DE1578089B1 - Warhead for a rocket-propelled missile or a projectile for combating armored targets - Google Patents

Description

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The invention relates to a warhead for a rocket propelled missile or projectile to combat armored targets, the missile or the projectile in a predetermined Point of the trajectory through an aerodynamic braking means in a substantially vertical one Final trajectory is forced and its forward speed is significantly reduced.

According to German patent specification 15 78 077, a missile with an armor-piercing warhead aerodynamic braking means provided at the tail in order to influence the trajectory of the missile. Be there after covering a certain trajectory section at a predetermined point of the trajectory, the braking means in the form of expanding flaps, which slows down the speed of the missile, which Trajectory initially strongly curved and this then decelerated in a substantially vertical case transforms. The reason for influencing the flight path in this way lies in the fact that the effectiveness armor-piercing projectiles in the manner of projectile-generating shaped charges depends on the missile striking the ground as perpendicularly as possible, with consideration for the Triggering of the ignition mechanism does not exceed or exceed certain limits with regard to the impact speed may be undercut.

According to French patent specification 9 33 558 it is known that a missile, in particular for transportation of messages, e.g. B. Post, after a flight similar to a gyroplane on an im essential vertical end orbit completes its descent. To do this, before reaching the target area wings otherwise placed on the projectile body spread out, making the missile relatively slowly floats to earth. Such a device has the disadvantage that this reduces the impact speed of the missile on the ground drops below the amount required for the purpose mentioned above.

Another known way to shorten the trajectory of a projectile is like that French patent 4 96 913 shows in changing the outer bullet shape so that the Air resistance is increased significantly. But this changes the structural design of the storey complicated and expensive. In addition, it is not guaranteed that the projectile in a specific Location hits the ground.

Furthermore, the United States patent specification 30 88 403 shows a missile for fighting submarines, the after covering a certain distance of the ascending branch its parabolic trajectory is slowed down by ejecting a parachute at the stern. This causes the missile to go into a vertical final trajectory over. Here, the speed of fall should ensure undamaged immersion of the To ensure missiles in the water are significantly reduced; because the missile should be in Moving water to the depth of the submarine to be fought in a functional manner. These Possibility of influencing the flight path of a missile required by the high speed a large braking parachute, which in turn, due to the extreme loads that occur, in his Functionality is at risk.

The invention is based on the object of the previously known methods and measures for braking of missiles or projectiles in order to achieve the most perpendicular possible angle of incidence with a to improve sufficient impact speed.

The object is achieved according to the invention in that the missile or the projectile in one predetermined point of the trajectory by applying suitable means at the tip of the warhead is temporarily destabilized that the missile or projectile by reducing its Temporary speed to transition into the intended, approximately vertical final flight path at right angles to the flight path, whereupon the warhead, which has been restabilized by its guide means, with its Longitudinal axis is set back into the path tangent of the approximately vertical final flight path.

The invention takes advantage of the known physical phenomenon (such as from an AIA Α report from January 1969 it can be seen) that by some measure in a position directed transversely to the flight path forced elongated (rod-shaped) missile with simultaneous reduction in airspeed maintains its bank position, thereby self-stabilizing. A facility for obtaining the proposed

According to the invention, behavior of the missile or projectile during the target approach is that the Missile or projectile hood in several, as Bremsbzw. Spreading segments serving destabilization areas is divided, which are extended at the predetermined point of the flight path. This turns the missile across and remains in this transverse position, thereby stabilizing itself, until the almost vertical position The descent path is reached, whereupon the expansion elements are retracted again. Then comes again stabilizing effect of existing tail surfaces in appearance, which the missile back into the Forces original attitude in which its longitudinal axis coincides with the rail tangent.

Another device according to the invention is characterized by a in the front end of the Missile or projectile housed braking parachute, which in the predetermined orbit point by Dropping a fairing is deployed and temporarily or at the missile or projectile tip attacks until the end of the trajectory. This means that the parachute either after the missile has taken its bank angle, blasted off or otherwise eliminated, so that the missile through Presence of tail fin back to its original position with its longitudinal axis in the direction the path tangent is forced back, or that the missile by remaining of the braking parachute is turned by 180 ° so that it carries out the vertical descent to earth with its stern ahead.

In the context of the invention, a missile or projectile is addressed in which the triggering of Explosive charge by means of a detonator arranged on the rear of the projectile when it hits the rear of the projectile takes place on the floor actuating pressure member, the distance between the occupancy elements from The rear of the projectile corresponds to the distance of the upper target distance from the arc of the earth. This invention The feature results in a further advantage when the described second possibility is implemented -, second flight phase with the tail of the missile ahead - occurs when the Missile from a warhead with an adjoining motor housing, z. B. a rocket engine, is composed. The advantage is that due to the length of the motor housing, for. B. des burned-out rocket motor that touches the ground first in this inverted attitude, which is the Achievement of the optimal effect of the projectile when detonating the explosive device required ground clearance is adhered to. In this case, the detonator is actuated by a pressure pin, the starting from the ignition mechanism and penetrating the housing of the rocket motor in the longitudinal direction, the The tail of the missile protrudes and first touches the ground on impact of the projectile.

The invention is illustrated in the drawing on the basis of two exemplary embodiments described below shown schematically and in principle. It shows

F i g. 1 is a schematic representation of the invention Shooting trial,

F i g. 2 in a side view and partially in section a rocket projectile with retractable braking surfaces for carrying out the method according to the invention,

3 shows the side view of a rocket projectile of a different design during the de-stabilization,

4 shows the missile projectile according to FIG Final flight phase.

At point A of FIG. 1, a missile has started at the angle φ. He should reach the goal flying in the point. The trajectory determined, among other things, by the angle 9 runs in a parabola and would end at B if it were not interrupted at the previously determined point C due to the destabilization of the missile. For a short period of time, braking means set the missile axis at right angles to the path tangent and the missile rapidly loses altitude. If it has reached point D , the residual stabilization becomes effective and the few degrees of angle still missing at the 90 ° angle of fall are set after stabilization has taken place, so that the impact in target E is perpendicular to the earth's surface, the angle γ is 90 °.

The rocket projectile shown in Figure 2 consists essentially of a warhead 2, the projectile hood 1 is divided into several, serving as braking and destabilization surfaces, extendable expansion segments la to id , also of the rocket motor 4 and the stabilizing surfaces arranged on the surface of the motor 5. On the circumference of the warhead 2, in a thin shell 2a surrounding the explosive charge 3, in several planes of arrangement at right angles to the projectile axis - in the exemplary embodiment in five planes - conical occupancy elements 6 are arranged.

A separate initiation point is provided for each occupancy level, one of which is shown and denoted by 7. All initiation points 7 are ignited simultaneously via an ignition line 8 connecting them, as soon as an impact fuse, not shown in detail, but known per se, is actuated in the warhead by means of a telescopic rod 9 that can be extended at the tip of the projectile. The telescopic rod is set to such a length that the detonation of the explosive charge takes place at the height DH.

The trajectory AB is when using the projectile described above according to FIG. 2 at C by extending the expansion segments la to unfortunately projectile hood 1 as a result of destabilized transverse steepness of the projectile to the path tangent strongly curved, so that an angle of incidence of about 90 to 10 ° is already reached. In point D of FIG. 1, the further process step according to the invention takes place, namely the residual stabilization by retracting the expansion segments again, ie by restoring the aerodynamically shaped warhead hood 1. The stabilizing stabilizer wings 5 cause the projectile to realign itself and the last section of its trajectory with it Axis aligned perpendicular to the ground rushes through until it is ignited when the telescopic rod touches the ground and detonates at the optimum height.

In Figures 3 and 4 is a missile projectile shown, which is both destabilized and restabilized by extending the braking parachute 10.

At the start of the projectile, the structure of the rest of that of shown in Figure 2 to the arrangement of the drogue parachute in place of the expansion segments la to id is very similar, the projectile hood 1 through the panel 11 and 12 is formed from sheet metal. When point C of the trajectory is reached, the covering 11 and 12 are thrown off and the collapsed screen 10 attached to the anchoring rod 14 underneath by means of a line unfolds. It initially causes a strong reduction in the horizontal speed of the projectile and turns

this, since it attacks the bullet tip, in the direction of arrow ti so far that the bullet axis, which was previously in the path tangent, is perpendicular to this direction. After this de-stabilization, the trajectory of the projectile is strongly curved and runs approximately in the direction of arrow i. The immediate restabilization takes place in such a way that the projectile, hanging with the stern first on the screen, sinks to the ground with increasing speed. The floor axis is again coaxial to the path tangent and it hits perpendicular to the ground at E. whereby the ignition is triggered by pressing in the pressure member 13 located on the rear of the projectile and the explosive charge is detonated at the optimal distance from the ground D / Z.

Tests have shown that the missile after a few seconds of the braking and destabilization phase is stabilized again, only to fall, practically vertically, to the ground. When dimensioning the Parachute was to make sure that the missile

ίο only went into a slight circular oscillation, d. i.e. that the Circular oscillation had to be dampened.

For this purpose 2 sheets of drawings

Claims (4)

Patent claims: 1. Warhead for a rocket-propelled missile or a projectile for combating armored targets, the missile or projectile being forced into a substantially vertical final flight path at a predetermined point of the flight path by an aerodynamic braking center] and its forward speed is considerably reduced, characterized in that that the missile or the projectile is temporarily destabilized at the predetermined point (C) of the trajectory by deploying suitable means at the tip of the warhead, that the missile or the projectile by reducing its speed and transition to the intended, approximately perpendicular The final trajectory temporarily transversely to the trajectory, whereupon the warhead, which has been restabilized by its guide means (at trajectory point D), is set with its longitudinal axis back into the path tangent of the approximately vertical final trajectory. 2. warhead according to claim 1, characterized in that the missile or projectile hood (1) is divided into several, serving as braking or destabilization surfaces spreading segments (la to \ d) which are spread out at the predetermined point C. 3. Warhead according to claim 1, characterized by a braking parachute (10) housed in the front end of the missile or projectile, which is deployed at the predetermined trajectory point (C) by throwing off a covering (11, 12) and at the missile or projectile tip attacks temporarily or until the end of the trajectory. 4. warhead according to claim 1 and 3, characterized in that the triggering of the explosive charge by means of a mounted on the missile or projectile tail, the detonator when it hits the Hecks on the floor actuating pressure member (13) takes place.