KR101903247B1 - Apparatus and method for locking of deployable fins - Google Patents

Abstract

The present invention relates to a wing fastening device for a charging intestine which is fixed in a folded state inside a launching tube so that the wing can be expanded immediately after being fired. The wing fixing device includes a rotary hinge part including a rotation center axis of the wing, And a hinge shaft which is coupled between the rotary hinge portion and the fixed hinge portion. The wing rotates with respect to the rotation center axis. When the angle is a predetermined angle, it is engaged with the bracket. A protruding portion and a clearance portion are formed so as to be fixed.

Description

Technical Field [0001] The present invention relates to an apparatus and a method for locking a loading wing,

The present invention relates to an apparatus and a method for fixing a wing of a charging burden which is fixed in a collapsed state inside a launch tube and then spreads immediately after being fired.

The wings of the bullet loaded in the tube are in a folded state, in order to minimize the size of the tube and to prevent interference with the inside. After the shot has been fired, the wing will be unfurled for a stable flight, and it must be firmly secured without being reversed. Failure to fix or incomplete is very important because structural damage and abnormal flight can occur.

Conventionally, there are many small-sized components (torsion springs, fixing pins, stoppers, etc.) constituting the fixing device, and the assembly process is complicated. This required an increase in manufacturing cost, excessive work time, and manpower. Also, due to manufacturing tolerances and complicated mechanisms between the components, clearance of the wing after fixing occurred. In the case of assemblies made up of many small parts, durability in extreme situations such as firing is poor and maintenance checks are difficult to perform.

In order to restrain the rotation of the hinge portion of the wing in the prior art, the bracket that supports the wing and the body is supported by using a spring or the like, but the spring has a limit in elasticity, durability and assemblability.

Korean Patent Publication No. 10-0467523 B1 (Jan. 13, 2005)

An object of the present invention is to provide a blade fixing device for forming a protruding portion on a rotation reference plane of a blade and forming an insertion groove in a fixed hinge portion of the bracket to fix the blade while restricting rotation of the blade when the blade reaches a predetermined angle .

The present invention relates to a wing fastening device for a charging intestine which is fixed in a folded state inside a launching tube so that the wing can be expanded immediately after being fired. The wing fixing device includes a rotary hinge part including a rotation center axis of the wing, And a hinge shaft which is coupled between the rotary hinge portion and the fixed hinge portion. The protrusion is formed on the rotation reference surface of the wing, and the protrusion is inserted into the fixed hinge portion of the bracket. Wherein the projecting portion is inserted into the clearance portion when the blade reaches a predetermined angle while the blade is deployed, and is fixed while restricting the rotation of the blade by the elasticity of the bracket.

The present invention can be robustly fixed and fixed when the wing is instantly developed in a state where the wing is folded up before the launch, and can be implemented only by changing a part without additional parts, and the low durability The durability is high and the time, cost, and manpower for manufacturing the component can be minimized. That is, the fixing and the stability of the blade can be ensured by using the deformation and the restoring force of the bracket.

1 is a front and a rear view of a wing according to the present invention;
FIG. 2 is a perspective view illustrating a combined structure of a rotating hinge portion and a fixed hinge portion according to the present invention.
3 is a reference plane of the rotating hinge according to the present invention.
4 is a cross-sectional view of a wing according to the present invention

For a better understanding of the present invention, a preferred embodiment of the present invention will be described with reference to the accompanying drawings. The embodiments of the present invention can be modified in various forms, and the scope of the present invention should not be construed as being limited to the embodiments described in detail below. The present embodiments are provided to enable those skilled in the art to more fully understand the present invention. Therefore, the shapes and the like of the elements in the drawings can be exaggeratedly expressed to emphasize a clearer description. It should be noted that the same components are denoted by the same reference numerals in the drawings. Detailed descriptions of well-known functions and constructions which may be unnecessarily obscured by the gist of the present invention are omitted.

FIG. 1 shows a state before and after the blade 10 is deployed. After the blade has been deployed by the rotation of the rotating hinge 20, the blade has to be fixed by the bracket 50 at a certain angle.

A specific structure for this is shown in Fig. In the lower portion of the wing, a rotary hinge portion 20 is formed from the rotation reference surface 30. The rotary hinge portions located on the left and right of Fig. 2 are a first rotary hinge portion and a second rotary hinge portion, A projection 40 is formed on the rotation reference surface between the second rotary hinge portions.

The fixed hinge portion 60 is formed at a predetermined height from the fixed reference surface 70 in the bracket 50. The fixed hinge portion is formed in the central fixed hinge portion located at the center in FIG 2 and the through hole 54 formed in the left and right fixed hinge portions, Is coupled to the first rotating hinge portion and the second rotating hinge portion by a hinge shaft (110) passing through the first rotating hinge portion (80). The central fixed hinge portion is provided with a clearance portion 90 for supporting and fixing the projecting portion 40 thereon. A portion of the hinge shaft passing through the central fixed hinge portion is formed to be smaller in diameter than a portion penetrating the left and right fixed hinge portions and the rotating hinge portion to minimize interference with the protrusion.

A concave portion 100 is formed on the central fixed hinge portion of the bracket so as not to be interfered by the rotation of the wing.

3 is an enlarged view of the rotating hinge portion 20 and the rotation reference plane 30 of the wing, and a protrusion 40 is formed at the center of the rotation reference plane. The height of the projecting portion 40 from the rotation reference plane 30 is not constant. 4, a taper 42 is formed so as to be inclined at a predetermined angle in a direction in which the wings are deployed and unfolded, and a vertical surface 44 is formed from the reference plane of the rotary hinge 20 in a direction in which the wings are closed. That is, the cross-section of the protrusion 40 has the shape of a right triangle. That is, the rotary hinge unit 20 includes a rotation center axis of the wing and is installed at a predetermined distance from the front end of the wing fixation unit of the loading bladder, which is fixed in a folded state inside the launch tube and spreads immediately after being fired. A fixed hinge portion 60 having the same rotation center axis as that of the rotary hinge portion 20 and alternately engaged with the rotary hinge portion 20; A hinge shaft 110 passing through the rotary hinge portion 20 and the fixed hinge portion 60; The protruding portion 40 is fixed to the rotation reference surface 30 between the first rotating hinge portion and the second rotating hinge portion so that the wing is fixed when the wing rotates with respect to the rotation center axis and the gap portion 90 is fixed And are formed on the hinge portion 60, respectively.

In order to fix the wings to the central fixed hinge portion, a clearance portion 90 is formed at a predetermined angle in the central fixed hinge portion, and the length of the clearance portion 90 is equal to the length of the central fixed hinge portion. The width of the clearance portion 90 is equal to the width of the protruding portion 40 and the height of the protruding portion 40 is such that it can be inserted and fixed in the clearance portion 90. 4, the clearance portion 90 is connected to the through hole 80 through which the hinge shaft 110 passes.

The upper surface of the fixed hinge portion 60 forms an inclined surface at an angle to support and fix the deployed wing. As shown in FIG. 4, the upper side surface 72 of the fixed hinge portion 60 is interposed with the rotation reference surface 30 of the blade to stop the rotation of the blade. At this time, a gap portion 90 having an insertion groove is formed to stop the rotation of the wing while fixing the wing, and the vertical surface 44 of the projection portion is fixed to the upper surface of the gap portion 90 to fix the wing.

 The method of fastening a wing fastener is a fastening method for fastening a wing fastening device of a charging burden in which the wing fastening device is fixed in a folded state inside a launching tube so that the wing fastening device is straightened after being fired. Inserting the hinge shaft into the through hole (80) of the wing and the bracket after the assembling; A completely assembling step of fixing both sides of the through hole 80 of the bracket 50 with bolts to prevent the hinge shaft 110 from being separated; And a folding step of folding the wings so as to contact the charging bins by rotating them. The joint is formed when the protrusion 40 is smaller than the angle at which the protrusion 40 is inserted into the clearance 90 and the through hole 80 of the rotating hinge portion 20 of the wing is fixed to the fixed hinge portion 60 of the bracket 50 In order to be aligned.

In the meantime, the process of fixing the wings in the folded state to the bracket 50 finally while the wings are expanded is prepared in a state that the wings are folded inside the tube. Initiating deployment as the wing of the loading shot exiting the launch tube by the firing is rotated; The rotary reference plane 30 of the developed blade is overshooted and developed while passing through the clearance 90 of the bracket 50;

A step in which an upper side surface 72 of the bracket 50 fixed hinge portion 60 is interfaced with the rotation reference surface 30 of the blade while the wing developed after passing through the gap portion is restored by the elastic force according to its own material; And the protruding portion 40 is inserted and fixed in the clearance portion 90. When the wing is overshooted, the clearance portion 90 becomes narrower than the initial preparation stage because the interval of the gap between the insertion grooves becomes smaller due to the elastic force of the rotating blade itself. The entrance of the narrowed portion 90 which is narrowed when the upper side surface 72 of the fixed hinge portion 60 of the bracket 50 is interfaced with the rotation reference plane 30 of the wing is restored to the initial preparation stage And the protruding portion 40 is inserted and fixed in the interference portion 90 in an interference fit manner.

It will be apparent to those skilled in the art that various modifications and equivalent arrangements may be made therein without departing from the spirit and scope of the invention as defined by the appended claims. Therefore, it is to be understood that the present invention is not limited to the above-described embodiments. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims. It is also to be understood that the invention includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as defined by the appended claims.

10: Wings
20:
30: rotation reference plane
40:
50: Bracket
60: Fixed hinge part
70: Fixed reference plane
80: Through hole
90:
100:
110: Hinge shaft

Claims (20)

A wing fixation device for a charging device for loading and unloading a wing,
A rotating hinge portion including a rotation center axis of the wing and spaced apart from the tip by a predetermined distance;
A fixed hinge portion having a rotation center axis identical to that of the rotation hinge portion and interlocking with the rotation hinge portion;
A hinge shaft passing through the rotary hinge portion and the fixed hinge portion;
Wherein the projecting portion is formed on the rotary hinge portion and the clearance portion is formed on the fixed hinge portion so that the wing is fixed when the wing rotates about the rotation center axis at a predetermined angle. The method according to claim 1,
Wherein the rotary hinge portion comprises a first rotating hinge portion and a second rotating hinge portion spaced apart from each other by a predetermined distance, and the fixed hinge portion comprises a left fixed hinge portion, a right fixed hinge portion, and a center fixed hinge portion. 3. The method of claim 2,
Wherein the left fixed hinge portion and the right fixed hinge portion are located on the outer side of the first rotating hinge portion and the second rotating hinge portion along the hinge axis. The method of claim 3,
Wherein the central fixed hinge portion is located inside the first rotating hinge portion and the second rotating hinge portion along the hinge axis. 5. The method of claim 4,
And the clearance portion is formed along the hinge axis on the central fixed hinge portion. 6. The method of claim 5,
And the length of the clearance portion is equal to the length of the center fixed hinge portion. The method according to claim 6,
And the width of the clearance portion is equal to the width of the protruding portion. 8. The method of claim 7,
And a height of the protrusion is inserted and fixed in the gap portion. 9. The method of claim 8,
Wherein the protruding portion is formed with a taper so as to be inclined at a predetermined angle in a direction in which the wing is deployed. 10. The method of claim 9,
Wherein the projecting portion forms a vertical surface from the reference plane of the rotary hinge portion in a direction in which the blades are closed. 11. The method of claim 10,
Wherein the cross section of the protrusion is a right triangle. 12. The method of claim 11,
Wherein the clearance portion is connected to a hole through which the hinge shaft passes. 13. The method of claim 12,
Wherein the projecting portion is formed between the first rotating hinge portion and the second rotating hinge portion. A wing of a charging burden applied with a wing fixing device according to any one of claims 1 to 13, wherein the charging wing is fixed in a folded state inside the tube and then straightened. A method of fastening a wing fastening device for a loading shot according to any one of claims 1 to 13, wherein the wing fastening device is fixed in a folded state inside the tube,
A wiping step of aligning the wing and the bracket in an axial direction;
Inserting the hinge shaft into the through hole of the blade and the bracket after the assembling;
A complete assembly step of fixing both sides of the through holes of the bracket with a bolt to prevent the hinge shaft from being separated;
A folding step of folding the wings so as to contact the charging charcoals by rotating the wings; And a fastening means for fastening the wing fastening device. 16. The method of claim 15,
Wherein the gap is formed at an angle smaller than an angle at which the projecting portion is inserted into the clearance portion. 17. The method according to claim 16, wherein the jigging is performed by aligning the fixed hinge portion of the bracket and the through hole of the rotating hinge portion of the wing. An apparatus for fixing a wing of a loading burl according to any one of claims 1 to 13
In the method for fixing the wing of the charging shot,
Preparing a wing folded inside the tube;
Developing the wings of the charging bullet exiting the bullet tube by firing while rotating; Rotating the reference plane of the wing so as to rotate and overshoot the gap of the bracket;
The rotation reference surface of the blade is rotated and restored so that an upper side surface of the bracket fixing hinge unit is interviewed;
A protrusion of the wing is inserted and fixed in a clearance portion of the bracket; Wherein the method comprises the steps of: 19. The method of claim 18,
Wherein the gap is narrowed by the rotational elastic force of the wing in the step of overshooting the wing. 20. The method of claim 19,
Wherein the wing is rotated and restored and the entrance of the gap is widened at a stage where the rotation reference plane of the wing and the upper side face of the bracket fixed hinge are in contact with each other so that the protrusion is inserted and fixed in the gap portion in an interference fit manner. A method of fixing a blade of a charging burden applying a blade fixing device of a bullet.

Images