KR101931034B1 - Tail fin unit and fastening method thereof for flight stabilized projectile - Google Patents

Abstract

The present invention relates to an air purifier, comprising: a tail blade coupled to a tail body of a projectile; and a protective lid for restraining the tail blade in a state of being fastened to the tail assembly, And the tail wing deployed by the centrifugal force and the elastic force is fixed by the fixing wedge.

Description

TECHNICAL FIELD [0001] The present invention relates to a tail wing unit for stabilizing a flight and a fastening unit for fastening the tail wing unit.

TECHNICAL FIELD The present invention relates to a tail wing unit for attaching a tail wing to a tail portion of a projectile to secure flight stability, and a fastening method thereof.

Most cannon-launched ammunition filled with currently used high explosives is being developed as a revolving ammunition that gives high speed rotation to the launched warhead to ensure flight stability until the target point is reached. If a revolving ammunition is not rotating or flying at low speed, the flight condition is unstable and the aircraft will not be able to reach the target.

In recent years, cannon-launch ammunition with induction control function has been studied. In order to realize smooth induction control function of the flying warhead, it is necessary to fly without rotation or at low speed. In order to ensure flight stability, it is necessary to study a new design concept that attaches a wing to the tail of a flying warhead.

It is an object of the present invention to provide a tail wing device and a fastening method of the tail wing device capable of stable flight even when there is no rotation or low speed rotation in order to realize smooth steering control of a flying object.

It is an object of the present invention to provide a tail wing device and a fastening method of the tail wing device capable of stable flight even when there is no rotation or low speed rotation in order to realize smooth steering control of a flying object.

The present invention relates to a torsion damper comprising a tail blade coupled to a tail body of a projectile and a protective lid for restraining the tail blade in a state of being assembled to the tail portion, Wherein the cover is detached and the tail wing developed by the centrifugal force and the elastic force is fixed by a fixing wedge.

In order to develop a stable stable ammunition filled with a high explosive in the warhead so as to be capable of stable flight even in the case of no-rotation or low-speed rotation like an inductively piloted ammunition, a plate-like tail wing To secure flight stability, and to ensure flight stability while minimizing the increase in length without increasing the outer diameter of the flight launch vehicle.

1 is a conceptual diagram of a configuration of a projectile according to the present invention before a launch.
2 is a conceptual diagram of a state after launch of a projectile according to the present invention.
3 is a perspective view of a tail assembly according to the present invention.
4 is a perspective view of a tail body according to the present invention.
5 is a perspective view of a tail wing according to the present invention.
6 is a perspective view of the tail wing according to the present invention in a state in which the tail wing is fastened to the tail body.
7 is a side cross-sectional view of a protective lid 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 is a state before launch of a projectile according to the present invention, and FIG. 2 is a state after launch of a projectile according to the present invention. 1, the present invention includes a tail assembly 50 coupled to a tail of a launch vehicle body 200, a tail wing 10 coupled to a tail body 54 of the tail assembly, And a protective cover (30) for restraining the cover (30) in a state of being fastened to the tail joint (50). When the projectile leaves the barrel, the propellant in the air pocket 51 in the tail joint is burnt, the protective lid 30 is released by the pressure of the combustion gas, and the tail blade is deployed as shown in Fig. The air pocket 51 stores the propellant combustion gas generated after the projectile is fired. That is, the tail wing is fixed as shown in Fig. 1 while receiving elastic force, and is unfolded as shown in Fig. 2 while simultaneously receiving restoring force and centrifugal force.

3, the tail joint assembly 50 of the projectile body is composed of a tightening ring 60 for preventing the tail body 54 and the tail wing 10 from departing in the direction of the rotation axis. The deployed tail wing (10) is fixed by the tail body (54). The tail body (54) is made of a low-density lightweight material and the high-strength and high-strength material is used for the constraining ring (60) to which a high stress is applied at the time of launching the canvas for weight reduction of the tail joint. The tail body and the restraint ring are made of a heterogeneous material composite structure using low density lightweight materials and high density high strength materials to secure the structurally safe structural structure at the same time as the weight reduction of the tail joint and the high impact acting upon launching the canvas. The tail body and the restraining ring are fastened by screws, bolts, welding, etc.

 A tail wing insertion groove 52 is formed in the tail body 54 of the projectile body to receive and fasten a tail hole 10 formed in the outer side of the tail body parallel to the central axis of the projectile, 52 are equally spaced along the circumferential direction with respect to the central axis of the projectile. 4 shows a case where four tail wings are mounted, and the number of the tail wings 10 can be adjusted.

 5, the tail wing 10 includes a wing 11, which is a plate-shaped elastic body, a tail wing rotation shaft 12 that becomes a central shaft when the tail wing is deployed, a tail wing straight line (13). That is, although the end face of the tail wing rotation shaft is circular, a tail wing straight portion 13 having a flat face on the center of the rotation shaft is separately provided.

The tail wing straight portion 13 functions to fix the tail wing so that it is not folded again after the tail wing is deployed. 6 shows that when the tail wing 11 is deployed, the plane of the fixed wedge 53 in the tail wing insertion groove 52 comes into contact with the tail wing straight portion 13, Thereby preventing rotation of the tail wing. In detail, the fixed wedge 53 is located in the fixed wedge groove 70 on one side of the tail wing insertion groove 52. The fixed wedge groove (70) communicates with the tail wing insertion groove (52). In other words, it is fixed in the fixed wedge groove so as to stay by a round outer circumferential surface which is part of the tail wing 11 formed in a circular cross section while receiving an elastic force by a compression coil spring or a leaf spring. Then, as the tail wing rotates, the round outer circumferential surface, which fixes the fixed wedge 53, changes from the tail wing insertion groove 52 to the tail wing straight line portion by the elastic force so that the plane of the fixed wedge 53 becomes the tail wing straight portion 13 So as to prevent rotation of the tail wing by the mutual contact surfaces. The fixed wedge 53 is formed in a wedge shape or a tapered shape with a narrow upper side and a wider downward side, a vertical plane on one side, and a tapered side on the other side.

Further, after the tail wing 11 is fixed while moving in the radial direction by a certain distance elastic force, the fixed wedge stopper (not shown) projecting the tail body 54 toward the tail wing insert groove 52 at a certain distance 72 are formed. The contact of the plane of the fixed wedge 53 with the tail wing rectilinear section 13 may be forcibly fixed by substantial surface contact or may be line contact with a certain distance.

The tail wing completely deployed in the radial direction of the tail body 54 by the centrifugal force and the elastic force is restrained by the fixed wedge so as not to move in the rotating direction and is fastened to the tail body.

Fig. 7 is a side cross-sectional view of the protective cover according to the present invention, in which the fastened wing is fastened to the tail portion. The combustion gas suction hole 31 and the protective cover body 32 are formed and the combustion gas suction hole 31 is formed to store a predetermined amount of propellant combustion gas without escaping.

Another embodiment according to the present invention is a method of fastening and deploying the tail wing unit 100. [ A tail wing fastening step of inserting the tail wing rotation shaft 12 into the tail wing insertion groove 52 and fastening the tail wing 10 to the tail body 54, a step of fastening the fastened tail wing to the outside of the tail joint, A combustion gas storing step in which the propellant combustion gas is collected in the air pocket 51 after the projectile is fired and the protective cover 30 is detached when the projectile is detached from the barrel A step of separating the protective cover by the pressure of the propellant combustion gas stored in the air pocket in the combustion gas storing step and the step of removing the restraint by the protective cover is developed , And the deployed tail wing is fixed with a fixed wedge. The step of fixing the deployed tail wing with the fixed wedge comprises a step of rotating the tail wing, a step of aligning the straight line of the tail wing with the plane of the fixed wedge, and the step of fixing the fixed wedge by the fixed wedge fixing part.

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.

100: tail wing unit
200: projectile body
10: tail wing
30: Protective cover
50: tail assembly
11: wing portion
12: tail wing rotating shaft
13: tail blade straight portion
31: Combustion gas suction hole
32: Protective cover body
51: Air pocket
52: Tail wing insertion groove
53: Fixed wedge
54: tail body
60: constraining ring
70: Fixed wedge groove
72: Fixed wedge stop

Claims (10)

Tail wing;
A tail wing insertion groove in which the rotation axis of the tail wing is accommodated in a tail body located at a tail portion of the projectile while receiving the elastic force of the tail wing;
A protective cover covering the fastened tail wing;
The protective cover is detached by the propellant combustion gas pressure, the tail wing is deployed by the elastic restoring force, and the tail wing is fixed to the tail wing insertion groove by the straight wing formed on the rotation axis of the tail wing,
Wherein the tail blade is formed on one side of the rotation axis of the tail blade and the tail blade is fixed to the tail blade insertion groove by a fixing wedge formed in the tail blade insertion groove according to rotation of the tail blade rotation axis Tail wing unit for flight stabilization. The method according to claim 1,
Wherein the fixed wedge is a tapered surface on one side of the vertical plane and the other side of the fixed wedge. 3. The method of claim 2,
And the tail wing is fixed to the tail wing insertion groove while the face of the fixed wing is in surface contact with the straight wing straight portion. The method of claim 3,
Wherein the fixed wedge is located in a fixed wedge groove communicating with the tail wing insertion groove before the tail wing is deployed. 5. The method of claim 4,
Wherein the fixed wedge is positioned while being suppressed and fixed by the outer circumferential surface of the rotation axis of the tail wing. 6. The method of claim 5,
And the fixed wedge is moved by the elastic force from the tail wing insertion groove after the tail wing is deployed. The method according to claim 6,
Wherein the moved fixed wedge is stopped by the fixed wedge stop. A method of fastening and deploying a tail wing unit for flight stabilization,
A tail wing fastening step of inserting a tail wing rotation shaft into the tail wing insertion groove and fastening the tail wing to the tail body;
Attaching the tightened tail wing to the outside of the tail body and restricting the tail cap so that the tail cap is not deployed;
Storing the propellant combustion gas in an air pocket after the projectile is fired;
A protective cover separating step of separating the protective cover when the projectile leaves the barrel;
Wherein the tail wing is fixed by a fixed wedge of a fixed wedge groove communicating with the tail wing insertion groove while being expanded. A method of fastening and deploying a tail wing unit for flight stabilization,
A tail wing fastening step of inserting a tail wing rotation shaft into the tail wing insertion groove and fastening the tail wing to the tail body;
Attaching the tightened tail wing to the outside of the tail body and restricting the tail cap so that the tail cap is not deployed;
Storing the propellant combustion gas in an air pocket after the projectile is fired;
A protective cover separating step of separating the protective cover when the projectile leaves the barrel;
Wherein the tail wing is fixed by a fixed wedge moved by an elastic force from the fixed wedge groove while the tail wing is deployed. A method of fastening and deploying a tail wing unit for flight stabilization,
A tail wing fastening step of inserting a tail wing rotation shaft into the tail wing insertion groove and fastening the tail wing to the tail body;
Attaching the tightened tail wing to the outside of the tail body and restricting the tail cap so that the tail cap is not deployed;
Storing the propellant combustion gas in an air pocket after the projectile is fired;
A protective cover separating step of separating the protective cover when the projectile leaves the barrel;
Wherein the tail wing is fixed by surface contact between a straight portion of the rotation axis of the tail wing and a vertical plane of the fixed wedge while the tail wing is deployed.

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