EP1211474B1 - Method for handing over a target to a missile - Google Patents

Description

The invention relates to a method according to the preamble of the claim.

Steering missiles are advantageously controlled by mobile launcher devices in order to make their location and destruction more difficult. In particular, in the anti-tank defense with the help of helicopter-guided missiles, it is possible to quickly change the position of the command post and launcher, which are identical in this case with the helicopter, either to improve their own shot position or be it to foreign influence to forestall or evade.

One of the most serious shortcomings of the current system PARS3 / LR is that the helicopter fired from the fire, despite mast sight for firing the anti-tank missile by leaving the cover must be exposed for a few seconds, so not only the shooter on the visor but also the ammunition through their seeker can see the target for briefing and targeting. Although the duration of this process is only a few seconds, the enemy can thereby locate the helicopter with simple modern reconnaissance tools. This means a significant risk to the helicopter and its crew.

A known solution to the problem is to bring the ammunition to the same height as the visor. This may be applicable to a land or sea vehicle by appropriate mounting of the launcher with ammunition. For mechanical reasons, it is completely unthinkable in a helicopter to mount the ammunition with the launcher at the visor height, ie above the helicopter rotor. Again, the starting missile forms a clearly visible optical signature, which increases the risk of locating accordingly.

From DE 41 32 233 A an anti-tank missile system for a combat vehicle is known in which by means of an elevierbaren mast arranged high-resolution camera, the target is detected, the target and flight data transmitted by optical fiber to the missile during the flight and the latter both from the navigation system of the Missile originating gyroscope as well as coming from a simpler camera located in the missile image signals via the optical fiber to the host computer or the steers in the vehicle zurückliefert so that the course can be corrected or the latter may cancel or modify the mission.

In this system, the missile must be in the vehicle throughout the mission via the fiber optic cable in conjunction with the master computer or sighting device. For the greater part of the route, the camera positioned on the mast must also be visually in line with the target, enabling it to be detected and for it to become the target of countermeasures.

DE 198 28 644 A discloses a system in which a missile which autonomously operates with the aid of its seeker head receives, directly or indirectly, additional information from an external reconnaissance system in order to increase the effectiveness of combat. This influence on the missile can extend from the start signal to the target approach phase. Although the starting device and the fire control is in cover; However, the helicopter carrying the reconnaissance system is all the more conspicuous.

In order to remedy the above problems in the system described above, it is proposed according to the invention that in the starting phase of the missile both command post and starting device remain in coverage and the missile by means of an inertial or optical fiber control of the starting device in one outside Cover lying, suitable for target detection Einweis-position is brought there detected with its own target search the target and then after separation of the start phase control the detected target approaches independently.

In fact, for the operational principle of the PARS3 / LR weapon system, it is not mandatory that the ammunition be connected to the helicopter during the referral process in which the alignment processor defines the target for the ammunition. It is rather important that the search head of the ammunition sees the target.

For example, from the program POLYPHEM a missile is known, which transmits the image information of the seeker in real time to the command state via a fiber optic. At the same time, this fiber serves for the trouble-free transmission of signals from the command post to the missile.

For a combat value increase, therefore, the missile for the launch phase is equipped with a corresponding data transmission via optical fiber according to the invention. The glass fiber only has to be so long that reliable instruction is possible during the first phase of flight. For the required period of one to two seconds, this results in a light guide length of about 500 m. The missile itself is expediently equipped with a reliable navigation system; He is thus steered approximately to the height of the sighting line. The requirements for the navigation are relatively low and can be supported if necessary still by image processing of the sighting image, as it is known from the system HOT.

Furthermore, the seeker must be sufficiently well aligned to start the briefing process. For this purpose, for example, good position gyros are used expediently.

The further course of the Zieleinweisung can run almost unchanged to the previous principle with the only difference that the ammunition is already on the way. During the initiation phase, the missile is still connected to the command post via the cable; this can be done interference-free data exchange in both directions.

Another advantage of the method according to the invention is that a shot runs much faster than before, since the start sequence of the missile engine can be done in parallel to the power-up of the seeker.

Furthermore, the parallax effect between the sighting axis and the line of sight of the seeker head to be injected is largely eliminated, which currently adversely affects the performance of the PARS3 system, especially at low altitudes of the helicopter.

Claims (1)

1. A method of relaying a target to a missile, wherein the target is identified by means of a sight, the missile is launched from a control station and directed towards the target and is then automatically guided to the target by a seeker head arranged in the missile, characterised in that

   - both the control station and the launching device remain completely in concealment during the launching phase of the missile,

   - in that the missile is brought by means of an inertial or fibre-optic guidance system of the launching device into a homing-in position lying out of concealment and suitable for target detection,

   - in that image data are transmitted in real time from the seeker head of the missile to the control station via the fibre-optic guide, and the image data from the seeker head and the image data from the launching device or sight are correlated and compared using an image processing method, and the target position and target size are automatically relayed to the seeker head,

   - in that the missile detects the target with its own target-seeking device and then automatically flies towards the detected target after disconnection of the launching-phase guidance system.