KR20210154056A - K-9 Sky Increasing Speed Cannon Shot - Google Patents

Abstract

The present invention relates to an anti-aircraft canister which intercepts long-range artillery or low-altitude missiles from the rear by improving a barrel and shells of the K9 thunder. More particularly, the present invention relates to an anti-aircraft canister which fires at an increased initial speed with a barrel that accelerates shells, and then flies while aiming with a heat-tracking image sensor, separates into 37 shells to intercept from the rear of the enemy shells, and deploys a parachute and retrieves the shells that cannot be shot down before falling to the ground.

Description

K-9 Anti-aircraft Accelerated Shotgun {K-9 Sky Increasing Speed Cannon Shot}

The present invention relates to an anti-aircraft shotgun that intercepts enemy long-range shells or low-altitude missiles from the aft by improving the barrel and shells of the K-9 self-propelled howitzer, and more specifically, to a barrel that accelerates shells, firing at an increased initial speed, and heat tracking It is about an anti-aircraft shotgun that separates and intercepts 37 shotguns from the rear of the enemy bullets by aiming with an image sensor, and recovers the shotguns that cannot be shot down by opening a parachute before falling to the ground.

Intercepting enemy long-range artillery shells or low-altitude missiles from the front is very difficult with current technology. Even if a shell carried close to the ground at a speed of Mach 3 or 4 is caught by the radar, it is almost impossible to shoot down it considering the interception and missile firing rates. However, if you capture the direction, speed, altitude, and position of the enemy projectiles, accelerate the firing of anti-aircraft shells, and conduct guided intercepts from the aft, which is easy to track heat, the accuracy will increase. need to double

As shown in Fig. 1, when fuel is injected into the high-pressure oxygen gas tank (A11) and ignited, ultra-high pressure combustion gas is generated, and the piston valve (A07) is operated by the explosion pressure to release the high-pressure gas into the barrel (A01). When the barrel gas discharge rate is high, the shell's charge (A05) is ignited and fired. Since the rate of gas discharge in the barrel is faster than the rate at which the shell is discharged, the acceleration air resistance of the shell is reduced, and compared to when the shell is fired only with charge, the total gas emission is increased, which has the effect of increasing the speed of the shell.

The improvement of the shell is adhered with 37 hexagonal cross-section shells as shown in Figs. 2 and 3, but the adhesion is separated by the ignition temperature increase of the flight acceleration solid fuel (Na 09) in the shell, and it is ignited with a delayed wick (Na 06). Discharge the parachute (B03). Through the detection of the warhead's thermal tracking image sensor (Na 19), the firing timing of the 18 outer shells is controlled to intercept the aiming flight. 37 bullets discharge tail wings (Na10) during accelerated ignition to maintain flight accuracy. The heat tracking sensor circuit (B17) is protected by the initial firing buffer spring (B18) and serves as a safe storage function of the shell by closing the contact (B16) connection until the time of firing. The empty space of the streamlined warhead front shot is molded with foamed resin to reduce air resistance. Flight acceleration fuel is a solid fuel and, like rocket fuel, has a +-type space (FIG. 6) inside, and a tail wing (FIG. 7) is built in this space, and is discharged upon ignition. Of the 37 pellet solid fuels, 18 on the outside are ignited by the detection of a heat tracking sensor, and 19 on the inside are ignited by the power of the firing power at the same time as the shell is fired.

1 is a cross-sectional view of the barrel
Figure 2 is a perspective view of the spray nozzle (A02) of the barrel
3 is a cross-sectional view of the shell
Figure 4 is a side view of the shell
5 is a cross-sectional view of a pellet
Figure 6 is a block diagram of the heat detection sensor of the warhead
7 is a perspective view of pellet solid fuel (Na09);
Figure 8 is a perspective view of the tail wing (Na 10)
9 is a perspective view of a shotgun being dropped
Figure 10 is an external view of an initial flying shell
<Explanation of symbols for main parts of the drawing>
A01: gun barrel
A02: barrel spray nozzle
A03: barrel piping
A04: cannonball
A05: cannonball charge
A06: pressure regulating spring
A07: piston valve
A08: high pressure oxygen inlet valve
A09: fuel injection nozzle
A10: flue gas outlet valve
A11: high pressure tank
B01: Shotgun Armored Warhead
B02: Parachute connection line
B03: Parachute
B04: Parachute discharge piston
B05: Parachute ejection ammunition
B06: delayed wick
B07: Igniter
B08: Ignition Ammunition
B09: pellet accelerated solid fuel
B10: shot tail wing
B11: Bullet Acceleration Nozzle
B12: Thermal tracing convex lens
B13: ignition wiring
B14: heat tracking concave lens
B15: Contact closure insulator
B16: Heat tracing circuit contact
B17: Thermal Tracking Circuit
B18: buffer spring
B19: Thermal tracking image sensor

In the calculation of the capacity of the high-pressure oxygen tank (A11) and the injection nozzle (A09) pump, if the weight of the charge (solid fuel, gunpowder) of the 155mm caliber K-9 self-propelled artillery shell is about 30 kg, high-pressure gas is discharged into the accelerating barrel The weight of the oxidizer (oxygen) and the fuel to be used must be the same or greater, so if you calculate the capacity with 24 kg of oxygen and 6 kg of diesel, which is a 4 to 1 ratio of the oxidizer and fuel, 22.4 liters of 1 mole of oxygen, 0℃, 1 atmosphere When the molecular weight is 32 g, 24 kg ÷ 32 g is 750 moles to fill 24 kg of oxygen gas with an atmospheric pressure of 250 kg/cm 2 , and 3 moles when 750 moles are compressed with an atmospheric pressure of 250 kg/cm 2 . Since 1 mole is 22.4 liters, the capacity of the tank is 67.2 liters, which requires a diameter of 450 mm and a length of 423 mm. The fuel injected is 6 kg, and if the specific gravity of the case (diesel) is calculated as 0.85, an injection pump of 7.1 liters with a diameter of 200 mm and a length of 226 mm of 1000 kg/cm 2 of a high-pressure piston type with a crankshaft RPM6000 (0.01 seconds per rotation) is required. However, if it is difficult to produce realistically and the development period is delayed, it can be used by igniting solid fuel such as the charge of shells.

The shell is adhered to the shell with 37 hexagonal cross-sections, but the heat resistance temperature is set so that it is separated by the ignition temperature of the solid fuel in the shell. As for the parachute (Na03), when the solid fuel (Na09) is ignited, the delayed wick (Na06) is ignited, the falling ammunition (Na05) is ignited, and the falling piston (Na04) is operated and discharged by that force. The thermal tracking image sensor (B19) detects with the focus of the lenses (B12, B14) attached to the front warhead of the shell center, and the tracking circuit (B17) closes the contact by the action of the buffer spring (B18) when firing Through the insulator (B15), the contact (B16) and 18 aim flight ignition wires (B13) are connected. The empty space in front of the warhead is molded with foamed resin in consideration of air, friction, and heat resistance temperature. The tail wing (B10) protrudes from the pressure when solid fuel (Na09) is ignited by the igniter (B07) and ignited ammunition (B08) to maintain flight accuracy.

Claims (2)

A device that accelerates the cannonball by reducing the acceleration air resistance of the shell and increasing the flow rate of the high-pressure gas in the barrel by ejecting high-pressure gas just before the shell is fired with a number of injection nozzles (A02) that accelerate the airflow in the barrel Thirty-seven hexagonal cross-section pellets (Fig. 3, Fig. 4) are glued and fired at the same time, but are separated by internal combustion heat during flight and intercepted and failed to shoot down the enemy projectiles by aiming flight with partial ignition of the pellets by the heat tracking circuit. A device that ignites the drop ammunition (Na05) through (Na06) and discharges the parachute (B03).

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