade clamping member 110 A first elevating guide bar member 510 may be provided.

A first clamping stopper portion 511 to which movement of the first guided bullet clamping member 110 is applied is located at an upper end of the first lifting guide bar member 510, and the first lifting guide bar member 510 The first clamping support portion 512 on which the first guided bullet clamping member 110 is seated is positioned at the lower portion.

The first guided bullet clamping member 110 is guided by the first lifting guide bar member 510 and vertically elevated and lowered, and the first launcher clamping member 310 at a top dead center applied to the first clamping stopper part 511 It is positioned higher so that the fuselage of the guided missile is seated without being caught by the first launch tube clamping member 310.

In addition, the first guided grenade clamping member 110 is located at the bottom dead center seated on the first clamping support portion 512, and the first launcher fixation part 300 and the second launcher fixation part have a launcher having a diameter larger than the body of the guided missile. When fixed with 400, it is positioned so as not to be caught by the launch tube.

The first guided grenade clamping member 110 is provided with a first clamping position fixture that secures a position at a top dead center, and the first clamping position fixture passes through the first guided grenade clamping member 110 to provide a first elevating guide bar member ( 510) It may be a set screw structure that pressurizes, and in addition, it can be carried out in various modifications by using other well-known structures of fixtures that can fix a position to be elevated.

The second base portion 600 is located on both sides of the third guided grenade clamping member 210 to penetrate the third guided grenade clamping member 210 to guide the up and down movement of the third guided grenade clamping member 210 A second elevating guide bar member 610 may be provided.

A second clamping stopper portion 611 to which movement of the third guided grenade clamping member 210 is applied is located at an upper end of the second elevating guide rod member 610, and of the second elevating guide rod member 610 The second clamping support portion 612 on which the third guided bullet clamping member 210 is seated is located at the lower portion.

The third guided grenade clamping member 210 is guided by the second elevating guide rod member 610 to vertically elevate, and the third launcher clamping member 410 at a top dead center applied to the second clamping stopper part 611 It is positioned higher so that the fuselage of the guided missile is seated without being caught by the third launching tube clamping member 410.

In addition, the third guided grenade clamping member 210 is located at the bottom dead center seated on the second clamping support portion 612, and the first launcher fixation part 300 and the second launcher fixation part are mounted on a launcher having a diameter larger than the body of the guided missile. When fixed with 400, it is positioned so as not to be caught by the launch tube.

The third guided grenade clamping member 210 is provided with a first clamping position fixture that secures a position at a top dead center, and the first clamping position fixture passes through the third guided grenade clamping member 210 and is a second elevating guide rod member ( 610) It may be a set screw structure that pressurizes, and in addition, it can be realized that it can be implemented in various modifications using structures of other known fasteners that can fix a position to be raised and lowered.

The first guided grenade clamping member 110 is a first movable body (that is, movably positioned on the first base portion 500), that is, movably positioned up and down on the first elevating guide bar member 510 ( 111), the first movable body 111 is positioned to be movable up and down, and moved up and down by the first elevating unit 700, and the first guided grenade insert that surrounds a part of the fuselage's fuselage is located. 2 may include a moving body (112).

In addition, the third guide grenade clamping member 210 is positioned to be movable up and down on the second base portion 600, that is, the third to be moved up and down on the second elevating guide bar member 610. A moving body 211, a third guided grenade inserting part positioned above and below the third moving body 211 and being moved up and down by the second elevating portion 800 and surrounding a part of the body of the guided missile It may include a fourth moving body 212 located.

The first moving body 111 is provided with a first moving part 700 for moving the second moving body 112 up and down, and a third moving body 211 is provided with a fourth moving body 212 for moving up and down. Two elevating and descending portions 800 may be located.

The first elevating and descending portion 700 is placed on the first movable body 111 and rotatably positioned, screwed to the second movable body 112 and rotated to move up and down the second movable body 112 according to the rotational direction. The first clamping elevating screw 710 may be included.

Then, the first elevating unit 700 is rotatably positioned on the first movable body 111 and is protruded outward, and the first elevating operation to generate a rotational force to operate the first clamping elevating screw 710. The member 720 may be further included.

Although the first elevating unit 700 is not shown, it is revealed that it may further include a first elevating rotary motor that is operated by receiving electric power to rotate the first clamping elevating screw 710.

The second lifting and descending part 800 is placed on the third moving body 211 and rotatably positioned, screwed to the fourth moving body 212 and rotated to move up and down the fourth moving body 212 according to the rotational direction. The second clamping may include an elevating screw (not shown).

In addition, the second elevating unit 800 is rotatably positioned on the third movable body 211 and is protruded to the outside, and the second elevating unit generates rotational force to operate the second clamping elevating screw (not shown). The operation member 820 may be further included.

The second clamping elevating screw (not shown) and the second elevating operation member 820 are not exactly shown in FIG. 1, but the first clamping elevating screw 710 and the first clamping elevating screw 710 can be confirmed. 1, it is confirmed that it can be carried out in the same manner as the configuration of the elevating operation member 720.

Although the second elevating unit 800 is not shown, it is revealed that it may further include a second elevating rotating motor (not shown) that operates by receiving electric power to rotate the second clamping elevating screw (not shown). .

The operator selectively rotates the first elevating operation member 720 and the second elevating operation member 820 in both directions to elevate or lower the second movable body 112 and the fourth movable body 212, respectively. The second moving body 112 and the fourth moving body 212 can be finely adjusted to fix the height of the second moving body 112 and the fourth moving body 212 by placing guided missiles.

The first elevating part 700 and the second elevating part 800 have a second moving body 112 provided with a first guided grenade insert which substantially raises the body of a guided missile and a third guided grenade insert with a fuselage of guided grenade. By finely adjusting the height of the fourth moving body 212 provided, it is convenient to inspect the location of the body of the guided missile when inspecting the guided missile, and to easily position the fuselage of the guided missile.

Although not shown, the first elevating part 700 and the second elevating part 800 may be hydraulic cylinders, or in addition, a recioning gear structure using a reciprocating gear that is linearly moved by a reciprocating gear and a reciprocating gear rotated by a motor. It can be a lifting device of, or, in addition, it is revealed that it can be carried out in various modifications using a known linear movement structure.

In addition, the fixing device for inspecting guided missiles according to the present invention moves the left and right of the first linear moving part 900 and the second base part 600 to enable the left and right movement of the first base part 500. It may further include a second linear moving unit 1000 to enable.

The first linear moving part 900 and the second linear moving part 1000 may move the first base part 500 and the second base part 600 left and right in the width direction of the guided bullet, that is, in the circumferential direction. do.

The first linear moving part 900 is a first linear moving guide rail in which the first base portion 500 is movably coupled and positioned in the circumferential direction of a guided missile or projectile to guide linear movement of the first base portion 500. It may include a member 910.

As an example, the first base portion 500 is movably positioned along the first linear movement guide rail member 910 and fixed in position with a positioning fixture such as a set screw.

The first base portion 500 is moved along the first linear movement guide rail member 910 and is positioned with a set screw that presses the first linear movement guide rail member 910 through the first base portion 500 It is assumed that is fixed, and the set screw is released and can be moved along the first linear movement guide rail member 910 again.

In addition, the second linear movement unit 1000 is a second linear movement in which the second base unit 600 is movably coupled and positioned in the circumferential direction of the guided missile or projectile to guide the linear movement of the second base unit 600. A guide rail member 1010 may be included.

As an example, the second base portion 600 is movably positioned along the second linear movement guide rail member 1010 and fixed in position with a position fixture such as a set screw.

The second base portion 600 is moved along the second linear movement guide rail member 1010, and is positioned with a set screw that presses the second linear movement guide rail member 1010 through the second base portion 600 It is assumed that is fixed, and the set screw is released and can be moved along the second linear movement guide rail member 1010 again.

The first linear moving unit 900 and the second linear moving unit 1000 include the linear actuator of the ball screw structure, and each of the first base unit 500 and the second electric power is transmitted by the operation of the motor included in the linear actuator. It is revealed that the base portion 600 can be moved in a straight line.

Further, in addition to the first linear moving part 900 and the second linear moving part 1000, well-known linear motion such as a pinion gear rotated by a hydraulic cylinder and a rotating motor and a pin and pinion structure that is linearly moved by the pinion gear are moved. It turns out that it can be implemented by various modifications using a structure.

The fixing device for inspecting guided missiles according to the present invention may further include a longitudinal linear moving part 1100 that enables front and rear movement of the first base part 500 and the second base part 600.

In the longitudinal linear moving part 1100, the rail connecting member 1110 and the rail connecting member 1110 connecting the first linear moving guide rail member 910 and the second linear moving guide rail member 1010 are movable. It may be coupled and is located in the longitudinal direction of the missile or projectile may include a longitudinal movement guide rail member 1120 to guide the linear movement of the rail connecting member 1110.

As an example, the rail connecting member 1110 is movably positioned along the longitudinal movement guide rail member 1120 and the position is fixed by a position fixture such as a set screw.

The rail connecting member 1110 is moved along the longitudinal moving guide rail member 1120, and the position is fixed by a set screw that presses the longitudinal moving guide rail member 1120 through the rail connecting member 1110, As an example, the set screw may be loosened and moved again along the longitudinal movement guide rail member 1120.

The lengthwise linear moving part 1100 includes linear motion actuators having a ball screw structure to linearly move the first base part 500 and the second base part 600 respectively by the operation of the motor included in the linear actuator. Reveals that it can.

In addition, the longitudinal linear moving part 1100 is variously modified by using a well-known linear moving structure such as a hydraulic cylinder, a pinion gear rotated by a rotating motor and a pin and a pinion gear which are linearly moved by a pinion gear. It can be revealed.

The first linear moving part 900, the second linear moving part 1000, and the longitudinal straight moving part 1100 are the first base part 500 and the second base part 600 in the horizontal direction and the front and rear direction. The guided grenade, which is mounted and fixed through the first guided grenade fixing unit 100 and the second guided grenade fixing unit 200 by being moved in a straight line, is mounted through the first launcher fixing unit 300 and the second grenade fixing unit 400 The fixed launcher can be moved to a location where inspection work is easy to improve convenience during inspection work.

On the other hand, Figures 2 and 3 is a perspective view showing an example of the use of the guide device for inspecting guided missiles according to the present invention, Figure 2 is a first guided grenade fixing part 100 and the first guided missile fixing device for checking guided missiles according to the invention 2 shows an example of checking the guided missile 10 by mounting and fixing the guided missile 10 through the guided missile fixing part 200, and FIG. 3 shows the first launcher fixation part of the fixed device for checking guided missiles according to the present invention ( 300) and the second launching tube fixing part 400 shows an example of checking the launching tube 20 by mounting and fixing the launching tube 20 into which the guided missile 10 is loaded.

Referring to Figure 2, the first guided grenade fixing part 100 and the second guided grenade fixing part 200, that is, the first guided grenade clamping member 110 and the second guided grenade clamping member 120 of the guided missile assembly 10 is completed It shows an example in which one side is clamped and fixed, and the other side of the guided missile 10, which has been assembled with the third guided bullet clamping member 210 and the fourth guided bullet clamping member 220, is clamped and fixed.

At this time, the second launching tube clamping member 320 and the fourth launching tube clamping member 420 are separated from the first launching tube clamping member 310 and the third launching tube clamping member 410, respectively, to remove the guided missile 10. The guided missile clamping member 110 and the third guided missile clamping member 210 may be seated and mounted.

That is, when checking the guided missile 10, which is the completed bullet, the second launcher clamping member 320, the fourth launcher clamping member 420, the second grenade clamping member 120, and the fourth guided grenade clamping member ( 220) is separated from the first launcher clamping member 310, the third launcher clamping member 410, the first grenade clamping member 110, and the third grenade clamping member 210, respectively, and the first grenade insert part and the third The upper side of the guided ammunition insertion section is opened.

Then, after the first guided grenade clamping member 110 and the third guided grenade clamping member 210 are seated on the guided bullet 10, that is, by inserting the guided grenade into the first guided grenade inserting portion and the third guided grenade inserting portion, After being seated, the second guided grenade clamping member 120 and the fourth guided grenade clamping member 220 are coupled to the first guided grenade clamping member 110 and the third guided grenade clamping member 210 to clamp the guided munitions 10 to position them. To fix.

In addition, referring to Figure 3, the first blast pipe fixing part 300 and the second blast pipe fixing part 400, that is, the first blast pipe clamping member 310 and the second blast pipe clamping member 320, the assembled guided ammunition inside By clamping one side of the launch tube 20 loaded with, and fixing the other side of the launch tube 20 in which the guided missiles assembled with the third launch tube clamping member 410 and the fourth launch tube clamping member 420 are charged into the inside, It shows a fixed example.

At this time, the second grenade clamping member 120 and the fourth grenade clamping member 220 are removed from the first grenade clamping member 110 and the third grenade clamping member 210, respectively, and the first grenade clamping member ( 110) and the third guided grenade clamping member 210 are lowered and positioned so as not to be caught by the launch tube 20.

That is, when checking the launch tube 20 loaded with the guided missile, which is the completed bullet, the second launcher clamping member 320, the fourth launcher clamping member 420, and the second guided grenade clamping member 120, fourth The guided missile clamping member 220 is separated from the first launcher clamping member 310, the third launcher clamping member 410, the first grenade clamping member 110, and the third grenade clamping member 210, respectively. By lowering the clamping member 110 and the third guide grenade clamping member 210 so as not to overlap the first blast tube insertion portion and the second blast tube insertion portion, the upper ends of the first blast pipe insertion portion and the third blast pipe insertion portion are respectively opened. do.

In addition, after the first launcher clamping member 310 and the third launcher clamping member 410 are seated on the launcher 20, which is loaded with guided bullets, that is, in the first launcher insertion section and the third launcher insertion section After the launch tube 20 is inserted and seated, the second launch tube clamping member 320 and the fourth launch tube clamping member 420 are coupled to the first launch tube clamping member 310 and the third launch tube clamping member 410 to launch the tube ( Fix the position by clamping 20).

4 is a perspective view showing an embodiment of a part supporting part 1200 in a guide device for inspecting a guided missile according to the present invention, and FIG. 5 is a part supporting part 1200 in a guide device for checking a guided missile according to the present invention. It is a perspective view showing an example of use.

Referring to Figures 4 and 5, the fixed device for checking guided missiles according to the present invention is detachably coupled to one end of the first blast tube fixing part 300 and the other end is detachably coupled to the second blast tube fixing part 400. In addition, it may further include a component support portion 1200 that can be mounted and mounted on the inner part 10c of the guided missile which is inserted into the interior of the guided missile.

The part supporting part 1200 is located at one end side of the part supporting member 1210, the part receiving member 1210 having an insert opening space of the upper part and is detachable from the first launch tube clamping member 310. The first fuselage coupling member 1220 capable of combining the separated fuselage 10a of the guided missile and located on the other end side of the component support member 1210 and detachable from the third launch tube clamping member 410 And a second fuselage coupling member 1230 that can be coupled and combine the separated fuselage 10b of guided missiles.

The first fuselage coupling member 1220 and the second fuselage coupling member 1230 are detachably coupled to the first launch tube clamping member 310 and the third launch tube clamping member 410 by bolting, respectively.

The first seating portion 1221, which is seated on the first launch tube clamping member 310 and bolted to the third clamping fixing bolt 321a, is located on both sides of the first fuselage coupling member 1220, and the second fuselage coupling member On both sides of 1230, a second seating portion 1231 that is seated on the third launching tube clamping member 410 and bolted to the fourth clamping fixing bolt 421a is located.

The component supporting member 1210 has a semi-circular cross-section of a component insertion space, and the first fuselage coupling member 1220 and the second fuselage coupling member 1230 surround a portion of the fuselage 10a, 10b. As an example, it is formed in a ring shape enclosing at least half of the fuselage and the fuselage 10a, 10b is inserted and mounted inside.

For example, the first fuselage coupling member 1220 and the second fuselage coupling member 1230 are formed in a ring shape with both ends spaced apart, and the fuselage bodies 10a, 10b of guided missiles are respectively fitted into each other.

In addition, a first auxiliary support portion 1220a, which is inserted into and seated in the first guided bullet inserting portion of the first guided bullet clamping member 110, is positioned on the outer side of the first fuselage coupling member 1220 to protrude.

The first auxiliary support portion 1220a has a curved surface having a curvature corresponding to the curvature of the first guided bullet inserting portion, and can be stably supported by being seated in the first guided bullet inserting portion.

The second auxiliary supporting portion 1230a, which is inserted into and seated in the third guided bullet inserting portion of the third guided bullet clamping member 210, is located on the outer side of the second fuselage coupling member 1230.

The second auxiliary support portion 1230a has a curved surface having a curvature corresponding to the curvature of the third guided bullet inserting portion, and can be stably supported in the third guided bullet inserting portion.

Referring to FIG. 5, when the inner part 10c and the body of the guided missile are checked together before the assembly of the guided missile is completed, the second launcher clamping member 320, the fourth launcher clamping member 420, and the second guided grenade clamping member ( 120), the fourth grenade clamping member 220 is separated from the first launcher clamping member 310, the third launcher clamping member 410, the first grenade clamping member 110, the third grenade clamping member 210, respectively And the first seating portion 1221 of the first fuselage coupling member 1220 and the second seating portion of the second fuselage coupling member 1230 on the first blast pipe clamping member 310 and the second blast pipe clamping member 320 Each of the (1231) is seated, and the part receiving part 1200 is mounted by bolting.

Then, the first fuselage member 1220 is coupled to and mounted on one of the fuselage bodies 10a of the guided grenade, and the second fuselage member 1230 is coupled to the other one of the fuselage bodies of the guided grenade by combining After mounting, the internal component 10c mounted in the guided bullet may be seated in the component insertion space of the component supporting member 1210 and mounted.

The present invention is a completed grenade-type guided grenade, a completed grenade-type guided launcher inside, and each fused body divided into an uncompleted state and an internal part of the guided grenade inserted into the fuselage (10c) After fixing the position by mounting, each of the inspection operations can be performed.

That is, the present invention can fix each of the deformed shapes of the missile during the assembly of the missile, thereby smoothly inspecting the missile in the process of assembling the missile, thereby reducing the time required to inspect the missile and reducing the number of personnel required Of course, the safety and convenience of inspection work are increased.

The present invention provides a favorable environment for inspection to grasp the mechanical characteristics by increasing the mechanical position of components during the inspection operation at each assembly step of the guided missile, and increases the convenience of manufacturing and operating inspection software I can do it.

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.

10: guided bullets 10a, 10b: fuselage
10c: inner part 20: launch tube
100: first guided grenade fixing part 110: first guided grenade clamping member
120: second guided grenade clamping member 121: first flange portion
121a: first clamping fixing bolt 200: second guided grenade fixing part
210: third guided grenade clamping member 220: fourth guided grenade clamping member
221: second flange portion 221a: second clamping fixing bolt
300: first blasting tube fixing part 310: first blasting tube clamping member
320: second clamping member clamping member 321: third flange portion
321a: 3rd clamping fixing bolt 400: 2nd launching tube fixing part
410: clamping member of the third launching tube 420: clamping member of the fourth launching tube
421: 4th flange portion 421a: 4th clamping fixing bolt
500: first base portion 510: first elevating guide bar member
511: first clamping stopper portion 512: first clamping support portion
600: second base portion 610: second elevating guide bar member
611: second clamping stopper portion 612: second clamping support portion
700: first lifting part 710: first clamping lifting screw
720: first elevating operation member 800: second elevating part
820: second elevating operation member 900: first linear moving part
910: first linear movement guide rail member 1000: second linear movement unit
1010: 2nd linear movement guide rail member 1100: longitudinal linear movement part
1110: rail connecting member
1120: longitudinal movement guide rail member
1200: parts supporting part 1210: parts supporting member
1220: first fuselage coupling member 1220a: first auxiliary support
1221: first seating portion 1230: second fuselage coupling member
1230a: Second auxiliary support 1231: Second seat

Claims (22)

A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed; And
It is located spaced apart from the first launcher fixed portion and includes a second launcher fixed portion is fixed to the other side of the launch tube,
The first launch tube fixing unit,
A first blast tube clamping member in which a first blast tube insertion portion surrounding a portion of the launcher tube is located; And
And a second launcher clamping member which is located in the second launcher tube surrounding the rest of the launcher and is detachably coupled to the first launcher clamping member,
The second launch tube fixing unit,
A third launching tube clamping member in which a third launching tube inserting part surrounding a part of the launching tube is located; And
And a fourth launcher clamping member which is located at a fourth launcher insertion portion surrounding the rest of the launcher and is detachably coupled to the third launcher clamping member.
The method according to claim 1,
The first guided grenade fixing part,
A first guided bullet clamping member in which a first guided bullet inserting portion surrounding a part of the body of the guided bullet is located;
A second guided grenade clamping member which is located on the second guided grenade clamping member and is detachably coupled to the first guided grenade clamping member;
The second guided grenade fixing part,
A third guided bullet clamping member in which a third guided bullet inserting portion surrounding a part of the body of the guided bullet is located; And
And a fourth guided grenade clamping member which is located on the third guided grenade clamping member and is detachably coupled to the third guided grenade clamping member.
delete The method according to claim 1,
A first base portion to which the first guided grenade fixing portion and the first launcher fixing portion are mounted and fixed; And
The second guided grenade fixing part and the second base tube fixing unit for checking guided missiles further comprising a second base portion is fixed.
A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed;
A second blast tube fixing part positioned to be spaced apart from the first blast tube fixing part and fixed to the other side of the launcher tube;
A first base portion to which the first guided grenade fixing portion and the first launcher fixing portion are mounted and fixed; And
The second guided grenade fixing portion and the second base portion fixing unit is mounted and includes a second base portion,
In the first base portion, the first guided grenade fixing portion is positioned to be movable up and down, and in the second base portion, a second guided grenade fixing portion is positioned to be movable up and down, so that the first launch tube fixing portion and the second Fixation device for the guided missile inspection, characterized in that to be fixed by mounting the launcher with a launcher fixed.
A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed; And
It is located spaced apart from the first launcher fixed portion and includes a second launcher fixed portion is fixed to the other side of the launch tube,
The first guided grenade fixing part,
A first guided bullet clamping member in which a first guided bullet inserting portion surrounding a part of the body of the guided bullet is located;
A second guided grenade clamping member which is located on the second guided grenade clamping member and is detachably coupled to the first guided grenade clamping member;
The second guided grenade fixing part,
A third guided bullet clamping member in which a third guided bullet inserting portion surrounding a part of the body of the guided bullet is located; And
A fourth guided grenade clamping member is disposed to surround the rest of the body of the guided grenade and is detachably coupled to the third guided grenade clamping member,
A first base portion to which the first guided grenade fixing portion and the first launcher fixing portion are mounted and fixed;
The second guided grenade fixing portion and the second base portion is fixed to the second launcher is mounted further comprises,
The first base portion is provided with first guiding and descending guide bar members positioned on both sides of the first guided bullet clamping member to penetrate the first guided bullet clamping member to guide up and down movement of the first guided bullet clamping member. ,
The second base portion is provided with a second lifting guide member on both sides of the third guided grenade clamping member to penetrate the third guided grenade clamping member to guide up and down movement of the third guided grenade clamping member. Fixed device for inspecting missiles, characterized in that.
The method according to claim 6,
A first clamping stopper portion to which movement of the first guided bullet clamping member is restricted is located at an upper portion of the first guide plate member, and the first guided bullet clamping member is seated at a lower end of the first guide plate member. The first clamping support portion is located,
A second clamping stopper portion to which movement of the third guided bullet clamping member is restricted is located at an upper end portion of the second guide plate member, and the third guided bullet clamping member is seated at a lower end of the second guide plate member. Fixed clamping device for inspecting missiles, characterized in that the second clamping support is located.
A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed;
A second blast tube fixing part positioned to be spaced apart from the first blast tube fixing part and fixed to the other side of the launcher tube;
A first base portion to which the first guided grenade fixing portion and the first launcher fixing portion are mounted and fixed; And
The second guided grenade fixing portion and the second base portion fixing unit is mounted and includes a second base portion,
The first guided grenade fixing part,
A first guided bullet clamping member in which a first guided bullet inserting portion surrounding a part of the body of the guided bullet is located;
A second guided grenade clamping member which is located on the second guided grenade clamping member and is detachably coupled to the first guided grenade clamping member;
The second guided grenade fixing part,
A third guided bullet clamping member in which a third guided bullet inserting portion surrounding a part of the body of the guided bullet is located; And
A fourth guided grenade clamping member is disposed to surround the rest of the body of the guided grenade and is detachably coupled to the third guided grenade clamping member,
The first grenade clamping member,
A first moving body positioned to be movable up and down on the first base; And
It includes a second moving body located on the upper portion of the first moving body to be moved up and down and moved up and down by a first elevating portion and positioned with a first guided bullet insert that surrounds a part of the body of the guided missile,
The third guided bullet clamping member,
A third moving body positioned to be movable up and down on the second base; And
It is characterized in that it comprises a fourth movable body located on the upper part of the third movable body, movable up and down, and moved up and down by a second elevating part, and positioned with a third guided grenade insert that surrounds a part of the body of the guided missile. Fixing device for checking guided missiles.
The method according to claim 8,
The first elevating unit is mounted on the first movable body to be rotatably positioned and screwed to the second movable body to rotate and rotate the first clamping elevating screw to elevate the second movable body according to the rotating direction. Including,
The second elevating portion is rotatably positioned on the third movable body and is screwed to the fourth movable body to rotate and rotate the second clamping elevating screw to elevate the fourth movable body according to the rotational direction. Fixed apparatus for checking missiles, characterized in that it comprises.
The method according to claim 9,
The first elevating unit,
Further comprising a first elevating operation member which is rotatably located on the first movable body and protrudes outward and generates a rotational force to operate the first clamping elevating screw,
The second elevating portion,
Fixed device for checking guided missiles, characterized in that it further comprises a second lifting and lowering operation member which is rotatably positioned on the third moving body and protrudes outward and generates a rotational force to operate the second clamping lifting screw. .
The method according to claim 9,
The first elevating unit,
Further comprising a first elevating rotary motor that is operated by receiving electrical power to rotate the first clamping elevating screw,
The second elevating portion,
A guide device for inspecting guided missiles, characterized in that it further comprises a second lifting and lowering rotating motor operated by receiving electrical power to rotate the second clamping lifting and lowering screw.
delete A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed;
A second blast tube fixing part positioned to be spaced apart from the first blast tube fixing part and fixed to the other side of the launcher tube;
A first base portion to which the first guided grenade fixing portion and the first launcher fixing portion are mounted and fixed;
A second base portion to which the second guide grenade fixing portion and the second launcher fixing portion are mounted and fixed;
A first linear moving portion enabling left and right movement of the first base portion; And
And a second linear moving part enabling left and right movement of the second base part,
The first linear moving portion includes a first linear moving guide rail member movably coupled to the first base portion and positioned in a circumferential direction of a guided missile or projectile to guide linear movement of the first base portion,
The second linear moving part is a check guide missile characterized in that the second base portion is movably coupled and includes a second linear movement guide rail member that is positioned in the circumferential direction of the projectile or projectile to guide the linear movement of the second base portion. Dragon fixture.
delete The method according to claim 13,
The first base portion and the second base portion further includes a longitudinal linear moving portion that enables movement before and after,
The longitudinal linear moving part,
A rail connecting member connecting the first linear moving guide rail member and the second linear moving guide rail member; And
The rail connecting member is movably coupled and is located in the longitudinal direction of the guided projectile or projectile, the guide device for checking guided missiles comprising a longitudinally moving guide rail member for guiding the linear movement of the rail connecting member.
A first guided grenade fixing part on which one side of the guided grenade is seated and fixed;
A second guided grenade fixed portion which is spaced apart from the first guided grenade fixed portion and is fixed by being seated on the other side of the guided grenade;
A first launcher fixed portion on which one side of the launcher where the assembled guided missile is loaded is fixed;
A second blast tube fixing part positioned to be spaced apart from the first blast tube fixing part and fixed to the other side of the launcher tube; And
One end part is detachably coupled to the first launch tube fixing part, the other end is detachably coupled to the second launch tube fixing part, and a part support capable of seating and mounting the internal parts of the guided missile inserted into and mounted inside the guide missile. Fixed apparatus for checking guided missiles, characterized in that it comprises a wealth.
The method according to claim 1,
One end part is detachably coupled to the first launch tube fixing part, the other end is detachably coupled to the second launch tube fixing part, and a part support capable of seating and mounting the internal parts of the guided missile inserted into and mounted inside the guide missile. More wealth,
The parts supporting portion,
A component support member provided with a component insertion space of an open type;
A first fuselage coupling member positioned at one end side of the component supporting member and detachably coupled with the first launch tube clamping member and capable of coupling a separated fuselage of guided missiles;
And a second fuselage coupling member positioned on the other end side of the component supporting member and detachably coupled with a third launch tube clamping member and capable of coupling a separated fuselage of guided missiles.
The method according to claim 17,
A first seating portion is mounted on both sides of the first fuselage coupling member and is bolted to the first blasting tube clamping member, and is mounted on both sides of the second fuselage coupling member to be bolted by being seated on the third blasting clamping member. 2 The fixing device for the guided missile inspection, characterized in that the seating portion is located.
The method according to claim 17,
The component supporting member is a fixing device for a guided missile inspection, characterized in that a component insertion space having a semi-circular cross-section is located therein.
The method according to claim 17,
The first fuselage coupling member and the second fuselage coupling member are formed in a ring shape enclosing a portion of the fuselage but at least more than half of the fuselage, so that the fuselage is inserted into the inside and mounted to check guided missiles. .
The method according to claim 17,
The first guided grenade fixing part,
A first guided bullet clamping member in which a first guided bullet inserting portion surrounding a part of the body of the guided bullet is located;
A second guided grenade clamping member which is located on the second guided grenade clamping member and is detachably coupled to the first guided grenade clamping member;
The second guided grenade fixing part,
A third guided bullet clamping member in which a third guided bullet inserting portion surrounding a part of the body of the guided bullet is located; And
A fourth guided grenade clamping member is disposed to surround the rest of the body of the guided missile and is detachably coupled to the third guided grenade clamping member.
On the outer surface of the first fuselage coupling member, a first auxiliary support portion inserted into and seated in the first guided bullet inserting portion of the first guided bullet clamping portion is protruded on the lower side,
A fixing device for checking guided missiles, characterized in that a second auxiliary support portion inserted into and seated in a second guided grenade inserting portion of the second guided grenade clamping member is disposed on an outer side of the second fuselage coupling member.
The method according to claim 21,
The first auxiliary support portion has a curvature having a curvature corresponding to the curvature of the first guided bullet inserting portion, and is seated in the first guided bullet inserting portion,
The second auxiliary support portion has a curved surface having a curvature corresponding to the curvature of the second guided grenade insert, characterized in that it is seated in the second guided grenade insert, guide device for checking guided missiles.

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