JPH0631719B2 - Flying body launcher - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial field of use] The present invention relates to a projectile launching cylinder, and more particularly to improvement of a steady rest releasing means at the time of launching a projectile.

[Prior Art] In general, when launching a projectile, the projectile is housed in a tubular launch tube, and a launcher is driven to launch the projectile.

FIG. 6 is a cross-sectional view showing a state where the flying body 1 is housed in the launching cylinder 2. The launching cylinder 2 is provided with a steady rest mechanism 3 for fixing and holding the front and rear portions of the flying body from the side, and by fastening the flying body by these steady rest mechanisms 3, The body 1 is prevented from rolling.

FIG. 7 is an enlarged view of part A in FIG.
The structure of is shown in detail. The steady rest mechanism 3 penetrates the side surface of the firing cylinder 2 and is slidably movable, and a shaft portion 31.
Bearing 3 which holds this shaft portion 31 on the inner wall surface of the firing cylinder 2.
2 and the shaft portion 3 provided on the side surface of the flying body 1.
1 and a steady rest 33 capable of engaging with each other. When the shaft portion 31 is rotated in the direction of arrow a in the drawing,
The shaft portion 31 slides in the b direction, and the tip of the shaft 31 engages with the steady-state force receiver 33 to fix and hold the flying body 1.

[Problems to be Solved by the Invention] By the way, it is necessary to release the fixed holding force by the steady rest mechanism 3 at the time of launching the flying body 1, but conventionally, the shaft portion is manually moved in the direction opposite to the a direction. The holding force was released by rotating. Therefore, the place where the projectile cannon can be placed is limited to the place where the operator can approach the projectile. Therefore, the operating range of the flying vehicle 1 was narrow. In addition, since the operator approaches the vicinity of the launch tube when launching the flying object, there is a risk of being involved in an accident or the like, which is a safety issue.

On the other hand, it is possible to assemble the shaft 31 so that it can be mechanically moved by hydraulic pressure or a motor so that the fixed holding force can be released by an operation from a distance. However, in this case, the structure of the launch tube itself became complicated, and it was inevitably expensive. Also,
In an environment where surface-to-ship or ship-to-ship missiles are used,
It is clear that malfunctions and the like are likely to occur due to the complication of the structure, resulting in a decrease in reliability.

Therefore, the present invention is a simple and inexpensive structure that can automatically release the fixed holding force to the flying object, which is safe and can extend the operating range of the flying object and improve reliability It is intended to provide a body launcher.

[Means for Solving Problems] In order to solve the above problems and achieve the object, the present invention provides
It is characterized by taking the following measures. That is, it has a slide member that is slidable in the direction perpendicular to the wall surface of the cylinder inside the cylinder, an operating portion that operates the sliding movement of the slide member from the outside of the cylinder, and an arc-shaped outer peripheral surface. The sliding member is rotatably supported on the flying body side end of the slide member at the center of the arc, and the sliding member is slid to the flying body side by the operation of the operation unit. By engaging the arcuate outer circumferential surface of the rotating member with the steady rest force receiver, the steady rest force receiver is fixedly held by the steady rest mechanism, and by the thrust generated from the flying body at the time of launching the flying body. It is characterized in that the rotating member is rotated to automatically release the fixed holding force of the steady rest of the steady rest by the steady rest mechanism.

[Operation] By taking such a means, it is possible to rotate by the thrust from the projectile even if the fixed holding force for the projectile is not released manually or by using a mechanical mechanism when launching the projectile. The member is rotated, and the fixed holding force of the steady rest of the steady rest is automatically released.

[Embodiment] An embodiment of the present invention will be described below with reference to the drawings. The present invention has been realized by improving the steady rest mechanism, and the external structure of the projectile launching cylinder is the same as that shown in FIG. 6, so the description thereof will be omitted with reference to this figure.

FIG. 1 is a schematic view showing an embodiment of a steady rest mechanism which is a main part of the present invention. In the figure, reference numeral 41 designates the firing cylinder 2.
A slide member disposed inside (not shown in FIG. 1) is formed with a guide groove 42, and while being guided by the guide groove 42, the guide member 42 is guided in a direction perpendicular to the wall surface of the firing cylinder 2 (arrow in the figure). It is slidable in the (b direction).
Further, a hole 43 is formed on the wall surface side of the firing cylinder of the slide member 41, and the screw groove formed in the hole 43 is the same as the screw groove formed in the shaft portion 46 of the operation unit 44 described later. Screw together. The operation portion 44 is composed of a stud portion 45 that can be rotated in the direction of arrow a in the figure by a dedicated tool, and a shaft portion 46 that can rotate integrally with the stud portion 45. A guide groove 47 is formed on a side surface of the stud portion 45, and a side wall of the firing cylinder 2 is embedded in the guide groove 47 to prevent movement in a direction other than the rotation direction.

On the other hand, a concave portion 48 is formed at the flying body side end of the slide member 41, and a fan-shaped rotating member 49 is interposed in the concave portion 48. The rotating member 49 has a shape in which a part of a circle is cut out, and is attached rotatably in the direction of arrow c in the drawing by a rotating shaft 50 at the center of the circle. Further, the arcuate outer peripheral surface 51 of the rotating member 49 can be engaged with the steady rest force receiver 52 attached to the flying body 1, and the lateral holding force of the flying body 1 is secured by the holding force at the time of engagement. Prevent shaking.

Hereinafter, in the present embodiment configured as described above, in the case where the flying body 1 is provided with a steady rest (see FIGS. 2 and 3),
The case where the steady rest is automatically released when the flying object 1 is launched (see FIGS. 4 and 5) will be described.

FIG. 2 shows a state in which the steady rest is released. In this state, when the stud portion 45 of the operation portion 44 is rotated in the arrow a1 direction in FIG. 2 with a dedicated tool, the slide member 41 moves in the arrow b1 direction in FIG. 2 via the shaft portion 46. Then, the arc-shaped outer peripheral surface 51 of the rotating member 49 is eventually provided.
The steady rest 5 provided on the side surface of the flying body 1.
Since it abuts on 2, the flying body 1 is fixedly held by tightening the stud portion 45. FIG. 3 shows a state in which the steady rest operation has been completed.

Next, if the motor of the flying vehicle 1 is ignited and the flying vehicle 1 fires in the direction of the arrow M in FIG. 4, the rotating member 49 is rotated about the rotating shaft 50 by the thrust generated from the flying vehicle 1. It rotates in the direction of arrow N in FIG. This is because the rotating member 49 has a shape in which a part of a circle is cut out, and the rotating member 49 can rotate without generating a large resistance due to the thrust. Thus, when the rotating member 49 rotates, the fifth member
As shown in the figure, the steady rest is released.
Can easily launch.

Thus, according to this embodiment, since the steady rest is automatically released by the thrust generated from the flying body 1 when the flying body is launched, it is not necessary for the operator to approach the flying body launch tube at the time of launch. Therefore, the operating range of the projectile canister is widened, and there is no risk of an operator being involved in an accident at the time of launching, and safety can be improved. Moreover, since a power source having a complicated structure such as a hydraulic mechanism and a motor is not used and the structure is simple, it can be realized at low cost. Therefore, the reliability can be improved even with respect to the environmental conditions in which the flying vehicle 1 is used.

The present invention is not limited to the above embodiment.
For example, in the above-described embodiment, the case where a new one is used as the steady rest force receiver 52 attached to the flying body 1 is shown, but there is no problem even if the conventional steady rest force receiver 33 is applied as it is. Absent. Further, the number of the steady rest mechanisms and the installation locations are not limited to those shown in FIG. 6, and it goes without saying that various modifications can be made. In addition, it goes without saying that modifications can be made without departing from the scope of the present invention.

[Advantages of the Invention] As described in detail above, the present invention provides a slide member that is slidable inside the cylinder in a direction perpendicular to the wall surface of the cylinder, and the sliding movement of the slide member from the outside of the cylinder. And a rotating member that has an arcuate outer peripheral surface and is rotatably supported by the flying body side end of the slide member at the center of the arc. The slide member is slid toward the flying body by engaging the arcuate outer peripheral surface of the rotating member with the steady rest by holding the steady rest by the steady rest mechanism. When the projectile is launched, the rotating member is rotated by the thrust generated by the projectile to automatically release the fixed holding force of the steady rest of the steady rest mechanism by the steady rest mechanism. .

Therefore, according to the present invention, the rotating member can be rotated by the thrust from the flying object without releasing the fixed holding force for the flying object at the time of launching the flying object manually or by using a mechanical mechanism. The steady-holding force of the receiver is automatically released by the steady-state steady-state mechanism, so it is possible to automatically release the fixed-holding force to the flying body with a simple and inexpensive structure, which is safe and It is possible to provide a projectile launcher capable of expanding the operational range of the projectile and improving reliability.

[Brief description of drawings]

1 to 5 are views showing an embodiment of the present invention, in which FIG. 1 is a schematic view showing the structure of a steady rest mechanism which is a main part, and FIGS. 2 and 3 are steady rest operations. FIG. 4, FIG. 4 and FIG. 5 are state diagrams showing the steady rest releasing operation, FIG. 6 is a sectional view showing the outline of a general projectile launching barrel, and FIG. 7 is a conventional steady rest mechanism. It is a schematic diagram which shows. 1 ... Flying object, 2 ... Launching cylinder, 3 ... Steady stop mechanism, 41 ... Sliding member, 44 ... Operating part, 45 ...
Stud portion, 46 ... Shaft portion, 49 ... Rotating member, 50 ...
… Rotation axis, 52 …… Anti-stable force receptor.

Claims (1)

[Claims] Claims: 1. A flight in which a plurality of wall surfaces of a cylindrical body for accommodating a flying body are provided with steady rest mechanisms for fixing and holding a plurality of steady rest receivers attached to the side surfaces of the flying body. In the body launching cylinder, the steady rest mechanism includes a slide member that is slidable in a direction perpendicular to a wall surface of the cylinder inside the cylinder, and an operation unit that operates the slide movement of the slide member from the outside of the cylinder. A slide member that has an arcuate outer peripheral surface and is rotatably supported at the center of the arc by the flying body side end of the slide member. By sliding to the side of the flying body to engage the arcuate outer peripheral surface of the rotating member with the steady rest, so that the steady rest is fixedly held by the steady rest mechanism. Start Flying object launcher, characterized by automatically releasing the fixed holding force of the retaining force receptor shake by the slide stop mechanism sometimes caused to rotate the rotating member by the thrust resulting from the spacecraft.