Tank-type container of warhead for liquid filler

FIELD: weapons and ammunition.

SUBSTANCE: tank-type container of warhead includes fairing, thin-walled tank body, front and rear bottoms, filler dispersion and ignition device. Buffer cavity where container weight compensators is made between the fairing and front bottom. Container fairing is designed as reinforced flat bottom with rounded edges attached to the container shell by screw connection. Front bottom of the container has a conical deflector shape. Deflector cone angle is 120-140°. Tank body features centring bulge at a distance of 3.6-3.8 of the calibre from the fairing. Filler dispersion and ignition device is positioned along longitudinal axis of the container and shifted inside the buffer cavity by 0.010-0.015 of its length and attached to a cross-shaped support.

EFFECT: enhanced efficiency of missile or ammunition with such container.

1 dwg

 

The invention relates to the field of rocketry and can be used in the development of combat troops incendiary type, equipped with thermobaric and demosaicing mixtures.

One of the important ways of improving the effectiveness of combat application of reactive projectiles and cannons is the development of combat troops, filled with liquid filler petroleum based incendiary actions to ensure that fire defeat of manpower and military equipment of the enemy. The main criteria of efficiency of action of missiles with such warheads are the fill factor is a mixture of free volumes of the design, the precision and accuracy of delivery of the munition to the target and the firing parameters of targets in the area of the enemy.

A known design of rotating missiles, containing the head part of a small elongation, filled with liquid filler petroleum based, air cavity, a device for spreading and ignition of the filler, rocket engine and empennage (see U.S. patent No. 3433437, CL. 244-3.23, publ. in R j "Arms", No. 7, 1970, p. 10).

This design rockets can improve the parameters of the firing of hitting the target due to the gear head portion with a liquid filler to compensate for thermal expansion �otorogu it is provided with an air cavity, since no air cavity under temperature variations may lead to violation of the integrity of the head. In addition, in the rocket with a warhead small elongation, displacement of the air cavity during the flight when changing the angular velocity of rotation of the missile does not result in violations of the imbalance masses in the head part and, therefore, has no effect on the stability of the rocket flight, accuracy and shooting accuracy.

Thus, the objective of this technical solution was to increase the effectiveness of fire damage targets through delivery to the target liquid filler in the head part of a small elongation without considering the influence of disturbing factors caused by the presence in the liquid filling the air cavity, without a presentation of requirements to ensure its fixation and stability of the missile in the trajectory.

Common features with the proposed design of the container tank type are the availability of capacity for equipment, liquid filler and device for spreading and ignition of the filler.

The closest in technical essence and the achieved technical result is incendiary rotating the head part of the rocket, in the tank which is behind the center of mass of the head portion diaphragm placed symmetrically located hole�plants, a device for spreading and ignition of the filler is made in a thin-walled cylindrical glass that is installed along the longitudinal axis of the head portion between the fairing and the diaphragm adopted by the authors for the prototype (patent RF №2174670).

The specified construction of the head part allows to solve the problem of fire damage target by performing in the tank behind the center of mass of the head portion of the diaphragm with symmetrically spaced holes with certain parameters and to provide damping of the vibrations of the filler, making for filler and moving it in the air cavity occur without fluctuations that negatively affect the flight of the rocket.

Device for spreading and ignition of the filler in a thin-walled cylindrical glass that is installed along the longitudinal axis of the head portion, accelerates the process of formation of the Central air channel at the expense of space in the area damped oscillations of the hard filler homogeneous rod (glass), around which is a slowdown in the flow of the filler, its subsequent separation from the stem and the formation of a vortex around him.

Task known invention (prototype) is to increase the effectiveness of fire damage target incendiary warhead by accounting for the influence of starting settling�x overloads and vibrational motions of the missile body on the behavior in the liquid filler head portion of the air cavity and improving the sustainability of the flying rotating rocket guaranteed by fixation position air cavities in the liquid filler at the launch site trajectory of the rocket.

Common features with the proposed design of the container tank type are the presence of thin-walled shell-tank equipment for liquid-filled, front and rear Dony, devices for spreading and ignition of the filler and fairing in front of the bow.

Unlike the prototype proposed by the authors in the design between the fairing and the front bottom is made of a buffer cavity, wherein the compensator mass of the container.

The fairing of the container made in the form of a reinforced flat bottom with rounded edges, fastened to the shell of the container by threaded connection.

The front bottom of the container made in the form of a conical reflector, a corner solution which is 120-140°.

The case-the tank is provided with a centering thickening, placed at a distance of 3.6-3.8 caliber spinner.

The device of the dispersion and ignition of the filler is located along the longitudinal axis of the container and offset inside the buffer cavity to 0,010-0,015 its length and bonded with cross-shaped support.

It allows to make a conclusion about the causal connection between the set of existing features of the proposed technical solution and achievable technical�Kim result.

These features, distinct from the prototype and covered by the requested amount of legal protection, in all cases sufficient.

The object of the invention is to increase the combat effectiveness of an opponent by increasing precision and accuracy of fire, reduce the depth of the container in the ground, improve the conditions of the dispersion and ignition of the liquid filler.

Said technical result of the invention is achieved in that in the known structure of the container containing the fairing, thin-walled corpus-tank, front and rear Dona, a device for dispersion and ignition of the filler between the fairing and the front bottom is made of a buffer cavity, wherein the compensator mass of the container, wherein the fairing of the container made in the form of a reinforced flat bottom with rounded edges, fastened to the shell of the container by threaded connection, the front bottom of the container made in the form of a conical reflector, a corner solution which is 120-140°, body-tank provided with centering thickening, placed at a distance of 3.6-3.8 caliber of the fairing device of the dispersion and ignition of the filler is located along the longitudinal axis of the container and offset inside the buffer cavity to 0,010-0,015 its length and the fastener�but with a cross-shaped support.

The new set of structural nodes and elements, as well as the presence of causal relationships between them allows to solve the task.

In particular, the execution of the fairing in the form of a reinforced flat bottom with spherical edges and fixing of expansion joints in mass allows, on the one hand, to increase the strength of the input side of the container, to reduce the penetration into the soil and to maintain the performance of the buffer cavity to shift the center of gravity in the fore part of the container and to increase the aerodynamic stability of its movement, and on the other hand, to reduce the magnitude of the force of drag acting on the container during the movement along the trajectory, which, ultimately, allows to improve the accuracy and accuracy of fire.

To improve aerodynamic stability in flight promotes placement in the front of the hull-tank centering thickening, placed at a distance of 3.6-3.8 calibre from the fairing. As in the previous case, this technique allows you to shift the center of gravity of the structure in the direction of the bow, and also increases the rigidity of the front part of the container in the initial period of burying it in the soil, which also has a positive effect on stability of the dispersion and ignition of the filler on the target surface.

At the same�enny, the presence between the fairing and the front bottom of the buffer cavity, leads to the fact that through the use of energy gases generated during actuation of the device for dispersion and ignition of the filler is created in the buffer cavity of the gas cushion, braking the container in the ground, and thus provides a more reliable dispersion and ignition of the liquid filler.

Thereby the front bottom of the container in the form of a conical reflector with angle approx 120-140° allows to reduce the depth of the container in the soil and significantly increase the completeness of detonation scattered filler.

This also contributes to the implementation of the fairing in the form of a reinforced flat bottom with spherical edges, fastened to the shell of the container by threaded connection. Threaded connection is destroyed in the process of meetings of the container with a barrier at a certain pressure in the buffer cavity arising from actuation of the front of the device for dispersion and ignition of the filler component 0,010-0,015 from its full length.

The supply device for the dispersion and ignition of the filler on the end of cross support, limits the radial displacement of the device and eliminates its failure, as in the process of filling the tank, and when moving along the trajectory, characterized by the presence�education high angular accelerations.

The invention is illustrated by drawings, where Fig. 1 is a perspective view of the tank container type to accommodate the liquid filler.

The proposed tank container type warhead for placement of liquid filler fairing contains 1, thin-walled corpus-tank 7, the front bottom 4, the rear bottom 9, a device for dispersion and ignition of the filler 5 is offset inside the buffer chamber And on the value of B, the compensator masses 2, thread 3, the centering thickening 6 placed at a distance L from the fairing, Phillips prop 8.

The above-described device starts to operate during the movement of the head portion along the trajectory, wherein the execution of the fairing 1 in the form of a reinforced flat bottom and attaching it compensators mass 2, as well as the supply container centering thickening 6, placed at a distance L from the fairing, allows to realize a positive quality, ensuring the maximum displacement of the center of gravity in the fore part of the container and increase the aerodynamic stability of motion, and execution of the fairing 1 with rounded edges reduces the magnitude of the force of drag, which ultimately increases the precision and accuracy of fire.

The use of cross support 8, rigidly connected with the device of the dispersion and ignition of the filler 5, VI reduces�the radio device, caused by the presence of angular accelerations and keeps it from breaking.

At the meeting the head part with the aim of runs the device dispersion and ignition of the filler 5.

The implementation of the buffer cavity And the angle β=120-140° front bottom 4, where the device of the dispersion and ignition of the filler 5, the offset value B of its length, allows to reduce the depth of the container in the soil and significantly increase the completeness of combustion scatter of the filler due to the rapid destruction of the threaded connection 3 and the creation of a gas cushion in the buffer cavity and thereby reduce the speed and magnitude of the depth of the container in the ground.

As a result liquid filler in the corpus-tank 7, is scattered over a larger area goals and provides increased fire damage target.

As the results of theoretical and experimental works, the execution of the head portion in accordance with the invention has improved the efficiency of fire damage, as well as to improve the precision and accuracy of delivery of the warhead to the target.

The present invention may be used for the design of combat troops incendiary type, curb or thermobaric demosaicing mixtures.

Specified positive effect is confirmed by tests of prototypes of �aket with incendiary warheads, made in accordance with the present invention.

Currently developed design documentation, tests and scheduled the manufacturing of the product.

The tank container type warhead for placement of liquid filler containing fairing, thin-walled corpus-tank, front and rear Dona, a device for dispersion and ignition of the filler, characterized in that between the fairing and the front bottom is made of a buffer cavity, wherein the compensator mass of the container, wherein the fairing of the container made in the form of a reinforced flat bottom with rounded edges, fastened to the shell of the container by threaded connection, the front bottom of the container made in the form of a conical reflector, a corner solution which is 120-140°, body-tank provided with centering thickening, placed at a distance of 3.6-3.8 caliber of the fairing device of the dispersion and ignition of the filler is located along the longitudinal axis of the container and offset inside the buffer cavity to 0,010-0,015 its length and bonded with cross-shaped support.



 

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