DE102018009843A1 - Decelerated direct fire with bullet - Google Patents

Abstract

Control device (6) for a projectile (2) that can be fired from a gun barrel (8) with at least one braking element (12), which has a smaller braking force (F) in an idle state (R) and a larger braking force (F) in a braking state (B) for the projectile (2) against the direction of flight (10), and with an activation module (14) for the braking state (B) when a braking criterion (K) is met.
Projectile (2) with the control device (6), which is assembled with a base body (4) to form the projectile (2).
Method for operating the projectile (2), in which the projectile (2) is fired and at least one braking element (12) is brought into the braking state (B) during the flight.
Method for fighting a target object (44), in which the projectile (2) is fired at the target object (44) with increased elevation compared to a direct flight path (46), the braking state (B) is activated and the braked projectile (2) is lowered is deflected onto the target object (44).

Description

The invention relates to the control of a target object or target. The target object is particularly heavily armored (especially in the front or on the side / at the rear), but weaker armored on its top.

Such combat is known from practice on the comparatively weaker armored top of the target z. B. with the ammunition SMArt 155 (Wikipedia, 'SMArt 155', https://de.wikipedia.org/ wiki / SMArt_155, accessed November 20, 2018). The projectile is fired with a conventional propellant charge from an artillery gun and releases the submunition after a preset flight time and thus distance. The warhead is designed as a projectile-forming charge with a tantalum liner similar to a shaped charge projectile. Its capabilities enable it to combat all combat vehicles, including reactive armor. However, such ammunition is complex and expensive.

Such combat is also known in practice with steerable / controllable missiles, for. B. Spike (Wikipedia, 'Spike (Panzerabwehrlenkwaffe)', https://de.wikipedia.org/wiki/Spike_(Panzerabwehrlenkwaffe), accessed on November 20, 2018 or (unprotected in the next area, from cover) by RPGs (Wikipedia, 'RPG (weapon)', https://de.wikipedia.org/wiki/RPG_(Waffe), accessed on November 20, 2018).

The object of the present invention is to improve the abovementioned control.

The object is achieved by a control device according to claim 1. Preferred or advantageous embodiments of the invention and other categories of invention result from the further claims, the following description and the attached figures.

With a base body of a projectile to be created, the control device can be assembled to form the projectile or assembled in an assembled state. The assembled projectile can be fired from a gun barrel by means of a propellant charge. However, alternative transportation options are also possible (e.g. Railgun or similar). The projectile has a proper direction of flight (after the launch or after the acceleration phase, i.e. in flight).

“In accordance with the intended purpose” means that the projectile is fired according to its dimensions from a weapon provided for it to an intended destination or target object and has a certain direction of flight. The flight of the projectile thus follows its firing from the weapon.

The control device contains at least one braking element. The braking element is initially in a state of rest after the launch and during a flight of the projectile. In the idle state, the braking element has a smaller one (than in a braking state, see below), in particular no braking force or braking effect for the projectile against the direction of flight. The braking element can be put into a braking state during the flight. In this braking state, it has a greater braking force or braking effect for the projectile than in the idle state, in particular, therefore, a noticeable braking force or braking effect at all.

The control device contains an activation module. This is used to move the braking element after firing from the idle state to the braking state. The shipment takes place only when a braking criterion is met. After the launch, the braking criterion is checked (permanently or repeatedly). If this is not fulfilled, the idle state is maintained; if it is fulfilled, the braking status is triggered or activated.

In an intended assembly state, the control device is therefore assembled with the base body. “Intended” means that the control device is structurally matched to a certain or a certain type of base body or floor and is intended for use there; e.g. B. is designed for the geometry requirements determined thereby, etc.

The control device assumes the idle state in particular from the moment of completion, in particular from installation in the base body, in particular at the latest when it is fired.

By activating the braking state, a braking force or braking effect on the projectile is brought about in flight. There is therefore targeted intervention in the (regular) trajectory of the projectile (which in principle corresponds to that of conventional or guided ammunition, see below) through a controlled (activation of the braking state) speed change of the projectile. Thus, for example, a main battle tank that fires a corresponding projectile has an improved possibility to combat heavily (actively / passively) armored targets (also behind cover).

According to the invention, in particular a projectile that is conventionally used in direct fire (in particular tank ammunition, for example 120 mm smooth tube or 155 mm steering ammunition) can be raised Firing angle (elevation, see below) and by the braking mechanism (bringing the braking element into the braking state) on a final steeply decreasing (shortened) trajectory. This allows a warhead of the projectile to act on the target from above. Optionally (see below) sensors and steering can optimize the target approach with regard to accuracy.

The invention offers the advantage of a low price compared to guided missiles. There is the advantage of faster access, that is, shorter flight time than indirect fire of the artillery. There is direct feedback on mission success through direct observation. And there is the advantage that hard targets can be fought even behind cover with tank ammunition.

According to the invention, this results in “direct fire top attack ammunition” or a trajectory modification by means of a braking mechanism in direct fire with an induced top attack. Using a braking mechanism, direct, especially armor-piercing ammunition (hollow / P-load, see below) is transferred from a frontal hit to a top attack scenario. In particular, this brings the rapid and targeted effect of tank ammunition (direct fire) to the weakly armored top of a main battle tank.

The invention makes it possible to combat heavily armored targets (especially in the front) through the projectile, in particular a hollow or P charge (or combination) on the weakly armored upper side of the target (e.g. main battle tank).

The invention is suitable for both spin-stabilized and wing-stabilized projectiles.

In a preferred embodiment, the braking element is a passive braking element. When the projectile is in flight, the braking element has an aerodynamic effect which can be changed between the idle state and the braking state (no or noticeable braking force or braking effect which varies in strength). The braking element can be extended and / or moved in particular from the projectile and / or its aerodynamically effective cross section can be changed. Such brake elements are structurally particularly simple and inexpensive to implement.

In a preferred variant of this embodiment, the braking element is movable relative to the base body. In particular, the brake element can be extended and / or folded out, in particular it is a brake flap or a brake wing. This relates in particular to an outline shape of the projectile in the idle state. According to the invention, (activation of the braking state), in particular, additional brake flaps open as braking elements after a programmed time (braking criterion) and increase the air resistance of the projectile considerably.

In a preferred embodiment, the braking element is an active braking element (at least in the braking state). The braking element is therefore in some way energy-operated or uses energy to brake the projectile. It is conceivable to drive energy, stored in the control device, for braking purposes, etc. In this way, the braking force or braking effect can be increased compared to passively acting braking elements.

In a preferred variant of this embodiment, the braking element contains an activatable recoil device. This releases chemically stored energy in particular. During or after activation, the recoil device serves to generate a recoil force against the direction of flight of the projectile. At least the recoil force has a component against the direction of flight. A corresponding recoil device can be used particularly simply and effectively for braking.

In a preferred variant of this embodiment, the recoil device contains at least one outlet channel. The outlet channel serves to discharge a recoil. The outlet channel extends along an outlet direction, the outlet direction having at least one direction component in the flight direction. Recoil means or medium, which flows out of the outlet channel and thus also along the outlet direction, therefore likewise has a braking direction component against the flight direction. The outlet direction is in particular the central longitudinal axis of the outlet channel and in particular a straight line. Such a recoil device is particularly easy to implement and effective. Recoil means are, for example, compressed air, engine, fire or explosion gases, particles, the product of a (rocket) propellant, etc.

In a preferred embodiment variant of this embodiment, the recoil device contains an activatable (in particular rocket) propellant. The propellant serves to generate and / or release the recoil in the form of the propellant's product. The projectile can be braked particularly easily and effectively by means of an appropriate propellant charge.

In particular, the propellant charge is ignited after or at a programmed time after the projectile has been fired. The propellant charge then generates a backward thrust through the outlets (outer ends of the outlet ducts) facing forwards (in the direction of flight), which leads to the projectile being braked.

In a preferred embodiment, the braking criterion is an expiry of a predefinable flight duration after the projectile has been fired. In other words, a period of time between firing and activation of the braking state is set in the projectile. With the known flight speed of the projectile, the braking and thus the targeted deflection of the projectile can take place in a simple manner on a desired shortened trajectory to a desired destination.

In a preferred embodiment, the control device contains a steering module for controlling and / or regulating the trajectory of the projectile after it has been fired. The steering module can contain, for example, air guiding means such as movable steering wings, lateral acceleration devices such as thrusters, etc., in order to specifically change the shortened trajectory of the projectile again, at least within certain limits. In particular, the projectile can be brought to a shortened target trajectory or can be held there. The steering can take place, for example, on the basis of the position of the projectile, the position of a target, on the basis of control signals received, etc. The floor can thus be guided to a destination in a particularly precise location.

While the invention itself uses only the ballistics or gravity of the projectile to shorten the trajectory based on the braking of the projectile, the steering module uses active or aerodynamic steering mechanisms such as. B. adjustable steering wing, thruster or the like. The braking therefore causes in particular the determination of the basic trajectory of the projectile or the definition on a large scale, the steering module, on the other hand, serves rather a fine correction around the uncorrected trajectory or in the vicinity.

In a preferred variant of this embodiment, the steering module therefore contains a route guidance module for guiding the projectile to a predefinable destination. The route guidance module is oriented, for example, to a target marking applied to a target object at the target location, to target coordinates, etc. In particular, the steering module regulates the projectile to a desired shortened trajectory. With the route guidance module, the above-mentioned precise route guidance of the storey can be realized in particular.

In a preferred embodiment, the control device contains a sensor module. Any sensor technology for obtaining sensor data, e.g. B. position, direction, speed sensors, etc. Target search sensors such as. B. laser, radar, camera sensors, etc. sensors in the form of communication receivers or transmitters for communicating the projectile with a control center or the like are also conceivable. Properties of any complexity can thus be assigned to the projectile, in particular, for example, to improve route guidance, prevent self-bombardment, establish security mechanisms, etc.

In a preferred variant of this embodiment, the sensor module therefore contains a position module for determining a current position of the projectile, at least during its flight. Thus, the current position, speed, direction, location, etc., which is useful for route guidance, is known, i.e. the position of the floor in the floor itself, and can be processed there directly and quickly.

The object of the invention is also achieved by a projectile according to claim 13. The projectile has already been mentioned above and contains the control device according to the invention and the base body mentioned in connection with this. The control device is assembled with the base body to form a floor.

The projectile and at least part of its embodiments and the respective advantages have already been explained in connection with the control device according to the invention.

The projectile is in particular an armor-piercing projectile or part of an armor-piercing ammunition or tank ammunition. The projectile is in particular a 120mm smooth-tube projectile or a 155mm steering projectile. The projectile contains in particular a shaped charge and / or a P charge (projectile-forming charge).

The object of the invention is also achieved by ammunition with the projectile and the above-mentioned propellant charge. The same advantages and embodiments result for the ammunition as have already been mentioned above for the projectile.

The object of the invention is also achieved by a method according to claim 14 for operating a projectile according to the invention. In the process, the projectile is fired from a weapon. Then at least one of the braking elements is brought into the braking state during the flight.

The method and at least some of its embodiments and the respective advantages have already been explained in connection with the projectile according to the invention or the control device.

The object of the invention is also achieved by a method according to claim 15 for combating a target object at a target location with the aid of the method according to the invention. The projectile is first fired from the weapon onto a regular trajectory. In this case, an elevation of the weapon is selected which is increased with respect to an elevation for a direct trajectory of the projectile aimed at the target object. The direct flight path is the one that would fly through a conventional projectile or the projectile according to the invention if it remained completely in the idle state. This can be an imaginary trajectory if, for example, there is actually a cover or an obstacle in this direct trajectory and the target object cannot therefore be bombarded conventionally on the direct trajectory. In fact, the projectile is fired on a regular trajectory elevated to the direct trajectory. In particular, the destination would not be hit at the target object along the regular trajectory. The regular trajectory is the one that would go through the projectile if the hibernation were maintained.

The projectile or at least one of the braking elements is then brought into the braking state during the flight, in particular at such a point in time after the launch, that the braking projectile is decelerated by braking from its regular trajectory, which it would continue to fly in the idle state , is deflected ballistically or by gravity downward to a target location at the target object. The projectile therefore describes an overall shortened trajectory that deviates from the regular trajectory. The target location at the target object is in particular one that could not be reached by direct shelling with the projectile in the direct trajectory.

In other words, the projectile is first "shot over the target", i.e. H. on a currently higher regular trajectory, which is higher than the direct trajectory (which leads to the target in the case of direct shelling on an imaginary trajectory). By activating at least one of the braking elements when the braking criterion is reached, in particular at a specific point in time (the criterion or the calculation results, for example, from the target coordinates of the target location and the ballistic properties of the projectile in a manner customary in the art), the target becomes compared to Direct bombardment hit more from above. A direct fire on the direct trajectory, on the other hand, would lower the target; H. rather hit sideways.

The idea of the invention is that z. B. a battle tank is heavily armored in its front section, but is weaker armored on the top. An increased firing angle and a trajectory that is heavily curved (shortened) due to braking helps to hit the target from above. Coverages and obstacles that would prevent an actual direct fire can also be overcome in this way.

• 1 ein Drall-stabilisiertes Geschoss mit Bremsklappen im a) Ruhezustand und b) Bremszustand,
• 2 entsprechend 1 ein Flügel-stabilisiertes Geschoss im a) Ruhezustand und b) Bremszustand,
• 3 ein Geschoss mit Treibsatz im a) Ruhezustand und b) Bremszustand,
• 4 den Beschuss eines Zielobjekts mit einem Geschoss,
• 5 das Zielobjekt aus 4 im Detail.

Further features, effects and advantages of the invention result from the following description of a preferred exemplary embodiment of the invention and the attached figures. Show, each in a schematic sketch:

• 1 a spin-stabilized projectile with brake flaps in a) idle state and b) braking state,
• 2nd corresponding 1 a wing-stabilized projectile in a) idle state and b) braking state,
• 3rd one projectile with propellant in a) idle state and b) braking state,
• 4th firing a bullet at a target,
• 5 the target object 4th in detail.

1 shows a spin-stabilized projectile 2nd which is a basic body 4th and a control device 6 contains. Basic body 4th and control device 6 are on the floor 2nd assembled. The projectile 2nd is from an in 4th indicated gun barrel 8th can be fired by means of a propellant charge, not shown. The projectile 2nd shows an intended direction of flight 10th (indicated by an arrow) in which it moves after being shot down.

The control device 6 contains two brake elements 12 . In 1a are the brake elements 12 in an idle state R . 1 shows the time t = 0 when the projectile was fired 2nd . In this idle state R causes the braking element during a subsequent flight of the projectile 2nd initially no braking force F for the floor 2nd against the direction of flight 10th .

1b shows the braking elements 12 in a braking state B at a time t = t0> 0. Now they have a (larger than in the idle state R ) Braking force F for the projectile that is still in flight 2nd against the direction of flight 10th on. The projectile 2nd is now slowed down in flight.

The control device 6 contains an activation module that is only symbolically indicated here 14 that is used to move the brake elements 12 from hibernation R in the braking state B serves. The shipment takes place after the projectile has been fired and a braking criterion has been met K .

The braking criterion K here is the sequence of the specified flight duration t0 after firing the bullet 2nd . At time t = t0, the braking elements are activated 12 from hibernation R in the braking state B brought.

The braking element 12 is a passive, namely aerodynamic, braking element whose aerodynamic effect here is from a zero effect in 1a to an actual braking force F in 1b is changeable or is changed.

To get out of sleep R in the braking state B to get there is the braking element 12 relative to the body 4th movable, here it is about a swivel axis 16 towards the in 1a shown arrows pivotable. In the example are the braking elements 12 Airbrakes.

The activation module 14 is set up or programmed so that the brake flaps after the programmed time or duration or flight duration t0 open after launch, that is, from hibernation R in the braking state B move and so the air resistance of the projectile 2nd increase significantly.

2nd shows an alternative floor 2nd that differs from that 1 only differs in that it is not spin-stabilized, but by wings 18th Wing stabilized. Otherwise, the same statements apply as for 1 .

3rd shows an alternative floor 2nd that differs from that 2nd only differs in that it is an alternative braking element 12 contains. The braking element 12 here is an active brake element that has an activatable recoil device instead of the brake flaps 20th contains. The recoil device 20th serves to generate a recoil force or braking force F against the direction of flight 10th . For this purpose, the recoil device contains 20th two outlet channels 22 for a recoil 24th , here exhaust gas from a propellant 26 , here a rocket propellant. The outlet channels 22 run along a respective outlet direction 28 , here a respective central longitudinal axis of the outlet channels 22 in the form of a straight line. The outlet direction 28 each has a directional component in the direction of flight 10th on.

At rest R according to 3a is the propellant 26 inactive or ignited. When transitioning to braking B at time t = t0 this is activated or fired and continues to set the recoil 24th free to brake power F to unfold. This arises from the recoil from the outlet channels 22 in the respective outlet direction 28 is expelled. The activation module is also here 14 set up to have the propellant 26 after a programmed time t0 after the projectile was shot down 2nd ignites by the forward (in the direction of flight 10th ) directed outlets (outer ends of the outlet channels 22 ) a reverse thrust, ie the braking force F , which is used to brake the projectile 2nd leads.

3b shows further details of the control device 6 who have a steering module 30th to regulate the trajectory of the projectile 2nd after its launch contains. The steering module 30th includes a route guidance module 32 to guide the projectile 2nd to a given destination Z there.

The control device also contains 6 here one with the steering module 30th interconnected sensor module 34 . This contains a position module 36 to determine a current location of the floor 2nd at least during its flight after the launch as well as target search sensors not explained in detail.

4th shows an application scene for the projectile according to the invention 2nd . A weapon 38 , here a gun of a main battle tank, with the gun barrel 8th to fire the bullet 2nd is in a site 40 . A target object 44 , here an enemy battle tank, is in relation to the weapon 38 behind a cover 42 . The target object 44 is said to be using the bullet 2nd be fought. Because of the cover 42 is a conventional direct bombardment of the target 44 with a conventional projectile on a direct trajectory 46 not possible. The direct flight path is an elevation E0 of the gun barrel 8th assigned. The direct flight path 46 therefore corresponds to a conventional direct trajectory. The elevation E0 it would also make the floor 2nd on the direct flight path 46 bring.

The projectile 2nd however, is out of the gun 38 with an elevation E1 shot at time t = 0, the elevation E0 is increased. Would the bullet 2nd permanently at rest R would remain the regular trajectory 48 for the floor 2nd result that far behind the target object 44 leads. At the programmed time t = t0 during the flight of the projectile 2nd on the regular trajectory 48 however, the braking condition B on the floor 2nd activated, as shown by the 1 to 3rd was explained. The braking elements 12 are therefore in the braking state at time t = t0 B brought. This leads to a shortened, steeply falling trajectory due to the braking of the projectile 50 so that the target object 44 about the cover 42 away at the destination Z from the floor 2nd is hit.

5 shows V in detail 4th the target object 44 out 4th in detail. The projectile 2nd is only symbolically indicated here. Here, however, a shaped charge is shown to combat the target object 44 that on the floor 2nd is included. Would the bullet 2nd on the direct flight path 46 conventional from the floor 2nd or a conventional bullet, the bullet would hit the heavily armored front section 52 of the main battle tank. According to the invention, however, the shortened trajectory results 50 so that the floor 2nd actually to the destination Z on the top 54 of the target object 44 hits. The invention thus brings about the effect of the projectile 2nd from above on the weak or compared to the front section 52 weaker armored top 54 of the target object 44 . The destination Z could be on the direct trajectory 46 cannot be reached from one floor.

Reference symbol list

2nd

bullet

4th

Basic body

6

Control device

8th

Gun barrel

10th

Flight direction

12

Braking element

14

Activation module

16

Swivel axis

18th

wing

20th

Recoil device

22

Exhaust duct

24th

Recoil

26

Propellant charge

28

Outlet direction

30th

Steering module

32

Route guidance module

34

Sensor module

36

Location module

38

weapon

40

terrain

42

cover

44

Target object

46

Direct trajectory

48

Trajectory (regular)

50

Trajectory (shortened)

52

Front section

54

Top

R

Hibernation

B

Braking condition

K

Braking criterion

F

Braking force

Z

Destination

E0.1

elevation

t

time

t0

Flight duration

Claims (15)

Control device (6) which can be assembled with a base body (4) to form a projectile (2) which can be fired from a gun barrel (8) by means of a propellant charge, the projectile (2) having an intended flight direction (10), - With at least one braking element (12) which during a flight of the projectile (2) in a rest state (R) has a smaller and in a braking state (B) a larger braking force (F) for the projectile (2) against the direction of flight (10 ) having, - With an activation module (14) for moving the braking element (12) after firing from the idle state (R) into the braking state (B) when a braking criterion (K) is met. Control device (6) after Claim 1 , characterized in that the braking element (12) is a passively acting braking element (12) with a variable aerodynamic effect. Control device (6) after Claim 2 , characterized in that the braking element (12) is movable relative to the base body (4). Control device (6) according to one of the preceding claims, characterized in that the braking element (12) is an actively acting braking element (12). Control device (6) after Claim 4 , characterized in that the braking element (12) contains an activatable recoil device (20) for generating a recoil force against the flight direction (10). Control device (6) after Claim 5 , characterized in that the recoil device (20) contains at least one outlet channel (22) for a recoil means (24) along an outlet direction (28), the outlet direction (28) has at least one directional component in the flight direction (10). Control device (6) according to one of the Claims 5 to 6 , characterized in that the recoil device (20) contains an activatable propellant charge (26) for generating and / or releasing the recoil means (24). Control device (6) according to one of the preceding claims, characterized in that the braking criterion (K) is an expiry of a predefinable flight duration (t0) after the projectile (2) has been fired. Control device (6) according to one of the preceding claims, characterized in that the control device (6) contains a steering module (30) for controlling and / or regulating the trajectory of the projectile (2). Control device (6) after Claim 9 , characterized in that the steering module (30) contains a route guidance module (32) for guiding the projectile (2) to a predeterminable destination (Z). Control device (6) according to one of the preceding claims, characterized in that the control device (6) contains a sensor module (34). Control device (6) after Claim 11 , characterized in that the sensor module (34) contains a position module (36) for determining a current location of the projectile (2) at least during its flight. Projectile (2), with a base body (4), and with a control device (6) according to one of the preceding claims, which is assembled with the base body (4) to form the storey (2). Method for operating a projectile (2) according to Claim 13 , in which - the projectile (2) is fired from a weapon (38), - at least one of the braking elements (12) is brought into the braking state (B) during the flight. Method for combating a target object (44) at a target location (Z) with the aid of a method according to Claim 14 , in which - the projectile (2) is fired from the weapon (38) with an elevation (E1) onto a regular trajectory (48) which, with respect to an elevation (E0), for a direct trajectory (46) aimed at the target object (44) ) of the projectile (2) is increased in the idle state (R), - at least one of the braking elements (12) is brought into the braking state (B) during the flight in such a way that the projectile (2) is decelerated from its regular trajectory (48 ) is deflected downward towards a destination (Z) along a shortened trajectory (50).

Images