GUIDANCE LAW FOR FLIGHT VEHICLES WITH ATTITUDE CONSTRAINTS AT IMPACT.

For some special missions, a flight vehicle must possess certain properties as it draws near the target; for example, the missile may be required to close in on the target along a given direction in order to improve the percentage of hits. This kind of problem leads essentially to missile guidance with nonzero terminal attitude constraints, which is of practical significance for carrier rockets as well as for tactical missiles. Such a plane guidance problem is studied in this paper from the viewpoint of flight dynamics. The realization of the optimal control, the calculation of the miss, and effects of terminal constraints on the control are discussed. It is shown through a numerical example that the terminal nonzero constraints on missiles will increase the demand for control in varying degree according to manoeuver of the target.