RU2681042C1 - Detachable master device of sub-caliber rocket projectile - Google Patents

Abstract

FIELD: rocket equipment.SUBSTANCE: invention relates to rocket engineering and can be used in sub-caliber small-sized rocket projectiles fired from launch tubes with a device for centering and guiding. Detachable sub-caliber missile master device consists of several sectors that are spring-loaded in the radial direction relative to the longitudinal axis of the projectile. Radial protrusions and counter grooves with equidistant protrusions surfaces are made on the lateral surfaces of the sectors in contact with each other. Front ends of the sectors are made flat and provided with protrusions in contact with the inner surface of the launch tube, the height of which is not less than half the difference between the internal diameter of the tube and the caliber of the projectile.EFFECT: invention allows to increase the reliability of the device operation while increasing the safety of its use and reducing its resistance when moving and exiting the launch tube.1 cl, 2 dwg

Description

The present invention relates to the field of rocketry and can be used in sub-caliber small-sized rockets fired from launch tubes with a device for centering and direction.

Known detachable leading device subcaliber projectile [RF Patent for the invention No. 2176376 IPC F42B 14/06 from 05/05/2000], selected as a prototype of the present alleged invention, containing supporting ring sectors with a tapered recess at the front end, spring-loaded in radial direction, relative to the longitudinal the axis of the projectile, in a place offset from the center of mass of the support ring sector by a distance due to the equality of the moments overturning the support ring sector, that is:

Fa × L = Fpr × l, where

Fa is the resulting aeroballistic force acting on the recess of the support ring sector;

Fpr - spring force;

L is the distance from the resulting aeroballistic force to the center of mass of the supporting ring sector;

l is the distance between the axis of the spring (pusher) and the center of mass of the annular sector.

When the projectile leaves the annular tube, the supporting sectors under the influence of the incoming flow into the recess and the springs fly apart in the radial direction.

This device can reduce the risk of damage protruding beyond the caliber elements of the projectile.

The disadvantage of this device is that for its movement along the launch tube, clearance is required between the pipe wall and sectors. At the moment the front of the sectors leaves the muzzle of the pipe, the sectors, under the action of the radial component of the aeroballistic force, begin to rotate by a certain angle within the clearance. The rotation angle increases as the sectors move. This can lead to jamming and uneven expansion, which will create lateral disturbances in the projectile. In addition, it is impossible to ensure constant equality of the overturning moments acting on the sector, since the value of the aeroballistic force is affected by the slope of the incoming air flow by the shell of the shell at the angles of attack and the muzzle velocity, depending on weather conditions (air temperature), while the spring force when it is straightened falls. Also, if the sectors fall after their expansion, the upper sector may fall into the high-speed part of the engine flame, while the sector will receive acceleration in the direction of the launch site, which is dangerous.

The objective of this proposed invention is to increase the reliability of the device while increasing the safety of its use and reducing its resistance when moving and leaving the launch tube.

The solution to this problem is achieved by the fact that in the detachable leading device of the sub-caliber rocket projectile, consisting of several sectors, spring-loaded in a radial direction relative to the longitudinal axis of the projectile, the new one is that radial protrusions and reciprocal grooves with equidistant protrusions are made on adjacent lateral surfaces of the sectors surfaces, while the front ends of the sectors are made flat and provided with protrusions in contact with the inner surface of the pipe, the height of the cat ryh at least half the difference between the inner diameter of the tube and the projectile caliber.

The essence of this proposed invention lies in the fact that due to the adhesion of the device sectors to each other, making their front ends flat and the presence of protrusions in contact with the inner surface of the pipe, the skew of the sectors in the launch tube and the possibility of their jamming when the projectile moves through the pipe and at the exit from her. The execution of the front ends of the sectors flat excludes from the separation process the radial component of the aeroballistic force and makes it possible to increase the energy of the springs directed in the radial direction. This ensures the height of the topping of the upper sectors, which allows them to be prevented from falling into the high-speed part of the engine plume when flying, as it will go forward relative to the trajectory of falling sectors.

The invention is illustrated by graphic materials, where in FIG. 1 shows a general view of a projectile in a launch tube, FIG. 2 projectile mounted in a detachable master and sector design.

The sub-caliber rocket projectile in the launch tube (Fig. 1) contains a launch tube 1, in which a sub-caliber projectile 2, a caliber rocket engine 3 with a powder charge 4, and a master device consisting of sectors 5 are placed. The sectors are interconnected by means of radial protrusions 6 and grooves 7, the ends of the sectors 8 are made flat and provided with protrusions 9. The sectors are spring-loaded (Fig. 2), for example, coil springs 10.

The principle of operation of the detachable sub-caliber projectile launcher is as follows: sectors are mounted on the shell of the shell in a structurally designated place and squeezed around the body with a special device, while the protrusion on the side surface of one sector is placed in the response groove of the neighboring sector. Then the projectile is pulled into the launch tube. Such a connection of the spring-loaded sectors to each other provides a rigid design of the host device, which increases the bending stiffness of the projectile and protects the sub-caliber part from the action of lateral overloads during transportation and official handling. In the launch tube, the spring-loaded sectors contact the protrusions at the front ends with the inner surface of the pipe, which ensures centering of the projectile. When starting a rocket-propelled projectile from the launch tube, the detachable lead device begins to move with the projectile. Moreover, the presence of interacting protrusions and grooves on the lateral surfaces of sectors and protrusions at the ends of sectors, the height of which is not less than two times the distance from the shell of the projectile to the pipe, eliminates the skew of the sectors relative to the projectile and relative to each other and jamming in the launch tube. In addition, both when the projectile moves through the pipe and when exiting from it, the front ends of the sectors, made flat, significantly reduce the free-stream lifting force acting on the projectile, which reduces lateral disturbances. And at the moment the projectile leaves the launch tube, together with the detachable master device, there is no effect of lifting aerodynamic force on each sector. Sectors are separated only by the action of springs in the radial direction, which allows you to designate places of application of forces directly in the centers of mass of the sectors and minimize torques, the impact of which slows down the sectors and maximize the use of spring energy in the radial direction. Due to this, the radius of expansion of the sectors increases and their entry is prevented when falling into the high-speed part of the engine plume.

Thus, the device provides damping of lateral disturbances when the projectile leaves the launch tube, which reduces its speed loss, increases operational reliability, and also improves the safety of combat use by eliminating the sectors entering the high-speed part of the gas jet and accelerating them to high speed.

Claims (1)

A detachable lead device for a sub-caliber rocket projectile, consisting of several sectors, spring-loaded in a radial direction relative to the longitudinal axis of the projectile, characterized in that radial projections and reciprocal grooves with equidistant projections of the surfaces are made on contacting side surfaces of the sectors, while the front ends of the sectors are made flat and equipped with protrusions in contact with the inner surface of the launch tube, the height of which is not less than half the difference of the inner pipe diameter and projectile caliber.

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