JPS62280595A - Missile launching tube - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed Description of the Invention] 3. Detailed Description of the Invention [Field of Industrial Application] The present invention relates to a projectile launcher, and particularly relates to an improvement of a steady rest mechanism releasing means when launching a projectile. .

[Prior Art] Generally, when launching a projectile, the projectile is housed in a knot-shaped launch tube and is launched by driving a launcher.

FIG. 6 is a sectional view showing the state in which the flying object 1 is housed within the launch tube 2. As shown in FIG. The launch tube body 2 is provided with a steady rest mechanism 3 that clamps the front and rear parts of the projectile from the sides to securely hold the projectile.By tightening the projectile with these steady rest mechanisms 3, the projectile This prevents the body 1 from rolling laterally.

FIG. 7 is an enlarged view of part A in FIG. 6, and shows the steady rest 131.
The structure of 1M3 is shown in detail. The steady rest transportation structure 3 is
A shaft portion 3 that penetrates the side surface of the launch barrel 2 and is slidable.
1, a bearing 32 that holds the shaft portion 31 on the inner wall surface of the launcher 2, and a steady force receptor 33 provided on the side surface of the flying object 1 and capable of engaging with the shaft portion 31. When the shaft portion 31 is rotated in the direction of the arrow a in the figure, the shaft portion 31 slides in the direction b, and the tip of the shaft 31 engages with the steady rest force receptor 33 to prevent flight. The body 1 is held fixed.

[Problems to be solved by the invention] By the way, when the flying object 1 is launched, there is a stopper 1fit.
Although it is necessary to release the fixed holding force by li3, conventionally, the holding force has been released by manually rotating the shaft portion in a direction opposite to the direction a. For this reason, the locations where the projectile launcher can be placed are limited to locations where the operator can approach the optical tA barrel. therefore,
The operational range of Flying Body 1 was narrow. Furthermore, since the operator approaches the vicinity of the launch tube when launching the projectile, there is a risk of being involved in an accident, which is also a problem in terms of safety.

On the other hand, it is possible to assemble the shaft portion 31 such that the sliding movement is performed intermittently by hydraulic pressure or a motor, and to release the fixing holding force by operating from a distance. However, in this case, the structure of the launch tube itself becomes complicated, and it has to be high (west).Also, in an environment where surface-to-ship or ship-to-ship guided missiles are operated, due to the complexity of the structure, It was clear that malfunctions and the like were likely to occur, resulting in a decrease in reliability.

Therefore, the present invention has a simple and inexpensive configuration that can self-help release the fixed holding force on the flying object, which is safe, expands the operating range of the flying object, and improves reliability. The purpose is to promote air vehicle launchers.

[Means for solving the problems] In order to solve the above problems and achieve the purpose, the present invention has the following features:
Taking the following measures is considered an ff sign. That is, a slide member that can be slid inside the cylinder in a direction perpendicular to the wall surface of the cylinder, an operating section that operates the sliding movement of the slide member from outside the cylinder, and a flying body side of the slide member. A rotation member is rotatably supported at the end and fixes and holds a steady rest force receptor attached to the flying object, and a rotating member is configured to form a restraining mechanism, and the stopping mechanism is configured such that the thrust force generated when the flying object is launched is The present invention is characterized in that the fixing force of the steady rest force receptor by the rotating member is automatically released.

[Function] By taking such measures, when the flying object is launched, the self-supporting force is generated by the thrust from the flying object without having to release the holding force against the flying object manually or using a mechanical mechanism. It will be canceled in

[Actual M Example] Hereinafter, one embodiment of the present invention will be described with reference to the drawings. The present invention has been realized by improving the steady rest structure, and the external structure of the projectile launcher is the same as that shown in FIG. 6, so a description thereof will be omitted with reference to FIG.

FIG. 1 is a schematic diagram showing an embodiment of the steady rest mechanism which is the main part of the present invention. In the same figure, 41 is the launch barrel 2 (
It is a slide member disposed inside the projector (not shown in FIG. 1), and has a guide groove 42 formed therein, and is guided by the guide groove 42 in a direction perpendicular to the wall surface of the firing cylinder 2 in the direction indicated by the arrow in the figure. direction). Further, a hole 43 is formed on the inner wall surface of the firing cylinder of the slide member 41, and a thread groove formed in this hole 43 is formed in the shaft portion 46 of the *(/\ portion 44), which will be described later. The operating portion 44 is made up of a stud portion 45 that can be rotated in the direction of arrow a in the figure using a special tool, and a shaft 146 that rotates integrally with the stud portion 45. The stud portion 45 has a guide groove 47 formed on the side surface,
By embedding the side wall of the firing barrel 2 in this guide groove 47, movement in directions other than the rotational direction is prevented.

On the other hand, a recess 48 is formed at the end of the slide member 41 on the flying body side, and a fan-shaped rotating member 49 is interposed in the recess 48 . The rotating member 49 has a shape obtained by cutting out a part of a circle, and is attached to the center of the circle so as to be rotatable in the direction of arrow C in the figure by a rotating shaft 50. Further, the arcuate outer circumferential surfaces 51 of the four rotating members can be engaged with a steady rest force receptor 52 attached to the flying body 1, and the lateral side of the flying body 1 is held by the fixed holding force of the engaging portion. Prevent shaking.

Hereinafter, in this embodiment configured as described above, when applying a stop to the flying object 1 (see FIGS. 2 and 3),
Also, the case where the steady rest is released by itself when the flying object 1 is launched (see FIGS. 4 and 5) will be explained.

FIG. 2 shows a state in which the steady rest is released. In this state, when the stud portion 45 of the operating portion 44 is rotated in the direction of arrow N in FIG. 4 using a special tool, the slide member 41 moves in the direction of arrow N in FIG. 4 via the shaft portion 46.

Then, the arcuate outer circumferential surfaces 51 of the four rotating members will eventually come into contact with the anti-steady force receptor 52 provided on the side surface of the flying object 1, so the stud portion 45 will be attached to hold the flying object 1 fixed. FIG. 5 shows the state in which the steady rest operation has been completed.

Next, if the motor of the flying object 1 is ignited and the flying object 1 is launched in the direction of arrow M in FIG. It rotates in the direction of arrow N in FIG. This is because the rotating member 49 has a shape obtained by cutting out a part of a circle, and can rotate without generating large resistance due to thrust force.

When the four rotating members rotate in this manner, the steady rest is released as shown in FIG. 5, so that the flying object 1 can easily start.

Thus, according to this embodiment, the steady rest is self-help released by the thrust generated from the flying object 1 when the flying object is launched, so there is no need for the operator to approach the flying object launcher during the launching. Therefore, the operational range of the projectile launcher is expanded, and there is no fear that the operator will be involved in an incident during launch, thereby increasing safety. Also, hydraulic pressure I! ! hl.

Since it does not use an assisting source with a complicated structure such as a motor and has a simple configuration, it can be realized at low cost. Therefore, reliability can be improved even under the environmental conditions in which the flying object 1 is used.

Note that the present invention is not limited to the above embodiments.

For example, in the above embodiment, a new steady rest force receptor 52 was used as the steady rest force receptor 52 attached to the flying body 1, but there is no problem if the conventional steady rest force receptor 33 is used as is. There isn't. Further, the number of steady rest mechanisms and the installation locations are not limited to those shown in FIG. 6, and of course, various modifications can be made. other than this,
It goes without saying that modifications can be made without departing from the spirit of the invention.

[Effects of the Invention] As described in detail above, the present invention includes a slide member that can be slid inside a cylinder in a direction perpendicular to the wall surface of the cylinder, and a slide member that can be slid and moved from the outside of the cylinder. and a rotary member rotatably supported by the end of the flying body of the slide member and fixedly holding the steady rest force receptor attached to the flying body. The mechanism is configured such that the holding force of the stabilizing force receptor by the rotating member is automatically divided by wI by the thrust generated when launching the airborne vehicle.

Therefore, according to the present invention, when the flying object is launched, the fixed holding force on the flying object can be released automatically by the thrust from the flying object without manually or mechanically releasing it. This makes it possible to automatically release the fixed holding force on the flying object with a simple and inexpensive configuration, making it possible to launch a flying object that is safe, expands the operational range of the flying object, and improves its reliability. We can provide tubes.

[Brief explanation of the drawing]

1 to 5 are diagrams showing one embodiment of the present invention, in which FIG. 1 is a schematic diagram showing the configuration of the steady rest mechanism, which is the main part, and FIGS. 2 and 3 are diagrams showing the steady rest operation. 4 and 5 are state diagrams showing the steady rest release operation, FIG. 6 is a sectional view schematically showing a general missile launcher, and FIG. 7 is a conventional steady rest mechanism. FIG. DESCRIPTION OF SYMBOLS 1... Flying body, 2... - Launch tube body, 3... Carrying stop mechanism, 41... Slide member, 44... Operation part, 45... Stud part, 46... 4 shaft parts...
Rotating member, 5o...Rotating shaft, 52... Steady rest force receptor. D'151 Figure 2 Figure 3 Figure 4 Figure 5 Figure 6 Figure 7

Claims (1)

[Claims] In a flying body launcher, a steady rest mechanism is provided at a plurality of locations on a wall surface of a cylinder housing a flying body, for fixing and holding a plurality of steady rest force receptors attached to a side surface of the flying body, the steady rest; The mechanism includes a slide member that is slidable inside the cylinder in a direction perpendicular to the wall surface of the cylinder, an operating section that operates the sliding movement of the slide member from outside the cylinder, and a flying body side of the slide member. The rotating member is rotatably supported at the end of the flying body and fixedly holds the steady rest force receptor attached to the flying body. A projectile launcher characterized in that the holding force of a stopping force receptor is automatically released.