RU44813U1 - Ammunition for ampoule flamethrower - Google Patents

Description

The utility model relates to the field of defense technology, namely to ampoule flamethrowers. It can be used in incendiary shells, missiles and aircraft bombs to destroy manpower located in sheltered buildings, structures, cars, as well as to create fires in these facilities and on the ground in all weather conditions. Defeat of targets is achieved by a burning jet of fire mixture.

Flamethrowers are known that use the displacement of a “cold” (non-burning) flame mixture from a cylinder, followed by its acceleration in the hydrotract and nozzle, the formation of a jet in the front section of the nozzle, and ignition of the jet along the trajectory with an incendiary torch torch. For example, the light infantry flamethrower LPO-50 and the heavy infantry flamethrower TPO-50, in which the flame throwing method, which involves displacing the mixture from a cylinder and then accelerating it in a hydrotract ending with a nozzle, forming a jet at the front end of the nozzle and igniting the jet on the trajectory with an incendiary cartridge torch (stars) is implemented in a jet heavy flamethrower.

A significant drawback is the small range of flame throwing. The flame throwing range can be increased by a large pressure of displacing the flame mixture (higher jet velocity) and, as a result, a large nozzle diameter and a large capacity of the cylinder with the flame mixture. However, a further increase in the range of flame throwing is associated with a violation of the integrity of the flame mixture due to the increased influence of the drag force of the air.

This disadvantage is eliminated in ampoule flamethrowers. Currently, widespread incendiary ammunition for ignition of objects and destruction (destruction) of various targets. The thermobaric combustible mixtures developed in recent years have allowed the creation of small-sized ammunition (grenades) for ampoule flamethrowers to destroy objects in a closed and half-closed space. Known ammunition design (US patent No. 3974774, CL F 42 B 13/46, 1976) with liquid filling contains an ampoule filled with a self-igniting fire mixture. Inside the ampoule along its axis there is an ignition-explosive charge in the form of a tube with a fuse and an ignition-explosive charge. In flight, the ammunition is stabilized by a stabilizer with expanding blades.

The closest in technical essence to the claimed ammunition is the "Method of destruction of a grenade with a volume-detonating mixture and grenade for ampoule

flamethrower ”according to the patent of the Russian Federation on invention No. 220/1820, IPC F 42 V 12/52, 1994. The ampoule flamethrower contains a housing with equipment, a central tube with a fuse and a stabilizer with expandable blades.

When fired, the products of combustion of the powder charge act on the rear bottom of the munition, dispersing it along the launch tube of the flamethrower until the required speed is reached. The range of the grenade depends on the magnitude of this speed and the elevation angle of the flamethrower.

Modern requirements for flamethrowers require a further increase in the range of flamethrowing.

The objective of the utility model is to increase the combat effectiveness of flamethrowers by increasing the range of flamethrowing.

The technical result that can be obtained using the utility model is to reduce the bottom resistance of the capsule with a flame mixture, which leads to a decrease in the resistance to movement.

The problem is achieved by the fact that in the tail of the capsule is a bonded solid fuel charge of ballistic fuel with a low burning rate. the shape of the inner surface of which repeats the external shape of the profile of the powder engine.

The invention is illustrated in the drawing (figure 1),

where: 1 - capsule;

2 powder engine;

3 perforated glass;

4 stabilizers;

5 - case;

6 - self-igniting flammable mixture;

7 - solid fuel charge;

8 - centering belts;

9 - perforation.

Ammunition for an ampoule flamethrower contains a capsule 1, a powder engine 2 and a perforated glass 3 with drop-down stabilizers 4 mounted at an angle to the longitudinal axis of the projectile. Capsule 1 is a thin-walled case 5 with a self-igniting flame mixture 6. In the rear part of capsule 1 there is a bonded solid fuel charge 7 of ballistic fuel with a low burning rate. The shape of the inner surface of the solid fuel charge 7 repeats the external shape of the profile of the powder engine 2. This embodiment contributes to

decrease in free volumes. The burning surface area and the mass of solid fuel charge 7 are calculated from the conditions of the flight of the ammunition to the maximum range.

On the side wall of the housing 5, centering belts 8 are formed, the diameter of which decreases towards the front end of the munition. At the bottom of the munition, a perforated glass 3 is fixed with a centering belt at its rear end. In this case, the perforation 9 is made at the bottom of the ammunition, and the skid stabilizers 4 are fixed on the glass 3 between the perforation and the centering belt, the diameter of which is made corresponding to the caliber of the flamethrower.

Ammunition for an ampoule flamethrower works as follows.

Ammunition is launched by issuing a command to the igniter igniter. Under the influence of temperature and pressure of the powder gases generated during the operation of the igniter, the powder charge of the engine 2 ignites. Due to the outflow of gases from the nozzle of the powder engine 2, the munition starts to move.

When launched, propellant propellant gases act on the rear bottom of the munition. accelerating it to the required speed. In this case, part of the powder gases through the perforation 9 in the glass 3 flows into the gap between the ammunition and the launch tube. This is accompanied by ignition of a solid fuel charge 7.

Since the centering belts on the side wall of the shell of the ammunition are made smaller than the internal diameter of the barrel, and their diameter decreases towards the front highlander, this makes it possible to ensure uniform compression of the ampoule by the pressure of powder gases, excluding the expansion of the thin-walled shell when it is fluidly equipped from the action of acceleration when moving along the trunk.

After starting, when the ammunition is still moving along the channel of the launch tube, the stabilizer blades 4 are in the folded position. After exiting the container guide, the blades of the stabilizer 4 of the ammunition are opened and installed at an angle to its longitudinal axis, which ensures a steady movement on the trajectory.

It is known that the aerodynamic form of ammunition affects the firing range through their aerodynamic characteristics. The aerodynamic characteristics of the ammunition are determined by its shape factor. A decrease in the shape factor of the ammunition leads to a decrease in the force of air resistance, which ensures an increase in the firing range at the same initial speed. The air resistance force includes three components: wave, viscous friction and vortex. The share of these components in the total value of the air resistance force depends on the velocity of the ammunition (see table).

At subsonic velocities of the movement of ammunition, air resistance is determined mainly by the vortex component, at supersonic wave and vortex velocities

components.

Components of air resistance Component Projectile speed, m / s Subsonic Supersonic Wave - fifty Viscous friction 20-30 10-15 Whirling 70-80 35-40

The vortex component of air resistance is caused by the disruption of the air flow from the bottom of the munition. In this case, behind the bottom section of the munition, a discharged space forms into which undisturbed layers of air rush with the formation of vortices. In addition, the presence of rarefaction behind the bottom cut increases the pressure difference acting on the head of the munition and the bottom cut, which also leads to an increase in air resistance. To reduce the vortex component and the effect of air discharge behind the bottom section, it is necessary to ensure that the bottom part of the ammunition flows around the air stream.

During the flight, the force of the frontal resistance F acts on the munition, which is directed in the direction opposite to the munition flight and is determined by the following expression

where: F is the drag force;

C _x is the drag coefficient;

ρ is the air density;

V is the velocity of the ammunition;

S _m - midship section of the ammunition.

From the analysis of expression (1) it follows that the smaller the value of C _x , the lower the drag force F.

On the other hand, the drag force F is defined by the following expression

where: p _{1 the} pressure at the entrance of the ammunition;

p _{2 the} pressure at the outlet of the ammunition.

From the analysis of expression (2) it follows that the greater the pressure at the output of the ammunition p ₂ . the lower the drag force F.

Thus, a decrease in the bottom resistance value both by decreasing the value of C _x and by increasing the pressure at the output of the ammunition p _{2 ,,} is an effective way to increase the flight range of the ammunition.

Consequently, the installation of a solid fuel charge from ballistic fuel with a low burning rate in the tail of the capsule, which acts as a bottom gas generator, increases the pressure at the outlet of the munition, which reduces its bottom resistance, and, consequently, reduces the drag force. In turn, this leads to an increase in the range of the munition.

Claims (1)

Ammunition for an ampoule flamethrower, including a capsule and a powder engine, characterized in that in the rear part of the capsule there is a bonded solid fuel charge of ballistic fuel with a low burning rate, the shape of the inner surface of which repeats the external shape of the profile part of the powder engine.