| 摘要 |
In a method of guiding a missile in flight to a target, the location of the missile and the radar (e.g. synthetic aperture radar) range to the target are measured at a plurality of moments during the flight of the missile. The location of the target is calculated from the measured ranges and the measured missile locations. Doppler measurements give relative velocity and hence acceleration. The target location calibrates angular measurements in the seeker. A required velocity vector angle is calculated from the calculated location of the target and a guidance law. A lateral acceleration required to provide the missile with a velocity oriented to the target at the required velocity vector angle is calculated for the missile. The missile is caused to accelerate with the calculated lateral acceleration, so that the missile follows the target, e.g. in an equiangular spiral followed by a maximum acceleration when the acceleration required to maintain the missile on the spiral becomes too large. The radar may use a conformal array antenna. |
