| 摘要 |
<p>PURPOSE:To track a target of a low altitude by reducing a side lobe gain of a reflected wave receiving antenna corresponding to an incident angle. CONSTITUTION:A speed vector, etc. of a mother aircraft are derived by execut ing an arithmetic processing 42 of each output of a rate gyro 38, an accelerome ter 39, an altimeter 40, and an alpha-beta meter 41 which have been loaded on the mother aircraft. Also, a distance and a direction of a target are derived by a radar range finder 43 and an antenna angle control system 44 of a target tracking antenna 10, and moreover, a distance and a direction of a missile are derived by a radar range finder 47 and an antenna angle control system 48 of a missile tracking antenna 46. Said each information is brought to opera tion processings 45, 49, 50 and 51 and an incident angle PSIM of a reflected wave receiving antenna 22 is derived. The value PSIM is transmitted to the missile by a transmitter 52 of the mother aircraft, and executes a control so that a side lobe gain of the antenna 22 is suppressed by an antenna envelope control mechanism 54. In this way, even a target of a low altitude can be tracked by varying adaptively an envelope of the antenna 22 so that a clutter power having a frequency transition of the vicinity of a Dopper frequency transition of the target is suppressed.</p> |
