RU2285220C1 - Rig for determining the momentum at a shot acting on launching device of small-arms or rocket armament - Google Patents

Abstract

FIELD: rocket and small-arms armament testing systems.

SUBSTANCE: the rig has a fixed platform, movable carriage with a launching device fastened on it, and a transducer for monitoring the characteristic of linear motion of the carriage. The movable carriage is positioned on rectilinear horizontal guides by means of the upper and lower roller supports, the guides are rigidly fastened on the fixed platform and provided on two sides with carriage motion stops. The transducer for monitoring the characteristic of the carriage linear motion is made in the form of a permanent magnet fastened on the carriage, and a strip-insulator with a current-conducting winding installed opposite it.

EFFECT: provided adjustment of the value and direction of the momentum by a purposeful variation of the construction of the launching device or rocket.

3 dwg

Description

The invention relates to test systems for missile and small arms, mainly small-sized missile systems with pulsed rocket engines of solid fuel.

A device is known for determining "instantaneous" impulses of force (impulses of a bullet, projectile, etc.) "by measuring the angle of rotation or linear movement of the pendulum." A ballistic pendulum for determining the momentum of force is a load suspended on four thin steel cables and swinging freely on a fixed axis. The deviation of the pendulum is recorded on paper using a recorder (Zeldovich Ya. B. et al. "Impulse of the reactive power of powder rockets." Oborongiz, Moscow, 1963, pp. 133 ... 139).

The disadvantage of the device is the low reliability of the recording device located directly on the device for mounting the power source. In the case under consideration, this is a transport and launch container with a rocket or a sample of small arms.

This drawback is eliminated by a pendulum test bench for missile and small arms containing a truss, to the upper brackets of which a carriage is hung through the rotation units for mounting the test object, and the recorder is placed on the upper truss bracket and is made in the form of a rotation angle sensor with a pulley on its axis, kinematically associated with a pulley mounted on the rotation unit of the carriage. In this case, the diameter of the pulley of the rotation unit is made larger than the diameter of the pulley on the axis of the sensor (application No. 2003108535, Russia, 2003, IPC 7 F 41 A 31/00).

This design of the stand for determining the momentum of force by the angle of rotation or linear movement of the pendulum allows you to determine the integral value of the impulse, but does not allow you to track the change in the magnitude and direction of the force impulse during the time of the force, which, in turn, does not allow you to purposefully refine the design of weapons, reducing the magnitude of the pulse.

The task of regulating the magnitude and direction of the force impulse acting on the launching device during a shot is especially relevant for small-sized missile systems. In most cases, a shot of such a system is carried out either from the shoulder or from an easy launcher in direct contact with the shooter, which imposes severe restrictions on the magnitude of the momentum of the dynamic imbalance force, which determines the safety of the shooter and the combat effectiveness of the shot. With a large momentum of the force of dynamic imbalance at the moment of exit from the tube, the rocket receives an initial disturbance leading it away from the line of sight. Moreover, with the rolling direction of the force pulse, the rocket goes up, with the rolling direction - down from the line of sight. It should be noted that the magnitude and direction of the deflection of the rocket is affected by both the magnitude and direction of the impulse of the resulting force acting on the launch tube during the movement of the rocket along it. In the general case, the main components of this force are the friction force of the rocket, the friction force of the gas, and the forces arising from the separation of the tube sealing caps. In the process of rocket movement through the tube, the ratio of forces changes, and the resulting acting forces can even change its direction. In order to adjust the magnitude and direction of the momentum of the dynamic imbalance force, it is necessary, at a minimum, to know the direction and magnitude of the momentum of force at the moment the rocket leaves the launch tube, as well as the maximum magnitude of the momentum of force in the process of movement through the pipe.

The objective of the invention is to determine the time dependence of the pulse of force acting on the starting device when firing rocket or small arms.

This task is carried out by a stand containing a fixed platform, a movable carriage with a starting device mounted on it and a sensor for detecting the linear movement of the carriage, in which the movable carriage, by means of the upper and lower roller bearings, is placed on rectilinear horizontal guides rigidly fixed to the fixed platform and equipped with two sides of the carriage limiters. At the same time, a permanent magnet is fixed on the movable carriage, and an insulator bar with a conductive winding is installed on the fixed platform opposite it.

The moving permanent magnet and the conductive winding form a speed sensor, the action of which is based on the law of electromagnetic induction

e = -BlV,

where B is the magnetic induction in t;

l is the length of the conductor in m;

V is the speed of the conductor in m / s;

e - induced in the EMF conductor

(Ageikin D.I. et al. "Sensors of control and regulation". Reference materials, "Engineering", 1965, p. 461).

A structural embodiment of the stand is shown in FIGS. 1 and 2. The investigated launching device, in this case, the launch tube 1, with the rocket 2 is mounted on the movable carriage 3. The carriage 3 is mounted on two rectilinear by means of four upper roller bearings 4 and two lower roller bearings 5 guides 6 placed on the fixed platform 7 of the launcher 8. The design with upper and lower roller bearings provides the necessary lateral stability of the carriage under the influence of lateral forces arising from the movement of the rocket with p running engine. A permanent magnet 9 is fixed to the carriage 3, and an insulator strip with a conductive winding 9 is mounted on the platform 7. At the ends of the guides 6, carriage travel stops 11 are provided with shock absorbers 12 (in case of an unaccountably large movement of the carriage 3).

The stand works as follows. When the rocket 2 is launched from the pipe 1 under the influence of unbalanced force, the carriage 3 on the rollers 4, 5 moves along the guides 6 together with the permanent magnet 9 mounted on it. When the magnet 9 is moved, the EMF recorded by the registration system is displayed in the conductive winding of the strip 9. The magnitude of the EMF is directly proportional to the speed of the carriage 5. The proportionality coefficient is determined by the previously obtained calibration graphs. The magnitude of the speed of the carriage at each moment of time (figure 3) and the mass of the moving parts of the stand (launch tube, carriage, permanent magnet, etc.) determines the impulse of unbalanced force.

Figure 3 shows a characteristic curve of the change in the speed of the carriage when the rocket V (τ) is launched. Point 0 is the beginning of the action of the force (the beginning of the rocket's movement), in the area "0-1" the resulting force has a rolling direction and grows to the maximum, which is determined by the forces arising from the separation of the sealing caps of the launch tube and the friction force of the rocket against the pipe wall. After point 1, the resulting force changes direction from rolling to rolling, since among the acting forces, the rolling force of friction of the gas against the pipe wall begins to prevail. Point 2 - the moment the rocket leaves the launch tube.

Thus, the device allows recording the speed of movement of the launch device and obtain a graph of the change in the pulse of the force acting on it during the entire time the rocket (bullet) moves along the launch tube (along the barrel), which makes it possible to control the magnitude and direction of the force pulse by a targeted change in the design of the launch devices or rockets.

Claims (1)

The stand for determining the momentum of the force acting when firing at the launcher of small arms or missile weapons, containing a fixed platform, a movable carriage with a launcher mounted on it and a sensor for detecting linear carriage movement characteristics, characterized in that the movable carriage is placed by means of upper and lower roller bearings on straight horizontal guides rigidly fixed to a fixed platform and equipped on both sides with carriage stops, and the sensor for detecting the linear movement of the carriage is made in the form of a permanent magnet fixed to it and mounted on the fixed platform of the insulator bar with a conductive winding.

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