DE3617487C1 - Warhead detonator for guided missile - compares radius vector valve with threshold signal as target is approached - Google Patents

Abstract

In a device for fitting the warhead of a guided missile, sensors register the target position, and an evaluator circuit generates on the sensor signals to produce a triggeer signal when the signals read a set value. During the flight of the missile, the value of the radius vector of the control command calculated in polar coordinates for the guidance device (LE) of the missile is compared to a threshold signal (S). Out of the sensor information regarding the angular position and/or the radial spacing between target and missile there is derived this threshold signal. When the radius vector (R) exceeds the threshold, the filing of the warhead (GK) of the missile, directable to the target is triggered when the operating direction of the head points to the target. ADVANTAGE - Uses steering electronics already present.

Description

The invention relates to a device for triggering the warhead a guided missile, which sensors for recording the target position and an evaluation circuit for has the sensor signals at which the reaching or exceeding a certain value of a sensor signal as a trigger criterion is used.

Steerable missiles of known type are with steering devices equipped by means of data transmission over a Wire, a light guide or over a radio link or one optical signal transmission to control the missile enable to the finish. There are several for the purpose of understanding the goal Types of sensors known. Usually they are Missiles equipped with warheads, their direction of action is identical to the direction of flight.

In DE-OS 24 45 488 a search head with active or passive Sensors described, the gimbal and which is connected to an ignition device that reaching or exceeding a certain value of a sensor signal used as trigger criterion. The missile contains in this case an active cargo oriented in the direction of flight.

DE-PS 14 53 815, on the other hand, describes an explosive charge projectile with a warhead, the direction of which is particularly effective for use against maneuverable flight targets also from the side  can be aligned to the direction of flight. However, it will no ignition circuit for high-precision triggering of the straightenable Warhead indicated.

Furthermore, from European patent application EP 01 61 962 a device for ignition of the radial to the main axis of the missile effective fragmentation charge known, in which the for the Trigger necessary delay time according to various measurable parameters, such as the airspeed of the Missile, the relative velocity between missiles and target and the direction of the vector of the relative speed is calculated. Apart from the fact that a radial around the Missile-directed active charge versus an alignable Active charge has a low efficiency, is in this document does not give any indication of how an optimal Triggering an alignable warhead at one Destination met both in the direction of flight and in the flyby can be.

The invention is therefore based on the object of a device for the highly precise triggering of an adjustable warhead a guided missile using sensor signals and to indicate existing means of steering electronics.

This task is accomplished by those set out in the main claim characteristic features of the device solved.

Further advantageous embodiments are in the characterizing Parts of the subclaims are described.

The particular advantages of the device according to the invention are to be seen in the fact that with simple means in the on-board system a guided missile in the form of circuits or signals already exist, an effect-optimized release  both in the case of direct hits as well as during a flyby can be achieved at the destination. Furthermore, due to use the missile control signals a high accuracy of target determination achieved. In addition, through the Specification of the rough target direction by the steering vector all others targets detected by the sensors are hidden. Eventually, due to the decreasing distance Missile / target matching rating threshold a higher Resolution near the target and also a higher immunity to interference Apparent targets and disruptive maneuvers.

An embodiment is shown in the drawing and is described in more detail below. It shows

Fig. 1 shows a typical situation encounter target / missile;

FIG. 2 shows the resulting values of the steering commands with respect to a threshold signal;

Fig. 3 is a block diagram of a device according to the invention.

Fig. 1 shows a typical situation encounter between a steerable missile FK and an elusive objective, at which the process described herein for the purpose of effectively optimized initiation of the warhead of the missile FK GK is applied. The initial situation is that the missile can no longer hit the target Z in the direct approach, be it that the target Z is a turning aircraft or in a tank in cover, which is detected by the sensors of the missile can only be discovered so late that a direct hit is no longer possible. In such a case, a directional warhead carried in the missile should be fired when the direction of action of the warhead is in target coverage at the point of the missile's trajectory closest to the target.

In FIG. 1, the current size of the steering vector LK ( ϕ , R) is also indicated for the missile FK , which are continuously calculated in the steering computer LE on the basis of the output signals of the sensors SE detecting the target Z.

Fig. 2 shows this, the steering vector LK (φ, R) in terms of magnitude R and angle φ according to the intended application in the example coordinate transformation into the polar coordinate system. The amount R of the steering vector LK ( ϕ , R) is compared in accordance with the method according to the invention with a direction-independent signal threshold, which can also be variable in size if necessary. If the amount R of the steering vector LK exceeds the threshold S , this means that the missile can no longer directly target the target. Therefore, the lateral angular deviation is used for triggering the warhead directable φ GK of the target relative to the aircraft from the steering computer LE together with the distance determined by the sensors SE Δ a missile used to target.

In FIG. 3, the means for triggering a directable warhead GK is shown in simplified. It contains a steering device LE in which the control signals of the guided missile FK are processed. The input variables in this steering device are, on the one hand, those from an external command point, such as, for. B. a launch system or a ground station, originating steering commands LK (ext.) And on the other hand the output signals LK (int.) Generated by the on-board sensors SE detecting the target position. Depending on the application, the output signals of the steering device LE are in a coordinate system that is unsuitable for further processing. They must then first be converted into a suitable coordinate system using a transformation circuit TR . In the exemplary embodiment, the steering commands are transmitted into the polar coordinate system, so that finally a steering vector LK ( ϕ , R) corresponding to the steering command is present according to amount R and angle of deposit ϕ .

The amount R of the steering vector LK ( ϕ , R) is then compared in a comparator K with a threshold signal S. This threshold signal S is originally obtained from the output signals SA of the sensors SE by these output signals SA, for example, various via a data bus BUS signal processing circuits SV 1, SV 2, SV are fed to 3, v for determining the relative position Δφ, Δ r and speed Δ of the missile FK serve against the target Z. The most critical value of the output signals Δϕ , Δ r , Δ v is used in the signal comparison circuit JS to generate a threshold signal S. At the same time, the relative distance Δ a of the missile FK in the flight direction to the target Z is determined in a further signal processing circuit SV 4 from the sensor signals SA . This size Δ A may, if necessary, the signal threshold S are used to change the value of, for example, in the manner that the threshold S after a certain regularity is getting smaller, the more the missile FK approaches the target Z.

In the comparator K , the amount R of the steering vector LK ( ϕ , R) is compared with the signal threshold S such that an output signal RS is emitted by the comparator K when the amount R exceeds the current signal threshold S. This output signal R < S serves to release the ignition of the ignition circuit ZS .

The actual ignition timing t is determined when the distance Δ a of the missile FK in the flight direction to the target Z has become approximately zero. The stipulation of the value Δ a ≈ 0 naturally depends on the maximum directional angle ϕ of the directional warhead GK relative to the direction of flight of the missile and must therefore be taken into account accordingly. This directional angle ϕ of the warhead GK is obtained from the steering device LE and fed to the ignition device of the warhead GK .

Claims (4)

1. Device for triggering the warhead of a steerable missile, which has sensors for detecting the target position and an evaluation circuit for the sensor signals, in which the reaching or exceeding of a certain value of a sensor signal is used as a trigger criterion, characterized in that during the target approach of the steerable Missile (FK) the values of the radius vector (R) of the control commands of the steering device (LE) of the missile (FK) calculated in polar coordinates are compared with a threshold signal (S) , which is based on the sensor information about the angular offset ( Δϕ ) and / or radial distance ( Δ v) between the target and the missile (FK) is obtained, and when the threshold (R < S) is exceeded the ignition of the warhead (GK) which can be aimed at the target is triggered when the direction of action (W) of the warhead (GK ) is aimed at the goal. 2. Device for triggering the warhead of a steerable missile according to claim 1, characterized in that the output signals of the sensors (SE) used in a known manner for guiding the missile (FK) to the three signal processing circuits (SV 1 , SV 2 , SV 3 ) Generation of differential signals ( Δϕ , Δ r , Δ v) are supplied, from the output signals of which an evaluating signal comparison circuit (JS) forms a threshold value (S) which, on the one hand, is related to the values of the radius vector (R) obtained from the missile's steering device (LE ) the control commands of the steering device (LE) calculated in polar coordinates are compared in a comparator (K) , which delivers a release signal to the ignition circuit (ZS) when the signal threshold (R < S) is exceeded, the ignition being triggered by the output signal ( Δ a ≈ 0 ) of the further signal processing circuit (SV 4 ), which is also controlled by the output signals of the sensors (SE) , can be triggered t. 3. Device for triggering the warhead of a steerable missile according to claim 1 or 2, characterized in that the height of the signal threshold (S) can be reduced in accordance with the distance missile / target. 4. Device for triggering the warhead of a steerable missile according to claim 1 to 3, characterized in that the value of the radial angle ( ϕ ) calculated by the steering device is used to determine the direction of action of the directed warhead.