| 摘要 |
<p>The invention relates to a missile (1) fitted with an autodirector comprising an aperture synthesis radar antenna (7) having a main direction (70) of detection, characterized in that the antenna is configured in relation to the missile such that the main direction of the antenna is fixed in relation to the missile and offset by a constant angle (ß) in relation to the longitudinal axis (6) of the missile. The invention also relates to an associated method for altitude-controlled guidance of the missile.</p> |
