PL189798B1 - Armor-piercing shell - Google Patents

Abstract

1. The armour-piercing shell is designed to pierce an armoured target. It is an artillery shell or a guided missile, equipped with a rocket acceleration engine to increase the missile velocity in the final flight phase. It is characterised in that it is equipped with an additional flight rocket engine (117, 401) to ensure a constant or increasing velocity of missile flight. The rocket propellant (116, 402) is stored in the external housing (118, 416). It is also equipped with a known acceleration engine (109, 405), consisting of the accelerating rocket propellant (106, 406), located in the housing (108), and of the set of nozzles (102,420). 12. The method of propelling an armour-piercing missile, designed to pierce an armoured target. It is characterised in that first, the propellant charge is ignited. The charge is contained in the gun chamber and gives the missile its initial flight velocity. Then, the flight engine (117, 401) is activated to ensure constant or increasing flight velocity. In the final flight phase, before the missile (100, 400) hits an armoured target (340, 536), the acceleration rocket engine (109, 405) is activated to increase the velocity of the missile (100, 400) flight up to the penetration speed, at which the missile hits the target and penetrates the armour.

Description

The subject of the invention is an anti-tank missile intended to penetrate an armored target and constituting an artillery missile or a guided missile equipped with an acceleration rocket engine for increasing the speed of the missile in the final phase of flight.

The invention also relates to a method of propelling an anti-tank missile intended to penetrate an armored target.

The use of armor to protect combat forces is widely used in hostilities. Land combat vehicles, such as tanks, are armored to protect the vehicle crew from enemy fire. Armored fighting vehicles are highly vulnerable to enemy attack, and therefore they are equipped with additional protective devices, for example a shield applied to the outer surface of the armor filled with water or an explosive charge, or a combination thereof, which generates a force in the event of a bullet impact. approximately equal and opposite to the explosive force of the projectile, reducing the possibility of its penetration.

The defense forces use conventional ballistic missiles in defense, aimed at the target with a sight mounted on the barrel of a gun. Both conventional and guided missiles designed for this purpose are used to defend against attack. In order to achieve high accuracy of conventional and guided missiles, many attempts have been made to launch the missile by the defense forces towards the target from a safe distance. However, after reaching their target, these projectiles, due to air resistance, do not have sufficient velocity to sufficiently penetrate the target's protective armor. In order for a projectile to hit, for example, an armored vehicle at a sufficient speed, called penetration speed, the defense forces must either approach the target or wait for the attacking armored vehicle to come close enough to them. However, reducing the distance between the defense forces and the attacking armored vehicle increases their threat accordingly.

Some combat vehicles are also specially armored against close-range attacks. The most modern land-based combat vehicles are equipped with reactive armor which, when struck by a projectile with a high velocity sufficient to penetrate it, activates, reducing the impact kinetic energy, thus preventing serious damage to the target.

Land defense forces face similar problems with armored helicopters or armored planes attacking ground targets. Ground installations, for example for the protection of decision-making operational centers, are usually armored to protect against attack, especially from enemy overhead attacks, by using aircraft that fire both free artillery and guided missiles. An air attack usually supports defense forces, which are ineffective against armored vehicles, as the impact speed of an ordinary armored projectile is too slow to significantly damage an armored target.

From the US patent specification US 5,189,248 a projectile is known to pierce targets having high mechanical strength, especially concrete surfaces of airport runways. This air-to-ground missile is fired from a very low height, making it impossible to be destroyed by surface-to-air defense. In order to increase the effectiveness of the projectile, it is equipped with a braking system in the form of a parachute fired and an additional projectile path correction system in the form of

189 798 of a gasoline-powered jet unit, with nozzles directed forward, embedded in the center of the projectile, which provides a direction of the velocity vector, at the moment of hitting the target, close to the vertical direction. After an appropriate time from the launch of the missile from the plane, the accelerating drive motor located in its rear part is fired, and then the parachute is ejected and the recoil braking force appears at the same time. Both of these factors slow down the projectile's motion, changing its direction to vertical. After the parachute is ejected at a height of about 40 m, the strong recoil accelerates the vertical movement of the projectile to the ground, increasing its penetration capacity and overall effectiveness. A significant disadvantage of this solution is the complex structure of the missile and the lack of certainty of its correct operation, especially when ejecting the parachute.

U.S. Patent No. 5,363,766 discloses an unguided jet armor-piercing projectile fired from a gun, with its jet engine, maintaining a constant speed of the projectile, located in its front part, and its jet nozzles - near its center of gravity, and the warhead - in the middle of the missile. The rear part of the projectile is equipped with stabilizing fins. The jet engine is slidably connected to the warhead, which moves forward when the projectile hits the target, while the jet engine surrounding the penetrating shaft disintegrates. Placing the jet engine in the front part of the missile maintains its spatial stabilization in flight to the target.

The described projectile is intended especially for piercing the thick armor of tanks, the use of a jet engine shortens the time from launching the projectile to hitting the target. The main disadvantage of this solution is the relatively low value of the target impact velocity, lower than the penetration velocity.

From US Patent No. 5 596 166 a penetrating missile is known, consisting of a front part containing an explosive charge and a rear part equipped with an accelerating rocket engine. The missile is further provided with a fuse that activates the rocket engine when the missile hits the target, the rocket motor's large and short recoil force counteracting the braking effect of the missile on hitting the target and increasing the depth of penetration of the target. For this purpose, the rocket engine is provided with an acceleration propellant the amount of which corresponds to a recoil force of at least 62.5 kN, operated for less than 0.5 s.

The missile is intended especially for penetrating very hard targets, for example walls of underground structures covered with additional protective layers or airfield surfaces.

A significant disadvantage of this solution is the launch of the rocket engine when the missile hits the target, which often causes the engine to disintegrate while it is being started.

The object of the invention is to develop such a structure of an anti-tank missile, in particular a long-range artillery projectile, which will enable it to hit an armored target with a significant velocity at least equal to the penetration speed which will penetrate its armor.

This aim is accomplished by the anti-tank missile according to the invention, which is characterized in that it is additionally equipped with a flight rocket engine for maintaining a constant or increased flight speed of the missile, equipped with an external flight rocket fuel, and at the same time with a known acceleration engine consisting of housed in the acceleration rocket fuel housing and the nozzle array.

In No. 7vnadkn pdv pressure of wcdbiP dtannw pressure of artvlcrviski nałflC7anv 7P g --- yg --------- s g ------- ----- a J ---------- ---------- f - r ---- g ---- with a ------ known shell containing a propellant charge, the flight fuel of the flight rocket engine surrounds a ring layer of the accelerator fuel of the rocket accelerator, and in the case of a guided missile, for example of the air-to-ground type, preferably the accelerator rocket motor is located at the front of the missile in series with the engine located at the rear of the missile.

The armor-piercing projectile according to the invention is preferably equipped with a bar slidably mounted inside it, along the projectile axis, for penetrating the target's armor, and preferably

189 798 also coupled with it and placed in the chamber in the front part of the projectile, a device for penetrating a reactive target, equipped with reactive armor.

The reactive target penetration device is provided with a neutralizing missile, with a reactive armor of the target, and a firing device for the neutralizing missile prior to hitting the target of the anti-tank missile, the neutralizing missile being preferably a shooting cartridge.

Moreover, the missile according to the invention is equipped with an electronic communication system for changing the trajectory of the missile consisting of a transmitter and a receiver, and is preferably equipped with a missile guidance system consisting of a target detection sensor and an electronic system for controlling the missile trajectory.

The target detection sensor is preferably a radar signal detection sensor or a sensor for detecting radiation emitted by the target, in particular infrared radiation.

The object of the invention is also realized by a method of propelling an anti-tank missile intended to penetrate an armored target, characterized in that a propelling charge contained in a casing in the chamber of a gun is ignited forward, giving the missile a muzzle velocity of flight, while the flight engine is switched on, keeping a constant constant or increasing flight speed, while in the final phase of flight, before the projectile hits the armored target, the rocket accelerator is activated, increasing the projectile's flight speed to the value of penetration speed at which the missile hits the target and penetrates its armor.

At a predetermined time, prior to the projectile hitting the target, the firing unit for target penetration devices equipped with reactive armor preferably fires a neutralizing projectile which strikes the target before the projectile strikes it.

The rocket flight engine of the projectile according to the invention is preferably activated in the initial phase of its flight, within a certain time after launching the missile.

The armor-piercing projectile according to the invention is shown in an exemplary construction in the drawing, in which: Fig. 1A shows the artillery projectile according to the invention in an axial section; 1B shows the same artillery shell in cross-section; Fig. 1C shows an artillery shell with a shell containing a propellant charge prior to its launch; Fig. 2 shows an axial section of a variant of the artillery shell according to the invention; Fig. 3 shows the flight trajectory of an artillery shell fired from a gun at an armored target; Fig. 4 shows an air-to-ground guided missile according to the invention, and Fig. 5 shows the trajectory of a guided missile launched from the aircraft to a designated target.

The anti-tank artillery or guided missile according to the invention should hit the armored target at a speed that allows armor penetration, that is, with penetration speed. In flight, the speed of the projectile according to the invention is kept by the rocket flight motor at the level of the so-called flight speed, which, before hitting the target, is increased by the rocket acceleration motor to the value of the penetration speed.

A rocket flight engine preferably contains rocket fuel, although in some cases it may only contain propellant which, once fired, maintains the missile's flight speed at its initial muzzle velocity. In contrast, the accelerator rocket engine preferably contains rocket fuel which, when fired, increases the flight speed of the missile to penetration speed.

The artillery shell 100 according to the invention, shown in Figures 1A, 1B and 1C, can be launched from a tank or from a gun and is equipped with a rod 104 penetrating the armor of the target, with the propelling fuel 106 surrounding the rod 104 contained in the housing 108, and with flight 116 fuel coaxially about said housing 108.

The inner casing 108 with the propellant propellant 106 contained therein, which is ignited later in the flight of the projectile 100, before it hits the target, and with the muzzle 102 or nozzle arrangement 102 at the end of the shell 108, form a rocket accelerator 109. with considerable thrust. In order to obtain the maximum acceleration value for a short period of time, the acceleration propellant 106 should preferably be a high-fossil fuel.

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The bar 104 piercing the target armor, embedded in a non-illustrated sleeve located along the axis of the projectile 100, may be suitably long and thin and terminated at the front with a blade so that upon impact on the target it is possible to concentrate the penetration force on the smallest possible surface. The rod 104 is made of a high-strength steel, or a tungsten alloy or other similar hard material.

The artillery shell 100 is further preferably equipped with a number of flight stabilizers 114 (Figures 1A and 1B) which decompose immediately after firing and increase the aerodynamic stability of the projectile.

The propulsion propellant 116 of the artillery missile 100, coaxially disposed about propellant acceleration 106, resides within the outer shell 118 of the missile, together forming a rocket engine 117 that provides the artillery shell with thrust for a relatively long period of time. Flight propellant 116 is ignited during the launch of the projectile 100, or somewhat later, when the projectile has reached flight speed and burns relatively slowly, providing it with relatively little thrust to maintain a constant or slightly increasing projectile speed. Thanks to this, its range is significantly increased and, moreover, by minimizing the influence of yaw forces, e.g. from crosswinds, its accuracy is increased.

The artillery shell 100 shown in Fig. 1C is connected to a shell 122 containing a propellant charge which causes the projectile to be launched and is provided with a fuse 126, which is, for example, a primer or an electrically activated fuse. The tightness of the joint between the projectile 100 and the shell 122 is ensured by the gasket 112.

The operation of the artillery shell 100 is as follows: the artillery shell 100 is fired at the target 340 from the artillery gun 338 (Fig. 3). Activation of the fuse 126 ignites the propellant contained in the shell 122, and the force of the explosion from the powder gases ejects the projectile 100 from the gun 338 at a muzzle velocity. Simultaneously or with a delay, the flight 116 propulsion fuel of the flight 117 rocket engine is ignited (FIG. 1A). The thrust generated by this engine 117 maintains a constant or slightly increasing flight speed of the projectile 100, and the stabilizers 114 ensure the flight stability.

Prior to the impact of the projectile 100 on the armored target 340 (Fig. 3), the propellant fuel 106 of the rocket accelerator 109 is ignited in the shield 108 of the propellant fuel 108. The propulsion propellant 106 may also be ignited at any time determined by the operator of the weapon. , for example, by using a proximity sensor at the front of the missile 100. The rocket accelerator 109 increases the velocity of the missile 100 to the penetration velocity at which it hits the target 340. The impact force of the projectile 100 and the increased momentum of its rod 104 ensure penetration of the armored target 340 at least through this rod 104.

2 shows a structural variant of the artillery shell 200 according to the invention, provided with a conical tip 240 and an electronic communication system therein consisting of a radio receiver 230 and a radio transmitter 232. Thus, the missile operator 200 is able to transmit to the receiver 230. instructions in the form of electromagnetic or light signals in response to received flight information transmitted by transmitter 232. Receiver 230 and transmitter 232 may also be an integrated transceiver with relatively little space. The communication system allows the operator to control the artillery shell 200, and even change its flight trajectory if necessary.

The anti-literal missile 200 is further preferably equipped with an on-board apparatus to neutralize the target's protective devices, or with a small firing device 234 towards an armored target 340 (Fig. 3) - a neutralizing missile 236 just before the artillery shell 200 hits it. may be a regular shot cartridge, then it activates the reactive armor of the target 340 (Fig. 3), thanks to which the artillery projectile hits the target already unprotected, allowing it to penetrate deeper through the rod 104.

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The combined operation of the artillery projectile 200 according to the invention is as follows: The artillery projectile 200 is fired at an armored target 340 from a tank gun or from an artillery gun 338 (Fig. 3), e.g. a howitzer, leaving the gun at point A at muzzle velocity. At point B of the projectile trajectory, the propellant of flight 116 ignites, whereby the speed of the projectile 200 increases to the value of flight speed. At trajectory C, a predetermined distance from target 340, the accelerator propellant 106 is ignited, causing the projectile velocity 200 to increase to penetration velocity. Both the propellant 106 and the propellant 116 are preferably ignited at a precise time by the operator. At a short distance of the projectile 200 from the target 340, a neutralizing projectile 236 is fired at it, which activates the reactive armor of the target 340, thereby allowing the rod 104 to penetrate deeply into the target 340.

Fig. 4 shows a further design of the missile according to the invention, which is an anti-tank guided missile 400, equipped with a rocket acceleration engine 405 and a flight engine 401 arranged in series with it at the rear of the missile, and with 405 and 401 inside these engines. piercing rod 408 the target's armor. The piercing bar 408 is slidably mounted in a sleeve 409 located along the axis of the projectile 400.

A rocket flight engine 401 equipped with propellant flight 402 contained in the housing 410 and nozzles 414 contained in the housing 412 gives the guided missile 400 a constant flight speed.

Rocket accelerator 405, located between the forward compartment 424 and the flight rocket engine 401, is provided with propellant accelerator 406 contained within housing 416 and provided with an axial passage 404 and nozzles 420 contained within housing 418. Propellant accelerator 406 it has the form of a hollow cylinder, provided in the center with a channel 404, which serves as a combustion chamber for the acceleration fuel 406. Due to the large combustion area it is possible for a sufficiently large volume of hot exhaust gas to escape through the nozzles 420, giving the guided missile 400 a penetration speed many times greater than the flight speed projectile.

After the acceleration fuel 406 is consumed, the flight rocket engine 401 is disconnected from the missile 400 and rejected approximately halfway along the flight path. As a result, the onward guided missile 400 has a much lower mass compared to the initial mass and can reach a correspondingly high speed when the rocket accelerator 405 is turned on.

The missile 400 is further equipped with a signal sensor 428 connected to the electronic system 426 and to the guidance system 422 residing in the chamber 424.

The signal sensor 428, which is adjacent to the sensor dome 430, receives the signals, e.g., a radar signal or infrared radiation, generated by the tracking target and transmits them to an electronic system 426 that processes the received signals, calculating the position and distance of the target 536 from the projectile 400 (Fig. 5), after which it transmits processed information to the guidance system 422, determining possible changes in the trajectory and flight speed of the guided missile 400. When the guided missile 400 reaches point B of the flight trajectory at a certain distance from the target 536 (Fig. 5), the electronic system 426 ignites the accelerator propellant 406 (FIG. 4) while simultaneously disconnecting the flight rocket engine 401 from the missile 400. Turning on the accelerator rocket engine 405 causes the missile speed 400 to increase to the penetration velocity value. However, before the guided missile 400 hits the target 536. ieeo the team foundalaiacv 432 fires a projectile neutralizuiacv 434.which hitting> y <y χ xyy - a Γ '' icy 'yyc at the target 536 activates the reactive protective armor of this target, and only then on this target now devoid of reactive protection, it hits the guided missile 400 piercing its armor.

Although the above-described armor-piercing projectile according to the invention is illustrated only by a few exemplary constructional solutions, of course other constructional variations as well as modifications to the above-described solutions are possible.

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FIG. 3

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Publishing Department of the UP RP. Circulation of 50 copies

Price PLN 2.00.

Claims (14)

Patent claims 1.An armor-piercing missile intended to penetrate an armored target and constituting an artillery missile or a guided missile, equipped with an acceleration rocket engine to increase the speed of the missile at the end of the flight, characterized in that it is additionally equipped with a flight rocket engine (117, 401) for maintaining a constant or increased flight speed of the projectile, equipped with a rocket fuel (116, 402) housed in the outer casing (118, 416), and at the same time with a known acceleration engine (109, 405) consisting of fuel housed in the casing (108) accelerator rocket (106, 406) and the nozzle system (102,420). 2. A bullet as claimed in claim The method of claim 1, characterized in that it is an artillery projectile (100, 200) connected to a known case (122) containing a propelling charge, the flight fuel (116) of the rocket flight engine (117) surrounding the annular layer of the accelerator fuel (106) of the rocket engine acceleration (109). 3. A bullet according to claim The rocket accelerator (405) is disposed at the front of the projectile in series with the flight engine (401) located at the rear of the missile as claimed in claim 1, wherein the missile is an air-to-ground guided missile. 4. A bullet according to claim 1 A bar as claimed in claim 1 or 3, characterized in that it is provided with a rod (104, 408) slidably mounted inside it along the projectile axis (100, 400) for piercing the armor of the target (340, 536). 5. A bullet according to claim 1 A device for penetrating a reactive target (340, 536) provided with reactive armor, coupled thereto and housed in the chamber (424) in the frontal portion of the projectile (400). 6. A bullet according to claim 6 5. A method according to claim 5, characterized in that the reactive target penetration device (340, 536) is equipped with a neutralizing missile (236, 434), a target reactive armor (340, 536) and a firing assembly (234, 432) that neutralizing missile (236 , 434) before hitting the target (340, 536) of the anti-tank missile (400). 7. A bullet according to claim 1 6. The method of claim 6, characterized in that the neutralizing projectile (236, 434) is a shooting cartridge. 8. A bullet according to claim 1 The method of claim 1, characterized in that it is equipped with an electronic communication system for changing the trajectory of the missile consisting of a transmitter (232) and a receiver (230). 9. A bullet according to claim 1 The method of claim 3, comprising a missile guidance system (422) comprised of a target detection sensor (428) and an electronic system (426) for controlling the missile trajectory. 10. A bullet according to claim 1 The method of claim 9, wherein the target detection sensor (428) is a radar detection sensor. 11. A bullet according to claim 11 The method of claim 9, characterized in that the target detection sensor (428) is a target detection sensor, particularly infrared radiation. 12. A method of propelling an anti-tank missile intended to penetrate an armored target, characterized in that the propelling charge contained in the shell in the gun chamber is ignited forward, giving the missile muzzle velocity, while the flight engine (117, 401) is turned on, keeping steel or increasing airspeed, while in the final phase of the flight, before the projectile (100, 400) hits the armored target (340, 536), the rocket acceleration engine (109, 405) is activated, increasing the flight speed (100, 400) to the value penetration speed at which this projectile hits the target, penetrating its armor. 189 798 13. The method according to p. The method of claim 12, characterized in that, at a predetermined time, before the projectile hits the target, the firing unit (234, 432) of the target penetration device (340, 536) equipped with reactive armor fires the neutralizing projectile (236, 434), which hits on the target (340, 536) before the projectile (100, 400) hits it. 14. The method according to p. The method of claim 12, characterized in that the rocket flight engine (117, 401) is activated in the initial phase of its flight, within a certain time after the missile (100, 400) has been launched.