JP2010007948A - Missile launching tube - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a launching tube reducing its vibration caused by blowout gas of a missile and stably launching the missile. <P>SOLUTION: The launching tube 11 storing the missile outputting blowout gas from the rear side includes: a projecting internal component 12 provided on the inner wall of the launching tube 11; and a drift member 15 provided on the launching side of the missile from the internal component 12 and diverting the blowout gas to be collided with the face on the launching side of the internal component 12. Due to the drift member 15 for avoiding blast, local launching reaction force generated on the launching port side of the internal component 12 is prevented, to enhance safety during separation of the missile launched from the launching tube 11. Launching reaction force transmitted to the launching tube 11 supporting the missile is reduced, to provide the launching tube 11 suitable for a propelling device etc. for launching the missile from the launching tube 11. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a projectile launcher for launching a projectile.

  On the inner wall of the projectile tube for the flying object, there are provided projecting internal components including a control device for sending a control signal for instructing the projecting timing and speed to the flying object. When a flying object injects from within such a launch tube, blast is generated behind the flying object due to the jet gas output from the rear of the flying object. In particular, when the blast is blocked by the internal components, a large launch reaction force is generated, and this launch reaction force adversely affects the launch tube as vibration.

As a conventional technique, there has been proposed a technique in which a blast deflector plate is provided at the rear part of the launch tube for the purpose of protecting the internal components of the launch tube (see Patent Document 1).
Japanese Patent Laid-Open No. 05-093598

  As described above, when the blast is blocked by the internal component, a large launch reaction force is generated, and this launch reaction force vibrates the launch tube and adversely affects the injection of the flying object.

  The present invention has been made paying attention to the above circumstances, and the object of the invention is to reduce the vibration of the launch tube caused by the jet gas of the projectile and to enable the launcher to stably eject the projectile Is to provide.

  In order to achieve the above object, a projectile launcher according to the present invention is a launcher that houses a projectile that outputs jet gas from the rear, a projecting member provided on an inner wall of the projecting tube, and the projecting member And a drift member that is provided on the exit side of the flying body and warps the ejected gas that collides with the surface on the exit side of the projecting member.

  Therefore, according to the present invention, it is possible to provide a flying object launcher that can reduce the vibration of the launcher that is caused by the jet gas of the flying object and enables stable ejection of the flying object.

Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.
FIG. 1 is a longitudinal sectional view showing an embodiment of a flying object launcher according to the present invention. FIG. 2 is a view of the launch tube of FIG. 1 as seen from the injection direction of the flying object.

  The launch tube 11 includes an internal component 12, a rail 13, and a front lid 14. The launch tube 11 is formed in a tubular shape, and accommodates a projectile that emits jet gas from behind and launches it. The front lid 14 is provided at the injection port of the launch tube 11 and is closed during storage. The rail 13 guides the flying object until it exits the launch tube when the flying object fires. The internal component 12 is provided so as to protrude from the inner wall of the launch tube 11 and includes a control device that sends a control signal instructing the launch timing and speed to the flying object.

  Here, when the flying object is ejected from the inside of the launch tube 11, blast is generated behind the flying object due to the jet gas output from the rear of the flying object. In particular, when the blast is blocked by the internal component 12, a large reaction force is generated, and this discharge reaction force adversely affects the injection direction on the discharge cylinder 11 as vibration.

  Therefore, in this embodiment, a drift member 15 as shown in FIG. 2 is provided on the surface on the emission side of the internal component 12 of the launch tube 11. That is, the drift member 15 having a size capable of sufficiently covering the internal component 12 is provided on the injection side of the internal component 12.

  The drift member 15 covers the internal component 12 provided on the inner wall of the launch tube 11 from the direction of the exit of the launch tube 11 and deflects the blast of the flying object from the front from the exit side surface of the internal component 12. It has a shape that drifts. For example, the drift member 15 is formed in a cone having a bottom surface on the exit side of the internal component 12 and a vertex on the inner wall of the launch tube 11 on the exit side from the bottom surface. The drift member 15 reduces the resistance that the flying body blast receives by the launcher internal component 12, and can reduce the local firing reaction force generated in the launcher. The drift member 15 may be formed integrally with the internal component 12.

  As described above, according to the above-described embodiment, by providing the drift member that prevents blasting, it is possible to prevent a local firing reaction force that occurs on the surface of the internal component on the injection port side, and to eject from the launch tube. It is possible to increase the safety of the flying object being detached. Moreover, the launch reaction force transmitted to the launcher that supports the flying object can be reduced, and a launcher suitable for use in a propulsion device that injects the flying object from the launcher can be realized.

  Note that the present invention is not limited to the above-described embodiment as it is, and can be embodied by modifying the constituent elements without departing from the scope of the invention in the implementation stage. Further, various inventions can be formed by appropriately combining a plurality of constituent elements disclosed in the embodiment. For example, some components may be deleted from all the components shown in the embodiment. Furthermore, you may combine suitably the component covering different embodiment.

1 is a longitudinal sectional view showing an embodiment of a flying object launcher according to the present invention. The figure which looked at the launch tube shown in FIG. 1 from the emission side.

Explanation of symbols

DESCRIPTION OF SYMBOLS 11 ... Launch tube 12 ... Internal component 13 ... Rail 14 ... Front cover 15 ... Diffusion member

Claims (3)

A launch tube containing a projectile that outputs jet gas from the rear,
A protruding member provided on the inner wall of the firing tube;
A projectile launcher comprising: a drift member provided on the exit side of the projectile from the projecting member, and deflecting the jet gas colliding with a surface of the projecting member on the exit side.   The drift member is formed in a cone having a bottom surface on the exit side of the projecting member, and a cone provided on the inner wall of the launch tube on the exit side from the bottom surface. .   The flying object launcher characterized in that the drift member is formed integrally with the protruding member.

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