JP2004226007A - Missile canister - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To carry out lightening and improvement of rigidity by integrally forming a recessed part in a wall of a canister body to form a wing guide part or the like. <P>SOLUTION: In a composition of the missile canister, the wing guide parts 4 and 5 are integrally formed on each one face 2 and 3 of the wall 1a of the canister body 1, a first recessed part 20 is formed on another face 6 of the wall 1a, and wiring 7 or the like is arranged in the first recessed part 20. <P>COPYRIGHT: (C)2004,JPO&NCIPI

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a missile canister, and more particularly, to integrally form a wing guide portion provided separately from a canister body, a wire attachment portion provided with wiring, and the like by deforming a wall of the canister body inward, thereby simplifying the structure. The present invention relates to a novel improvement for achieving a reduction in weight, weight, and rigidity.
[0002]
[Prior art]
2. Description of the Related Art A conventional missile canister of this type has a configuration shown in FIG.
In FIG. 2, reference numeral 1 denotes a canister main body made of metal and having a square tubular shape as a whole, and semicircular projections are formed on inner surfaces of one surface 2, 3 on both sides of the canister main body 1. A pair of wing guide portions 4 and 5 are attached as separate bodies by bolts or the like.
[0003]
On the inner surface of the other surface 6 orthogonal to the first surfaces 2 and 3, a cover body 9 for housing the wiring 7 and the pipe 8 and the like is provided.
A guide rail portion 12 for guiding a peripheral surface 11a of the missile 11 is provided on an inner surface of the other surface 10 opposite to the other surface 6, and an arc surface formed on the inner surface of the guide rail portion 12. 12a is in sliding contact with the peripheral surface 11a. On both sides of the missile 11, a pair of wings 13 and 14 are provided in a folded state.
[0004]
Therefore, when the missile 11 is ignited and fired in the above-described state, the peripheral surface 11a of the missile 11 is guided by the arc surface 12a of the guide rail portion 12, and the pair of wings 13 and 14 of the missile 11 In the folded state, the wings are slidably contacted with the wing guides 4 and 5 so that the posture at the time of firing is maintained.
[0005]
[Patent Document 1]
JP-A-7-151497
[Problems to be solved by the invention]
Since the conventional missile canister is configured as described above, the following problems exist.
That is, a pair of wing guides and a cover formed as separate bodies must be attached to the inner surface of the canister body with bolts or the like, which increases the manufacturing cost and adds extra weight to the canister body. It was added, which was an obstacle to weight reduction.
[0007]
The present invention has been made in order to solve the above-described problems, and in particular, a wing guide portion provided separately from a canister body, a wire attachment portion provided with wires, and the like, with the wall of the canister body facing inward. It is an object of the present invention to provide a missile canister that is integrally formed by being deformed to obtain a simplified structure, reduced weight, and improved rigidity.
[0008]
[Means for Solving the Problems]
A missile canister according to the present invention is a missile canister having a cylindrical shape, a canister body having a guide rail portion for guiding a missile, and a wing guide portion provided on the canister body for guiding a wing of the missile. , The wing guide portion is configured such that a wall of the canister body is integrally protruded inward and extended, and at least one other surface different from one surface of the canister body on which the wing guide portion is formed. A first recess formed by integrally protruding the wall inward is formed on the surface, and at least wiring is provided in the first recess, and the other surface of the canister body is provided. A second concave portion formed by integrally protruding the wall inward is formed on the other surface opposite to the second surface. The guide rail portion is provided on the inner surface of the concave portion, and the wall is integrally formed on at least one other surface of the canister body different from the one surface on which the wing guide portion is formed. A second concave portion is formed so as to protrude from the second concave portion, and the guide rail portion is provided on an inner surface of the second concave portion.
[0009]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, preferred embodiments of a missile canister according to the present invention will be described with reference to the drawings. The same or equivalent parts as those of the conventional example are denoted by the same reference numerals and will be described.
1 is a canister body made of metal and having a quadrangular cylindrical shape in its entirety. The inner surfaces of both sides 2 and 3 of the canister body 1 are provided with walls 1a of the canister body 1. The wing guides 4 and 5 are formed by squeezing together and forming an inward semicircular cross section.
Each of the wing guide portions 4 and 5 is formed in a protruding shape along the longitudinal direction of the canister body 1.
[0010]
On the inner surface of one other surface 6 of each of the other surfaces 6 and 10 orthogonal to the one surfaces 2 and 3 of the canister body 1, a first concave portion 20 formed by being narrowed down integrally from the wall 1a is formed. The wiring 7, the pipe 8, and the like are accommodated in the first recess 20.
[0011]
On the other surface 10 of the canister body 1 facing the other surface 6, a second recess 21 is formed by narrowing the wall 1a similarly to the first recess 20. A guide rail portion 12 for guiding the peripheral surface 11a of the missile 11 is provided on an inner surface 21a of the missile 11. In addition, since the guide rail portion 12 is provided inside the second concave portion 21, the length thereof is shorter than that of the conventional case, and the material and weight can be reduced. An arcuate surface 12a formed on the inner surface of the guide rail portion 12 is in sliding contact with the peripheral surface 11a of the missile 11, and a pair of wings 13, 14 on both sides of the missile 11 are in sliding contact with a pair of wing guide portions 4, 5. Is provided. The portion indicated by hunting in FIG. 1 shows a state in which the shape of the canister body 1 is depressed and reduced in size as compared with the conventional configuration. In the above-described case, the recess 20 is formed on at least one other surface 6 to provide wiring and piping. However, the recess 21 may be formed on the other surface 10 to provide wiring and piping. .
[0012]
Therefore, when the missile 11 is ignited and fired in the above-described state, the peripheral surface 11a of the missile 11 is guided by the arc surface 12a of the guide rail portion 12, and the pair of wings 13 and 14 of the missile 11 Sliding contact with the wing guides 4 and 5 maintains the posture at the time of firing.
[0013]
The wing guides 4 and 5 are formed in the same shape, and the first and second recesses 20 and 21 are formed in the same shape. In addition, in order to reduce friction, a Teflon (registered trademark) tape or the like is applied, hard plating is performed, and molybdenum disulfide or the like is applied to a surface of the wing guide portion formed integrally with the wall 1a of the canister body 1 so as to reduce friction. It goes without saying that a treatment such as applying a lubricant may be performed.
[0014]
【The invention's effect】
Since the missile canister according to the present invention is configured as described above, the following effects can be obtained.
That is, the wing guides for holding the canister are integrally formed on the wall of the canister body, and the case for accommodating the wiring and the like is integrally formed as a recess on the wall of the canister body. It is not necessary to make a part, and the cost and weight can be reduced, and the rigidity of the canister body is improved by each concave shape.
[Brief description of the drawings]
FIG. 1 is a plan view showing a missile canister according to the present invention.
FIG. 2 is a plan view showing a conventional missile canister.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Canister main body 1a Wall 2, 3 One surface 4, 5 Wing guide part 6 Other surface 7 Wiring 10 Other surface 11 Missile 12 Guide rail part 13, 14 Wing 20 First concave part 21 Second concave part 21a Inner surface

Claims (4)

A canister body (1) having a guide rail (12) for guiding a missile (11) having a tubular shape, and wings (13, 14) of the missile (11) provided on the canister body (1). In a missile canister having a wing guide part (4, 5) for guiding,
The missile canister according to claim 1, wherein the wing guides (4, 5) have a configuration in which a wall (1a) of the canister body (1) is integrally extended and protruded inward. The wall (1a) is integrally formed on at least one other surface (6) different from the one surface (2, 3) of the canister body (1) on which the wing guide portions (4, 5) are formed. The missile canister according to claim 1, wherein a first concave portion (20) formed so as to protrude is formed, and at least wiring is provided in the first concave portion (20). A second concave portion (21) formed by integrally projecting the wall (1a) inward is formed on the other surface (10) of the canister body (1) facing the other surface (6). The missile canister according to claim 2, wherein the guide rail (12) is provided on an inner surface (21a) of the second recess (21). At least one other surface (10) of the canister body (1), which is different from the one surface (2, 3) on which the wing guide portions (4, 5) are formed, integrally has the wall (1a) inside. A second concave portion (21) formed so as to protrude toward the second concave portion, and the guide rail portion (12) is provided on an inner surface (21a) of the second concave portion (21). Missile canister as described.

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