DE19806066B4 - Missile against reactive armor - Google Patents

Abstract

Supersonic missile (10) against reactive armor
with a tip (11, 12) oriented in the direction of flight for penetrating the reactive armor, preferably without activating it,
and with a shaped charge warhead (18) arranged behind it, the firing channel (19) of which is pivoted by an angle (β) to the longitudinal center axis (L) of the missile (10).

Description

The invention relates to a missile against reactive armor, especially a tank, encompassing passive armor first an explosive and then one or more scatter plates, with a shaped charge.

common missile for fighting of tanks with reactive armor have so-called warheads Tandem shaped charges, each comprising two shaped charges, from which the first shaped charge in the direction of flight has a hole in the reactive armor blows up a passage for those in Flight direction rear, second shaped charge through the reactive armor leaves so that the second shaped charge causes the passive armor to melt, i.e. the firing channel of the second shaped charge penetrates into the interior of the tank. Such tandem shaped charges need a relatively large one Storage space and have a high weight.

Furthermore, missiles for combating near-ground targets, such as helicopters, for example, are in the unpublished version DE 42 10 113 C1 described and from the DE 196 26 075 C1 known. These missiles comprise at least one engine or at least one engine for starting and driving or marching during an essentially vertical take-off, a deflection and - at least partially - a horizontal search phase, a seeker-based tail-wing-controlled steering device and a radiation-sensitive seeker head, in particular on IR Basis, for tracking down a target during the search phase and for target tracking as well as for guiding the missile after target acquisition in a target approach phase following the search phase, and enable a targeted attack.However, these missiles are not dimensioned in such a way that they are known tandem shaped charges for combating a a reactive armor equipped tank, especially due to the space and weight required by tandem shaped charges.

From the DE-OS 6 05 455 is a tandem projectile with a combination of two different modes of operation, namely that of a pure balancing projectile and that of a shaped charge. The balancing body can have a guide channel for a spike to be formed from the shaped charge and a hard material tip which is arranged in the front mouth region of the guide channel, the guide channel running along the longitudinal central axis of the projectile.

The DE 38 00 975 A1 discloses an armored projectile with a projectile head with a penetration effect and a shaped charge for forming a beam of a detonating shaped charge, the beam in turn running along the longitudinal central axis of the projectile.

From the DE 35 25 147 C1 is a cambered missile, the axis of which is oriented almost perpendicular at the point of impact.

The FR 1.002.092 discloses a projectile whose tip is essentially used for steering, while a balancing body is arranged behind the tip in the direction of flight. So that the balancing body can develop its effect at the point of impact, either the tip must be blown away or the balancing body accelerated out of the projectile.

Based on the known state of the art Technology is therefore an object of the present invention, a missile against reactive armor is available to provide a high with little space and weight effectiveness achieved.

This task is accomplished by a missile according to claim 1 solved. The requirements 2 to 5 relate to particularly advantageous embodiments of the missile according to the invention.

One embodiment of the invention is characterized in that the kinetic energy of the missile, especially the top, when hitting the reactive armor, is so adjustable that the Reactive armor penetrable without activating your explosives is.

It can be provided the angle between the longitudinal central axis of the missile and its horizontal line at the point of impact of the missile on the reactive armor dependent on on the angle between the longitudinal central axis of the missile and the firing channel of the shaped charge warhead is adjustable.

The invention also sees further developments before, which are characterized in that the tip is a heat-resistant, resistance-reducing in the supersonic area Anströmspitze is, which preferably with an outer shell supporting spars a tricorn connected to the remaining components of the missile forms.

It is preferred according to the invention that the missile is a seeking head supported rear wing controlled Steering device includes.

Finally, the invention also proposes that the Actuator including the rear wings between a start engine in the direction of flight and a tail March and exhaust motor is arranged.

The invention is therefore based on the knowledge that the effectiveness of a missile can be increased by providing a tip for penetrating reactive armor, which is oriented in the direction of flight of the missile, while a single shaped charge is provided in a shaped charge warhead, the firing channel of which is directed the direction of flight by an angle β is pivoted.

Thereby the kinetic energy the peak at the time of hitting the reactive armor sufficient to penetrate the reactive armor without triggering the Explosives of the reactive armor can be set.

Because of the configuration according to the invention of the missile with one for penetration of the reactive armor can be accelerated sufficiently and sufficiently heavy tip, which is aligned in the direction of flight is, and the provision of a shaped charge, the firing channel around an angle β to Optimal mode of action is ensured. Also opened the possibility for the first time that the Missile itself in the form of a with a seeker-based, rear wing-controlled Steering equipment missile is formed in which a seeker head between the reactive armor penetrating tip and the shaped charge floor is arranged.

Other features and advantages of Invention result from the following description, in which an embodiment is explained in detail with reference to schematic drawings. It shows:

1 a perspective view of a missile according to the invention on final approach to a tank;

2a a sectional view through a missile according to the invention; and

2 B a front view of the missile according to the invention, viewed from the direction of flight.

In a missile according to the invention 10 , especially to combat a tank equipped with a reactive armor, not shown 1 , as in 1 shown, is suitable, it is an aerodynamic, tail-controlled, wing-free to the rear wing IR supersonic missile with inertial forward steering phase, namely during a start phase, a redirection phase and a search phase, and autonomous target guidance in a target approach phase. So the missile can 10 after starting a search area for a target like the tank 1 , scan and after target acquisition on a course to the tank 1 shake gently. The typical orbit includes the launch phase in which the missile 10 in a relatively steep orbit to a search altitude, the search phase in which the missile 10 flies along a flat orbit and the search area is scanned for possible targets, and the final approach phase in which the tank 1 is detected and the missile 10 the captured tank 1 approaches and the in 1 is shown.

The missile 10 includes, viewed in the direction of flight from front to back and like that 2a and 2 B you can see a tricorn 11 , an IR seeker head 15 , a flight control unit 16 , an electrical power supply unit 17 , a shaped charge warhead 18 , a start engine 20 , an actuator 22 , Rear wing 23 . 23 ' , a marching and ejection engine 24 and a jet nozzle 25 , The tricorn 11 from an inflow tip 12 and an outer jacket 14 supporting support bars 13 . 13 ' . 13 '' educated. Between the start engine 20 and the actuator 22 are side jet nozzles 21 . 21 ' provided, in 2a the starting engine 20 and the actuator 22 by 45 ° around the longitudinal center axis L of the missile 10 are shown rotated so that the side jet nozzles 21 . 21 ' able to see.

The inflow tip 12 must be so heavy and at the time of hitting the armor's reactive armor 1 be quick that it has a kinetic energy that, under energy conversion, allows penetration of the reactive armor, preferably without deflection, so that the firing channel 19 of the shaped charge warhead 18 the passive armor of the tank 1 penetrate and thus into the interior of the tank 1 can penetrate. It is particularly advantageous if the firing channel 19 substantially perpendicular to the passive armor, which is achieved by adjusting the angle α between the longitudinal center axis L of the missile 10 and a horizontal H at the point of impact on the tank 1 , please refer 1 , depending on the angle β between the longitudinal center axis L of the missile 10 and the firing channel 19 , please refer 2a , is adjustable. The angle β is chosen such that consumption of the shaped charge of the shaped charge warhead 18 in the missile 10 is essentially avoided.

The in the description above, in the drawings and in the claims disclosed features of Invention can both individually and in any combination for the realization of the invention in its various embodiments.

1

tank

10

missile

11

tricorn

12

top

13 13 ', 13' '

support spar

14

outer sheath

15

IR seeker

16

Flight guide unit

17

electrical Power supply unit

18

Shaped charge warhead

19

ejection channel

20

start engine

21 21 '

Seitenstrahldüse

22

actuator

23 23 '

rear wing

24

March- and exhaust motor

27

jet

L

Longitudinal central axis

H

horizontal

α

angle

β

angle

Claims (5)

Supersonic missile ( 10 ) against reactive armor with a point oriented in the direction of flight ( 11 . 12 ) to penetrate the reactive armor, preferably without its activation, and with a shaped charge warhead arranged behind it ( 18 ) whose firing channel ( 19 ) at an angle (β) to the longitudinal center axis (L) of the missile ( 10 ) is pivoted. Missile according to claim 1, characterized in that an angle (α) between the longitudinal central axis (L) of the missile ( 10 ) and a horizontal (H) at the point of impact of the missile ( 10 ) on the reactive armor as a function of the angle (β) between the longitudinal center axis (L) of the missile and the firing channel ( 19 ) of the shaped charge warhead ( 18 ) is adjustable. Missile according to one of the preceding claims, characterized in that the tip ( 12 ) is a heat-resistant inflow tip that reduces drag in the supersonic area, preferably with an outer jacket ( 14 ) supporting supports ( 13 . 13 ' . 13 '' ) one with the remaining components of the missile ( 10 ) connected tricorne ( 11 ) forms. missile according to one of the preceding claims, characterized by a seeking head supported rear wing controlled Steering device. Missile according to one of the preceding claims, characterized in that an actuating unit ( 22 ) including the rear wings ( 23 . 23 ' ) between a start motor ( 20 ) in the direction of flight and a rear-facing march and exhaust motor ( 24 ) is arranged.