RU2331041C1 - Method of antitank guided missile launch and antitank guided missile - Google Patents

Abstract

FIELD: weapon.

SUBSTANCE: group of inventions relates to missilery, particularly, to the antitank guided missiles (ATGM) with a powder gyroscopic device in the control system. The method of the antitank guided missile launch includes missile discharge with its further guidance on a target while using an aboard gyroscopic device with a propelling powder. Before discharging of the missiles the rotor of gyroscopic device is sped up and high frequency vibratory load on the rotor to the direction that is perpendicular to axes of the rotation is created. At the end of speedup of gyroscopic device rotor, the destruction of its propelling powder for pressure increase of powder gases inside of the rotor is made. The antitank guided missile contains payload, rocket propulsion, controlling equipment, line of communications, mainly, wire line. The gyroscopic device is fixed on the cardan suspension, rotor of which is supplied with discharge orifices and set-in propelling powder as cylindrical explosive cartridge. The inner frame of the cardan suspension is locked and covers the outer side of the rotor. Additionally the inner frame is supplied with a number of radial holes, symmetrically placed in circumferential direction in the plane of the discharge orifices. The overall length of the orifices in the plane equals 0,3-0,6 of the length of the circumference, and propelling powder is placed with the outer side on the collars of one diameter formed in the inner cylindrical surface of the rotor.

EFFECT: decreased balance weight of the rotor, increased accuracy and reliability of ATGM targeting.

2 cl, 4 dwg

Description

The invention relates to the field of rocket technology, and more particularly to anti-tank guided missiles with a powder gyroscopic device in the control system.

In the designs of modern guided missiles (shells), gyroscopic devices, which are an important element of the control system, whose rotor is accelerated (spun) by powder gases flowing out through tangential nozzles, are widely used. Moreover, in a short period of time, the rotor can accelerate to one hundred thousand revolutions per minute, thereby providing the necessary kinetic moment to maintain the stability of its position in space during the entire flight time of a guided missile (projectile).

A known method of launching an anti-tank guided missile and anti-tank guided missile for its implementation [1], which are the closest analogue (prototype) of the proposed technical solution. This method of launching an anti-tank guided missile (ATGM) and its device are as follows.

An ATGM has the following main components: a warhead, a rocket engine, control equipment, a communication line, mainly wired, and a gyroscopic device mounted on a gimbal, the rotor of which is equipped with nozzle openings and a gunpowder charge in the form of a cylindrical checker. The ATGM under consideration is fired from a transport and launch container, and its control is carried out from the launcher via a wired communication line. In this case, before firing a rocket in a transport and launch container, a powder charge in the rotor of a gyroscopic device is ignited by an electric igniter. Powder gases flowing through the tangential nozzles of the rotor spin the rotor, creating the necessary kinetic moment, thereby ensuring its stable position relative to the coordinate axes associated with the launcher during the entire flight time of the guided missile. The gyroscopic device ensures coordination of control commands generated by the launcher with the coordinate system of the guided missile, i.e. distributes the command along the course and pitch for the electromagnetic drive by means of a lamella sensor, depending on the spatial position of the guided missile during the flight. The movement on the trajectory is provided by the marching rocket engine, and the impact on the target is undermined by the warhead.

However, as testing of such a design has shown, there are cases of incomplete burning of the charge in the rotor of the gyroscopic device at subzero temperatures, which can lead to a decrease in the energy of the powder charge, as well as to an increase in the unbalance of the rotor and, as a consequence, a decrease in the accuracy of the gyroscopic device. All this can lead to a decrease in the reliability and accuracy of rocket control on the trajectory. Accuracy can be reduced both by reducing the rotor speed (ie, reducing its kinetic moment), and the appearance of "noise" when taking signals from a coordinate sensor, the current collectors of which are kinetically connected with the axis of the rotor. This phenomenon is due to the large unbalance of the rotor, which can occur due to the remains of the powder charge.

The technical task of the invention is to increase the accuracy and reliability of guidance anti-tank systems by reducing the unbalance of the rotor of the gyroscopic device by eliminating the burning of powder charge in combat use of guided missiles at subzero temperatures.

To achieve this goal, the following operations were introduced into the method of launching an anti-tank guided missile, which consists in firing a missile and pointing it at a target with determining its position along the course and pitch with an onboard gyroscopic device:

- before firing the rockets, the rotor of the gyroscopic device is accelerated and at the same time a high-frequency vibration load on the rotor is created in the direction perpendicular to the axis of its rotation;

- at the end of acceleration of the rotor of the gyroscopic device, its powder charge is destroyed to increase the pressure of the powder gases inside the rotor.

The stated technical problem is also solved by the design of an ATGM containing a warhead, a rocket engine, control equipment, a communication line, mainly wired, and a gyroscopic device mounted on a gimbal, the rotor of which is equipped with nozzle openings and a gunpowder charge in the form of a cylindrical checker, where:

- the inner frame of the gimbal is made closed and covering the outer surface of the rotor and is equipped with a number of radial holes symmetrically spaced around the circumference in the plane of the nozzle holes;

- the total length of the holes in the said plane is 0.3-0.6 circumference;

- the powder charge with its outer surface is placed on the annular protrusions of the same diameter formed on the inner cylindrical surface of the rotor.

A positive effect is achieved by improving the combustion conditions of the powder charge and complete burnout at the end of the rotor acceleration in the combat use of ATGM at subzero temperatures.

The invention is illustrated by drawings, in which Fig. 1 shows a general view of an ATGM, in Fig. 2 is a sectional general view of a gyroscopic device, in Fig. 3 is a section A-A in Fig. 2, in Fig. 4 is a cutout I in Fig. .2.

ATGM contains a warhead 1, a rocket engine 2, control equipment 3 with a gyroscopic device 4, a wired communication line 5. The gyroscopic device contains a cylindrical rotor 6 with nozzles 7, a powder charge 8, a pyrotechnic igniter 9. The powder charge with its outer surface is placed on the annular protrusions 10. The rotor is mounted on the axes 11 in the inner 12 frame, which is located in the outer 13 frame of the gimbal, and is connected with the coordinate sensor 14. In the inner frame 12 on the outer cylindrical surface there are formed metrically located holes 15, which occupy 0.3-0.6 of the circumference of this surface in the section of the plane passing through the axis of the nozzles 7. The rotor is locked with a lock in the form of a nut 16 screwed onto the rotor axis and connected by a flexible connection, for example, a spring 17, with base 18. Arrows B show the direction of expiration of the powder gases from the combustion of the powder charge.

The operation of the described device is as follows. Before launching the rocket, a current is supplied from the barrel of the container to ignite the pyrotechnic igniter 9, the gases of which ignite the powder charge 8. Due to the reactive force arising from the expiration of the powder gases through the nozzle 7, the rotor begins to gain speed. In this case, the nozzles pass when the rotor rotates alternately under the holes 15 in the inner frame, then under the jumpers between them. In this case, an increase in local pressure of the outgoing gases is formed under the jumpers. Due to this, a vibrational load is created on the rotor in the direction perpendicular to its axis of rotation. This vibration load provides high-frequency oscillation of the rotor in the same direction within the tolerances of the thrust bearings, leading to the exclusion of "sticking" of the surfaces of the powder charge 8 with the inner "cold" surface of the rotor at subzero temperatures. And this, in turn, ensures uniform burning of the powder charge over its entire surface, excluding zones with an increased burning set (difference), leading to unburned charge at the end of its operation. The ratio of the lengths of the holes to the circumference in this section of 0.3-0.6 allows you to get an increase in local pressure acting on the rotor, sufficient for high-frequency oscillation of it. At a lower value of the ratio than 0.3, the relative size of the jumpers between the holes increases, which leads to an increase in local pressure, which already affects the pressure inside the rotor. This will affect the combustion process of the powder charge, leading to an off-design combustion process and a decrease in the reliability of the gyroscopic device.

The ratio of lengths of more than 0.6 leads to a decrease in the relative size of the jumpers between the holes and a decrease in local pressure under the jumpers, which leads to the exclusion of high-frequency oscillations of the rotor during burning of the powder charge and, thereby, to the appearance of unburned charge residues in the rotor.

It also reduces the accuracy of the gyroscopic device for the reasons described above. When the rotor reaches the required number of revolutions, the nut 16 is screwed from its axis 11 and the rotor is sacked. With further combustion, the powder charge reaches such a thickness of the burning arch that it cannot withstand overloads and breaks along arrow B, since there is always a gap between the cylindrical surface of the powder charge and the wall of the rotor due to the annular protrusions 10 on the inner surface of the rotor.

When the charge is destroyed, an additional combustion surface is formed, which leads to an increase in pressure inside the rotor and to a more intense burning of the powder charge, since the burning rate of ballistic powders depends on the pressure in the combustion chamber. Such combustion of the powder charge excludes its extinction at the end of combustion and sticking to the relatively cold walls of the rotor, which reduces the rotor unbalance. Since the burning time of the powder charge does not exceed several tenths of a second (usually not more than 0.3 s), the vibration load on the rotor does not reduce the accuracy of the gyroscopic device due to the fact that the ATGM is still on the launcher.

Elimination of the vibration of the rotor and the associated elements of the coordinate sensor at subzero temperatures after burning of the powder charge (after acceleration of the rotor) significantly reduces the "noise" in the coordinate sensor and, thereby, increases the accuracy of its operation.

Without using the indicated method of launching ATGMs and the structural solutions given, the remaining powder charge in the rotor can reach 30% of its original weight, and the vibration of the rotor leads to the appearance of “noise” in the coordinate sensor, which can lead to missile missile.

In addition, a more complete combustion of the powder charge increases the kinetic energy reserve of the rotor, which leads to an increase in the accuracy of the gyroscopic device and, as a result, to an increase in the accuracy and reliability of ATGM guidance.

According to the proposed technical solution, an experimental batch of anti-tank guided missiles was manufactured, which passed laboratory-bench and firing tests with positive results.

Information sources

1. Guided missile 9M113. Technical description and instruction manual. - Military publishing house of the Ministry of Defense of the USSR, Moscow - 1978. - prototype.

Claims (2)

1. A method of launching an anti-tank guided missile, including firing a missile followed by pointing it at a target using an on-board gyroscopic device with a powder charge, characterized in that before the firing of the rocket, the gyroscopic device rotates, creating a high-frequency vibration load on the rotor in a direction perpendicular to its axis rotation, and at the end of acceleration of the rotor of the gyroscopic device, its powder charge is destroyed to increase the pressure of the powder gases inside p torus. 2. An anti-tank guided missile containing a warhead, rocket engine, control equipment, a communication line, mainly wired, and a gyroscopic device mounted on a gimbal, the rotor of which is equipped with nozzle openings and a powder insert charge in the form of a cylindrical checker, characterized in that the inner frame the gimbal is made closed and covering the outer surface of the rotor and is equipped with a number of radial holes symmetrically spaced around the circumference in the plane of the nozzle holes sty, the total length of the openings in said plane is 0.3-0.6 circumference, and its propellant charge is placed on the outer surface of the annular projection of the same diameter, formed on the inner cylindrical surface of the rotor.

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