| 摘要 |
An anti-radar missile control system which is required to impose a glide phase and a terminal phase on the missile flight. The glide phase produces a constant angle of look and is required to pass smoothly into the terminal phase which has a circular or near circular path descending vertically or near vertically on the target. This basic form is subject to substantial error resulting from the large angle of look that obtains for a considerable part of the terminal phase. The terminal phase could be improved, sharpening up the curve and reducing the dwell at high look angle, by increasing the navigation gain. This, however, tends to increase the instability significantly. The invention effectively simulates a high gain trajectory by adding a bias to the look angle so inducing the glide phase to remain operative longer. This in effect determines a larger intercept angle on impact. By removing the bias during the terminal phase the intercept angle is brought back to the vertical (or other predetermined value) and a sharper curve results so gaining the benefit of a high gain system without lessening the stability. |
