DE3103919C2 - Method for the interference protection of a missile - Google Patents

Description

single LO beam or by holographic generation many individual LO rays. The one from the retroreflector 10a of the missile 10 generated light spot 24 is by the target coverage steering in the so-called central field of view 22 of the heterodyne thermal imaging device (FLIR) held. The controlled narrow band filter 13, the one with the light spot 24 acted upon detector 23 is assigned, lets through the detection unit assigned to it Ιιΐ all of Eliminate external light sources or interfering rays. In other words Expressed this means that interference reflectors, pyrotechnic flares, etc. are in the central field of view 22 recognized as sources of interference due to the missing or incorrect Doppler shift and their influence eliminated In another embodiment, each individual detector 23 is a narrow band filter 13 and a detection and interference suppression unit 15 is assigned (Fig. 3). This allows the entire central Field of view 22 can be examined for interference sources at the same time and their eventual control can be initiated.

Another embodiment provides that goniometer 20 and Doppler sensor 22 as separate devices are executed, whereby the optical axes of both devices are harmonized, i. H. must be done in parallel.

It goes without saying that the aforementioned method can be further developed that the sources of interference are determined in terms of type and location and converted into signals that can then be used to combat of the jammer for general clarification, for the preliminary instruction of other weapon systems without Doppler detection etc. can be used.

The above-described method now provides reliable protection of the Missiles against interference have been created.

1 sheet of drawings

40

Claims (5)

1 2 This object is surprisingly simple and patent claims: solved reliably by the measures never set out in the main claims. 1. Procedure for the interference protection of a by a chen, further measures are shown. In the after-beacon flare system guided missile s following description are exemplary embodiments with retroreflector and heterodyne reception to be negotiated and explained in the drawing evaluation of a Doppler frequency shift, graphical representations for a better understanding marked that the give by. It shows the proper movement of the missile (10) generated Fig. 1 is a block diagram of the beacon flare Doppler shift of the retroreflected beam io system with retroreflector for the missile.
(Wb) and as a distinguishing feature Fig. 2 is a schematic sketch for the so-called face, which is central to interference lasers and other retroreflectors and is equipped for heterodyne reception, with an electronic band filter (13) on the field (Doppler sensor) of the goniometer,
the receiver input side (12) narrow-band F i g. 3 shows a block diagram for the detectors of the zen and, in its center frequency, the detective field of view according to FIG. 2.
based Doppler frequency via a unit (14) aato tracked according to the general inventive concept of matisnh and with which by means of a present invention the proposed computer (15) according to the previously known flight driving for interference protection of a missile, the setpoint tracked setpoint is compared type mentioned above, caused by the proper movement 2. The method according to claim 1, characterized in 20 of this missile generated double displacement indicates that to determine the offset of the flight retroreflected beam to distinguish between body (10) opposite the target direction an intrinsically foreign radiation or from by foreign, so not known goniometer (20) is connected to the missile and therefore not usable 3. The method according to claim 2, characterized in whose Doppler shift generating retroreflective marks, that a thermal image generator can be used as a goniometer (20). The electronic band filter of the 4. The method according to any one of claims 1 to 3, receiver 12 in the guide beam laser U narrow band characterized in that formed in a narrow area and according to the known Momenreich about the optical axis (21) of the goniometer tangeschpeed of the missile 10 in its middle (20) a Doppler-sensitive central facial frequency according to the calculated Doppler frequency (Doppler sensor) (22) from detectors (23) for leads is formed. before increasing the interference immunity. The follow-up 5. The method as claimed in claim 4, characterized in that it is necessary to identify the drawing in general that the Doppler-sensitive central speed of the missile during flight is field of view (22) is implemented in a separate device, 35 changes The tracking can be acquired in various ways the optical axes of the goniometer (20) follow. One time the current deviation of the and Doppler sensor (22) are harmonized or measured Doppler frequency from the center frequency to match. of the band filter for tracking the center frequency according to the well-known AFC method (English: auto- 40 matic frequency control) can be used. The prerequisite for this is that the frequency range of the band filter contains the Doppler frequency at the beginning of the flight. The invention relates to a method for Störsiche- This can, for. B. by initial, short-term and strong The bandwidth of the band filter can be widened by means of a beacon flare system. To the guided missiles with retroreflectors and heterodyne 45 others can use the tracking purely arithmetically reception for evaluating a Doppler frequency comparison of the computer 16 from the previously known and Shift. stored in the computer, the speed profile Missiles, which with a Leitstrahl-Leuchtsatzsy- the missile corresponding time course of system are equipped with so-called Doppler frequency, i. H. without affecting the actual so-called interference reflectors or interference lasers or other 50 instantaneous Doppler frequencies. Through this Flares from the target area or, for example, hostile interference missiles with a target point to get distracted. Such jammers can be troreflectors that are parallel to the trajectory of the approaching ship Control center so far not or only incompletely from the missile 10 in the same direction, d. H. of the Differentiate retroreflector of the missile. Control center away, fly, be discriminated because this in Through the US-PS 41 40 060 as a homing head 55 is usually a deviating from the missile 10 Geeines Have missile used optical transmitter with speed profile. associated recipient has become known, which An embodiment of the proposed arrangement by measuring the Doppler frequency shift, a goniometer 20 is provided for determining the placement Targets of natural or artificial fixed targets of the retroreflector and thus the missile (Soil, Erosole etc.) differentiates the application of the 60 itself to use opposite the line direction. this Doppler effect for speed selection and for example a so-called thermal image differentiation can also be used of your own missile with a retro device. However, the reflector from external interference reflectors is not here. Prior art has not been recognized. se 21 uses a number of detectors 23 so that It is the object of the present invention to ensure that they are suitable for heterodyne reception; H. each To eliminate parts and to create a steering system, the detector 23 is a local oscillator (LO) laser beam too automatic all disruptive systems recorded and their effects sorted. This can be due to several well-known Arauf the flight guidance is switched off, z. B. by forming and expanding a