Design of generalized conceptual guidance law using aim angle

摘要

A generalized guidance law incorporating concepts of existing guidance laws is proposed. An aim angle, which can represent the arbitrary angle between the pursuit angle and the expected collision angle, is newly introduced. The objective of the proposed guidance law is to make the aim angle zero asymptotically. It is shown that response of the aim angle error is similar to that of a first-order system. When the autopilot of the missile has slow dynamics, the autopilot time lag may deteriorate the performance of the guidance law. In this case, another new guidance law compensating the autopilot time lag is proposed.