Composite Guidance Scheme for Impact Angle Control Against a Nonmaneuvering Moving Target.

The article presents a proposed optimal impact angle control guidance law which lessens the time-to-go weighted energy cost function. It explores the development of a three-dimensional guidance laws that were based on proportional navigation (PN) having adaptive guidance parameters to obtain impact angle requirements. The impact angle control created the missile trajectory highly curved that might missed the target in the look-angle limit of the seeker.