| 摘要 |
<p>PURPOSE:To improve the guidance accuracy by reducing a side lobe gain of an antenna corresponding to an incident angle, and tracking a target of a low altitude. CONSTITUTION:A speed vector of a missile is derived by executing an arithmetic processing 31 of an angular velocity and an acceleration of the missile, which are obtained from a rate gyro 20 and an accelerometer 30 which are loaded on the missile. On the other hand, a distance and a direction of a target are known by a radar range finder 32 and an antenna angle control system 21. By bringing these information and speed vector to an arithmetic processing 33, a speed vector, etc. of the target are obtained, and furthermore, by executing an arithmetic processing 34, an incident angle PSIM to an antenna 3 of a radio wave is derived. A side lobe gain of the antenna 3 is suppressed by operating an antenna envelope control mechanism 35 in accordance with the angle PSIM. In this way, even the target of a low altitude can be tracked by varying adap tively an envelope of the antenna 3 so that a clutter power having a frequency transition of the vicinity of a Doppler frequency transition of the target is suppressed, and the guidance accuracy is improved remarkably.</p> |
