DE2815206C2 - Procedure, guided missile and weapon system for combating ground targets - Google Patents

Description

17. Weapon system according to claim 16, characterized in that the ground TV camera and / or the front TV camera of the LFK can be pivoted about a transverse axis.

18. Weapon system according to claim 16 or 17, characterized in that the LFK with additional missiles for an additional thrust during the Dive and / or dive is equipped.

19. Weapon system according to claim 16, 17 or 18, characterized by a radio remote control device for controlling the LFK during the Nosedive.

20. Weapon system according to claim 16, 17 or 18, characterized by the following features:

a) A control device that approximates the LFK at the beginning of the dive in holds the ground target directed longitudinal axis position;

b) the bow TV camera is swiveled by radio command until an optical marker, e.g. B. a crosshair in the transmitted Image is brought into alignment with the ground target;

c) the target image or a section thereof is stored in a sensor;

d) an independent final phase target approach control, in which the LFK through the respective in their Zero control in the LFK swiveled back bow TV camera is readjusted.

21. Weapon system according to claim 16, 17, 19 and 20, characterized in that the LFK is equipped with brake rockets to slow down the dive is

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The invention relates to a method for combating ground targets by means of a guided missile (LFK), which describes a looping trajectory near the ground target, the apex of which is higher than the approach altitude to the target area and its descent path essentially perpendicular from above to the ground target directed, the trajectory of the LFK is controlled to the point of impact.

The invention also relates to a ventilated missile as well as a weapon system for carrying out this ω method. _

As ground targets, stationary or moving point targets come into consideration, in particular armored vehicles, guns, ships or the like.

The method explained at the beginning can be found in DE-AS 12 67 100. With this well-known The combat against ground targets is carried out from a carrier aircraft during a low-level procedure horizontal flight at high speed with dropping bodies which are designed as aerodynamically controllable glide bombs and which initially maintain the aircraft's direction of flight during the deployment process. After being released, the ejection bodies win by utilizing their own kinetic energy for the generation of aerodynamic lift force, an elevation above the flight altitude of the carrier aircraft and describe either a looping trajectory opposite to the flight direction of the in the previous flight altitude of the carrier aircraft flying further or! are another similar trajectory. Included the trajectory to the point of impact can either be determined by prior adjustment of the control elements of the dropping body or influenced arbitrarily by remote control from the carrier aircraft. These are TV cameras built into the missile so that the descent trajectory through a crew member of the Aircraft can be remotely steered to the target with the help of the television image transmitted to the aircraft.

This known method must therefore be carried out with a carrier aircraft, one of which aerodynamically controllable glide bomb is dropped. A major disadvantage of this process is to see that the ground target to be combated is inspected by flying over it must in order to be able to make the decision to trigger the glide bomb at all. But now it offers Carrier aircraft, because of its large radar silhouette and the strong infrared radiation of its engine, an easy-to-detect target that is in the Fly in the area of the defense fire of the air defense accompanying and protecting the ground targets must in order to be able to reach the goal with his glide bomb. So there is no risk involved in this process only the loss of the carrier aircraft but above all that of its flight crew.

In order to reduce this risk at least somewhat, the approaching method must be used in the previously known method Carrier aircraft fly very low. Laterally next to the immediate flight route, z. B. well camouflaged Tanks cannot be seen at all at such a low altitude because of the obstructions to the view. In the As a rule, therefore, the target to be fought must be flown over immediately. The decision to trigger the glide bomb and, if necessary, the subsequent control of the end phase of the looping movement will usually have to take place under the direct influence of the enemy, which is likely to affect the accuracy of the target.

Since the aerodynamically controllable glide bomb does not have its own drive, you can choose your solution only a very limited amount of energy from the carrier aircraft to execute the looping trajectory to disposal. The potential energy of the glide bomb is low at the moment of triggering because the Carrier aircraft is supposed to fly close to the ground. This results in only a very small difference in altitude »plane to Target". So while the potential energy of the glide bomb is practically negligible, it results their kinetic energy from the airspeed of the carrier aircraft at the moment of deployment. Since the The approach to the target is to take place horizontally, the result is the

kinetic energy from the maximum possible horizontal flight speed of the carrier aircraft loaded with bombs. The resulting kinetic Energy allows nu; very limited flight movements and maneuvers of the glide bomb. It is true with that known method also possible to move the dropping body in a side to the flight path of the carrier aircraft Guiding direction to steer when the carrier aircraft hits the target sideways and not directly skimmed. Because of the relatively low kinetic energy, the lateral distance must also be be kept low between carrier aircraft and ground target; so the carrier aircraft does not come out of that Air defense area out.

Since in the previously known method the projectile steering only during the descending part of the The trajectory of the glide bomb is possible, the detectable target area must necessarily be proportionate stay small. If the ground target to be attacked has already moved out of this target area, then the can Missing shot can also not be prevented by the steering of the missile. Aborting the target approach and a subsequent new target approach are excluded.

In all other comparable previously known methods, the missiles are on a ballistic Flight curve brought into the target area. Some of these procedures are detailed below:

DE-AS 15 78 089 is a rocket propelled Missile for combating armored targets has become known, which in a ballistic trajectory is shot. At a certain point on the parabolic trajectory, the missile is destabilized. For a short period of time, braking means make the missile axis perpendicular to the path tangent posed, with the missile rapidly losing altitude. By an effective after a certain period of time With residual stabilization, the missile arrives on a vertical fall curve, so that the impact hits the target takes place perpendicular to the earth's surface.

The US-PS 30 88 403 shows a missile for fighting submarines, which after covering a certain distance of the ascending branch of its parabolic trajectory by ejection a parachute is braked at the stern. This causes the missile to enter a vertical final flight path above. The speed of fall is to be reduced considerably in order to ensure undamaged immersion Ensure the missile in the water.

DE-AS 24 11 791 discloses a method for fighting ground targets by means of steerable projectiles. By means of an image recording device provided on the floor, one gains during the Approach to the target image information of the target area. This image information is used to launch and / or Fire control base transmitted, shown there as an image According to the observation of this image Control signals for the steerable projectile generated With this method, the projectile is converted into an indirect (im Ballistic trajectory leading to the target area shot down while image acquisition of the target area and the projectile guidance can be performed during the descending portion of the trajectory. Also at With this method, the projectile can be decelerated on the descending part of the trajectory. That Weapon system for carrying out this known method consists of a surface-bound Launching base with at least one steerable projectile and a device for transmitting signals between the launch base and the projectile in flight. The projectile is with one in the direction of flight directed image recording device provided. At the launch base there is a device for visual display the image information and a device for generating steering signals for the projectile on the basis of the Observation of the picture provided. The launch base has at least one directional launch guide

ίο Firing the projectile into a leading one near the target indirect ballistic trajectory.

With these known methods it is possible to use ground targets from a ground launch base to combat steerable missiles even when there is no direct line of sight to the target object Possible uses and the range of target engagement with guided ground / surface missiles are thereby improved. In the previously known method explained last, by setting up a Launcher on a suspected target area most of the ballistic trajectory without guidance given. The shooter only takes over the projectile guidance in the last part of the flight path, where a better target acquisition by the image recording device is already possible. The image capture device captures the target area steeply from above in this phase of the flight, so that it is suitable for the steerers provides a bird's eye view and recognition, selection and targeted control of individual targets is possible, which are very difficult or impossible to make out or close from each other when approaching a straight target from the front would be separate.

Common to all of these known methods is the ballistic trajectory leading into the target area and thus also the resulting disadvantages: The one on a ballistic trajectory into the target area missiles brought have a relatively high altitude and are therefore defensive to locate the enemy to be attacked at an early stage and, accordingly, to combat it at an early stage. Through the ballistic trajectory, the range is limited. Another disadvantage is that by only during of the descending part of the trajectory, the possible projectile guidance is proportionate to the detectable target area remains small; the target to be attacked has already moved out of this target area (e.g. a fast-moving one Combat vehicle), then the missile cannot be prevented by steering the missile will. A cancellation of the target approach and a

such subsequent new target approaches are excluded.

The invention is based on the object that

To improve the initially explained method so that Ground targets lying outside the range of vision of an operator without endangering an aircraft crew let fight.

This object is achieved according to the invention in that the LFK. be with its own marching engine Ground target over long distances in low flight flies over the immediate target area for stinging flight pulls up approximately perpendicularly and then on reaching one for the subsequent end phase reverses its direction of flight at a sufficient height and during the now following final-phase nosedive up to is precision-controlled for impact in the ground target.

it The guided missile can be operated from a ground-based, mobile launch device or be launched from a carrier aircraft. The new Procedure leads to numerous advantages:

The approach to the target area, which extends over a very large distance into enemy territory, takes place in horizontal low-altitude flight, at about treetop height, or in off-road flight. Because the guided missile (LFK) only a very small radar reflection surface as well as showing only a low level of heat radiation, this object is difficult to locate and track. Of the Approach will therefore mostly remain undetected. In addition, the high airspeed in the Can be of the order of magnitude of 1 mach or more, Air defense very difficult. But even if an LFK started to fight tanks before reaching the the targeted ground target is destroyed by the enemy or does not hit the ground target due to enemy action, the economic loss remains relatively small; in particular, there are no human losses. Since the launch pad for the LFK is a correspondingly large distance from the targeted ground target in protected standby position, the operating team working here is also protected from enemy action largely protected.

Because of the lower influence of the weather, flying low is associated with increased visibility and thus offers more favorable conditions for in comparison to high-approaching ballistic missiles the homing process.

Main battle tanks or comparable vehicles offer a greater attack from above according to the invention surface to be hit as from the side or from the front or back. This will increase the hit probability increased accordingly. In addition, the roof surfaces of such vehicles are essentially flat and lie horizontally so that they are at least approximated by a projectile approaching perpendicularly from above be hit vertically. The projectiles have their greatest penetration effect at this angle of impact. This proves to be all the more advantageous as the ceiling surfaces are by far the weakest armored Form places of armored car. The side and front wall surfaces of a combat or armored personnel carrier not only have a much stronger armor, but are largely inclined so that the guided missile launched according to the usual procedure not vertically, but under one more or less acute angles and thereby tend to slide off. When using the invention The method can thus meet the requirements for the effectiveness of the warhead of the guided missile be reduced accordingly, which is particularly in the training of the warhead as Balancing projectile is advantageous. Conversely, the increased effectiveness of the warhead can also be used for the foreseeable future will ensure that combat vehicles with modern, largely puncture-proof Armor can be successfully combated, as it is not possible for several reasons the large ceiling areas of the combat vehicle with one of the side and front armor comparable To provide armor.

Thanks to the large range that can be achieved with the new process, tank formations are already way ahead their entry into the direct battle distance of the battlefield, i.e. already on the approach or in theirs Combat deployments. Since tank units are mostly in forests, settlements or the like and thus against Camouflaged enemy lines can be set up in readiness, so camouflaged tank formations can be carried through horizontally Do not fight anti-tank systems at all, because on the one hand the necessary direct view is blocked on the ground targets, and because on the other hand a horizontally stretched approaching missile of Buildings, the terrain, forest or the like would be held up or distracted in an uncontrolled manner. Here is one of the great advantages of the method according to the invention, since here both the target search and the fight against above.

The speed during the stinging flight can be at least as great as, but preferably greater than during the low flight. The speed during the dive should be when using of a bullet as a warhead can be much greater than the speed during the Low-level flight, but when using a shaped charge as a warhead, it can only be as large as that Speed while flying low.

Advantageously, the LFK should turn one rotation at the latest when the stinging flight is initiated its longitudinal axis exclusive position are held.

The approach to the immediate target area can take place automatically. Immediately after the start goes then the LFK over to the entered flight altitude and target approach direction and thus steers itself automatically into the target area. The initiation of the stinging flight can also take place automatically via a target identifier. In the end the maximum height of climb can also be preprogrammed in the stinging flight. Takes place in an advantageous manner the reversal of the flight direction to initiate the dive through a rollover against the horizontal approach, ie by a "flip backwards". In a dive, target recognition occurs, if necessary Friend-foe detection as well as autonomous precision target approach guidance with per se known Facilities.

The method according to the invention explained above is what is known as “fire and” forget «procedure.

However, within the scope of the invention it is also possible to influence the course of the LFK during low-level flight to be carried out by radio from a staffed control center. Also the initiation of the automatic Stinging and diving can be done by radio from the control center. Deviations from the LFK Process coordinates entered for the target flight can then be corrected. Likewise after Sudden changes in the target area occurring at the start of the LFK are taken into account. But it is It is also possible to control the final phase of the dive via radio from a staffed control center.

Is the observer in the control section not clear about a ground target to be attacked, or else? he could give the radio command to initiate the stinging flight do not give in time, it can be useful if a program control can be activated via radio from a staffed control center that controls the LFK before initiating the stinging flight turns 180 ° so that the LFK is twice the turning radius distance from the previously flown approach line and fly back parallel to it and then turn around after another turn 180 ° again in the direction of and roughly in the track of the to fly into the target area for the first time.

It can also be advantageous if a staffed control center uses radio to send another Program control can be switched on to allow the LFK to fly low into the target area in the horizontal plane

at an angle to the first approach direction. Such a repeated approach can Observers from different directions in low flight continue to carry out until he finds the most favorable approach direction to identify the ground target and the actual attack.

A guided missile with a cruise engine, an airframe, a warhead, and guided and Search devices for carrying out the method according to the invention, as far as the entire flight of the LFK up to takes place automatically into the target by the LFK, is characterized according to the invention by the following features:

a) An attitude control that steers the LFK into the preprogrammed flight altitude and direction, holds on this course and in a normal flight attitude around the longitudinal, vertical and transverse axes stabilized;

b) a homing device in the form of a ground sensor, which is approximately parallel to the vertical axis is directed downwards and when the ground target is detected in its detection cone a signal by which the flight attitude control of the aerodynamic steering devices of the LFK is disconnected;

c) a program control that, after decoupling the flight attitude control, controls the LFK in the Stinging flight takes over until the nosedive position is reached and is then disconnected;

d) a target search and control system for the self-target-seeking final phase dive with a in the longitudinal axis of the LFK advance sensor device for target search, target selection and Target detection;

e) a regulation and control device, which the LFK after decoupling of the flight attitude control up to Holds impact in the ground target in a position excluding rotation about its longitudinal axis.

The attitude control can work in the manner of an inertial control. The program control pulls the LFK by turning it by about 90 ° around its transverse axis on a curve with the smallest possible radius approximately vertically upwards, prevents it from turning around the longitudinal axis of the LFK and maintains the stinging flight up to the programmed height above the target point. After reaching this height , the program steering steers the LFK by a backward rollover, i.e. by rotating 180 ° around its transverse axis, on a curve radius so that it flies approximately perpendicularly downwards in a general direction towards the ground target

To carry out the method according to the invention, in which the control of the LFK takes place partially or completely via an observer, one starts from a known weapon system, which consists of a launch base with at least one launch guide for an LFK, an LFK with a marching engine, an airframe, a warhead , Steering and search devices as well as an image recording device directed in the direction of flight (bow TV camera), a control center with a monitor to which the image information from the bow TV camera is transmitted, and a device for generating and transmitting steering signals for the LFK. According to the invention, this weapon system is characterized by the following features:

a) The launching guidance of the launching base starts the LFK in an approach leading to the target horizontal low altitude;

b) the LFK has a ground TV camera which scans the terrain overflown at low altitude and which Transmits image information to a monitor at the control center;

c) an attitude control overridden by the control center, which the LFK in the desired

ίο controls altitude and direction on this course holds and stabilizes in a normal flight position around the longitudinal, vertical and transverse axes;

d) a program control that can be switched on by the control center, which controls the LFK in the stinging flight up to Reaching the nosedive position takes over;

e) a regulating and control device that takes effect simultaneously with the program control and each Prevents the LFK from rotating around its longitudinal axis.

The overview that the observer receives of the area to be overflown by the LFK, as well as the Timely detection of ground targets can be improved by having the bow TV camera at the same time is used with the ground TV camera to display the terrain on the monitor (s). In Advantageously, the floor TV camera and / or the front TV camera of the LFK can be a The transverse axis can be pivoted, preferably by radio. It is useful during the low flight if the bow TV camera slightly around its horizontal transverse axis, which is parallel to the transverse axis of the missile their perpendicular to the missile longitudinal axis arrangement of the image is pivoted down so that it the ground image hurries ahead of the LFK.

The LFK can be equipped with additional missiles for an additional thrust during the stinging flight and / or the dive or be equipped with brake rockets to slow down the dive.

A radio remote control system can also be provided for controlling the LFK during the dive be. The recognition of the target after reaching the target area as well as the control of the LFK in Dive into the ground target can basically with known radar, laser, infrared or other electro-optical systems or with systems based on Schailentvicklung and / or magnetic Address properties of the target. The image recording device can be a normal optical TV camera, a low-light camera, an infrared or thermal imaging camera, or one on the Be a recording device based on laser technology.

All of these devices are not part of the invention.

The recognition of a target on the monitor can be facilitated by the observer an addition to the ground-TV camera provided and this little ahead hurrying working sensor at

Target recognition emits an announcement signal The final phase target control by radio can be from

the observer can only be carried out on the basis of the monitor image in the control center, for example with the help of a control stick on a work desk. In the In the zero position of the camera, the longitudinal axis of the LFK runs preferably through the intersection of the thread

65 cross of the camera. The observer directs over Funk the LFK in a nosedive so that the intersection of the crosshairs is now back with one of the LFK longitudinal axis arranged parallel to the image axis

The bow TV camera comes into line with the target point and holds this situation if necessary with further control commands upright until it hits the target. This also lets you move or suddenly change its direction Hit changing ground targets with a high probability.

The radio remote control device for the LFK enables steering around two axes that are perpendicular to each other and on the longitudinal axis of the LFK (transverse and vertical axis), parallel to which the axes of the wings of the LFK lie. When the camera is in the zero position, the crosshair lines in the image field of the bow TV camera are in the direction of the transverse and vertical axes.

A weapon system in which the LFK automatically steers itself into the target has the following according to the invention Features on:

a) A control device that approximates the LFK at the beginning of the dive into the Longitudinal axis position directed towards the ground;

b) the bow TV camera is swiveled by radio command until an optical marker, e.g. B. a crosshair is brought into line with the ground target in the transmitted image;

c) the target image or a section thereof is stored in a sensor;

d) an independent final phase target approach control, in which the LFK through the respective in their Zero control in the LFK swiveled back bow TV camera is readjusted.

Holding the LFK in an approximated longitudinal axis position directed into the bottom target can, for. B. by inertia control can be performed. The gimbal in the bow of the LFK is then attached to its TV camera swiveling vertically and transversely with its crosshairs in the field of view of the observer the control center by radio command via a remote control built into the LFK around these axes moved until your nosedive image transferred to the monitor coincides with the crosshair intersection and target point shows. The observer then again sends a radio command to the bow TV camera optically fixed on this target point, whereupon the radio contact between observer and LFK ends can be. The independent end-phase target approach control is now carried out in such a way that the is now effective becoming automatic control of the LFK the missile when automatically swiveling back the bow TV camera readjusts to its zero position in the LFK so that the crosshair intersection point and optically fixed target point is always exactly maintained. The LFK is self-directed in this way guided exactly to the target, without the observer's tutoring, even when the target point is off emigrates to its initial target location and / or its direction and speed during movement of the dive changes This end-phase target approach control allows an early termination of the Radio contact between observer and LFK and enables a lock in this critical approach phase for receiving disruptive radio commands or signals that could come from the enemy side.

Is the bow TV camera of the LFK rigidly installed or, if necessary, from one before the start of the dive? swiveled back position so that the image axis of the camera is parallel to the LFK longitudinal axis

"> is then the final phase control of the LFK can be carried out as follows: The observer closes At the beginning of the dive, the LFK based on the monitor image by means of remote control in the direction of the ground target that the crosshair of the camera with the

ίο the selected ground target is brought into line. A TV camera sensor device of the LFK is fixed on this target via radio command. That ends the Radio contact between observer and missile. To observe the impact, however, the Transmission of the monitor image continue. By the subsequent automatic electro-optical The automatic control system steers the LFK precisely to the ground target that is at the intersection of the crosshairs Bug TV camera had been "fixed". With this procedure, the LFK follows as a self-seeking, precision-controlled weapon every change in movement of the target point until it hits the target.

The procedure explained above can be modified as follows:

As soon as the crosshair intersection of the bow TV camera and the target point are in cover, the LFK in its longitudinal axis direction sent a laser beam to the target point. The target point is at least reflective some of the energy encountered. One in the LFK

^J0 built-in laser sensor receives part of this reflection and now steers the LFK into the laser-marked target. As soon as the laser control system starts, the remote control is switched off by the observer.

In the methods explained above, the observer sitting in the control center can use the TV cameras the LFK also conduct reconnaissance and the knowledge gained in this way in control consider subsequent missiles.

«Ο To achieve a high accuracy it is of of great importance, the LFK to the different weather and lighting conditions respectively to be able to customize. It is therefore advantageous if the sensor and target image acquisition and recording

«Measuring devices as easily exchangeable replacement units are built in. These facilities can then be passed through for immediately before the start of the LFK Replace more suitable devices depending on the situation.

The drawing schematically shows three examples of the trajectory according to the invention of a steering body shown.

A guided missile 1 flies at low altitude 2 into a target area marked by a tank 3. Above this target area, the missile 1 is pulled up approximately vertically for a dive 4 on a curve with the radius R. When it reaches a height sufficient for the subsequent final phase, the missile reverses its flight direction and then flies in an approximately perpendicular direction downward dive 5 at the ground target.

1 sheet of drawings

Claims (16)

Patent claims: 1. Procedure for combating ground targets by means of a guided missile (LFK), which is in the Describes a looping trajectory in the vicinity of the ground target, the apex of which is higher than the Approach altitude to the target area and its descent path essentially perpendicular from above to the ground target is directed, wherein the trajectory of the LFK is controlled to the point of impact, characterized in that the LFK with its own cruise engine its ground target over large distances approaches at low altitude, approximately perpendicular to is over the immediate target area for the stinging flight pulls up at the top and then its when it reaches a height sufficient for the subsequent end phase Direction of flight is reversed and during the end-phase nosedive that follows until impact is precision-controlled in the ground target. 2. The method according to claim 1, characterized in that the speed during the The stinging flight is at least as great as that during the low flight. 3. The method according to claim 1 or 2, characterized in 2; characterized that the speed during of the dive when using a bullet as a warhead is much larger than that Speed while flying low. 4. The method according to claim 1 or 2, characterized in that the speed during of the dive when using a shaped charge as a warhead is at most as high as the Speed while flying low. 5. The method according to any one of the preceding claims, characterized in that the LFK at the latest when the stinging flight is initiated in a rotation around its longitudinal axis that precludes it Position is held. 6. The method according to any one of the preceding claims, characterized in that the approach takes place automatically in the immediate target area 7. The method according to any one of the preceding claims, characterized in that the initiation of the stinging flight automatically via a target tion takes place 8. The method according to any one of the preceding claims, characterized in that the maximum climb altitude is preprogrammed in each case in the stinging flight. 9. The method according to any one of the preceding claims, characterized in that the reversal of the flight direction to initiate the dive occurs by a rollover against the horizontal approach 10. The method according to any one of claims 1 to 5, characterized in that during the low flight a course influencing of the LFK via radio from from a staffed control center 11. The method according to claim 10, characterized in that the initiation of the automatic Stinging and swooping takes place via radio from the control center. 12. The method according to claim 10 or 11, characterized marked that the final phase of the dive via radio from a staffed control center is controlled. 13. The method according to claim 10, 11 or 12, characterized in that a program control can be switched on from a staffed control center via radio, which the LFK before the initiation of LFK turns 180 ° so that the LFK is twice the turning radius of the previous one flown approach line and fly back parallel to it and then turn around after another turn To fly 180 ° again in the direction of and approximately in the lane of the first approach into the target area. 14. The method according to any one of claims 10 to 13, characterized in that a program control can be switched on by a staffed control center via radio, which the LFK the low flight in the The target area can be repeated horizontally at an angle to the first approach direction 15.Guided missiles with a cruise engine, an airframe, a warhead and guided and search devices for performing the method according to one of claims 1 to 9, characterized by the following features: a) an attitude control, which the LFK in the preprogrammed flight altitude and direction steers in, holds on this course and in a normal flight attitude around longitudinal, vertical and Stabilized transverse axis; b) a homing device in the form of a ground sensor, which is approximately parallel to the vertical axis is directed downwards and when detecting the ground target in its detection cone Emits signal through which the flight attitude control of the aerodynamic steering devices the LFK is disconnected; c) a program control that, after decoupling the flight attitude control, controls the LFK takes over in stinging flight until the nosedive position is reached and is then disconnected; d) a target search and control system for the self-target-seeking final-phase dive with one in the longitudinal axis of the LFK advance sensor device for target search, target section and target recognition; e) a regulation and control device, which the LFK after decoupling of the flight attitude control up for impact in the ground target in a rotation around its longitudinal axis excluding Holds position. 16. Weapon system for performing the method according to one of claims 10 to 14, consisting the end a launch base with at least one launch guide for an LFK, an LFK with a cruise engine, an airframe, a warhead, guidance and search equipment and one directed in the direction of flight Image capture device iBug TV camera), a control center with a monitor to which the image information from the bow TV camera is transmitted as well as a device for generating and transmitting steering signals for the LFK based on the observation of the monitor, characterized by the following features: a) The launching lead of the launching base starts the LFK in a leading one near the target, approximately horizontal low-level flight; b) the LFK has a floor TV camera that scans the terrain overflown at low altitude and displays the image information on a monitor the control center transmits; c) an attitude control overridden by the control center, which the LFK in the desired Altitude and direction steered, held on this course and turned in a normal attitude Longitudinal, vertical and transverse axes stabilized; d) A rogram steering that can be switched on by the control center, which controls the LFK in the Takes over diving flight until the nosedive position is reached; e) a regulation and control device that takes effect at the same time as the program control and prevents any rotation of the LFK about its longitudinal axis.