Midcourse Trajectory Optimization for Ducted Rocket Missiles Considering Field-of-view Constraints for Data Link

To ensure successful interception of highly maneuvering targets by long-range air-to-air missiles, continuous target tracking by the fighter-mounted radar and its transmission to the missile via a data link should be maintained during the mid-course guidance phase to compensate for variations in the predicted intercept point caused by target maneuvers. For this purpose, the missile and the target need to remain within the radar field of view of the launcher aircraft. However, the launching fighter typically executes a crank maneuver after missile release to enhance its survivability, which may cause the missile’s trajectory to exit the aircraft’s radar coverage. To address this issue, the present study formulates a three-dimensional trajectory optimization problem that explicitly accounts for the field-of-view constraints, particularly for missiles equipped with ducted-rocket propulsion systems. A sequential convex programming approach is proposed to solve the formulated problem, and the effects of the field-of-view constraint on the missile trajectories are analyzed under various engagement scenarios.