  This paper proposes a feedback guidance law to move the instantaneous impact
point (IIP) of a rocket to a desired location. Analytic expressions relating
the time derivatives of an IIP with the external acceleration of the rocket are
introduced. A near time-optimal feedback-form guidance law to determine the
direction of the acceleration for guiding the IIP is developed using the
de-rivative expressions. The effectiveness of the proposed guidance law, in
comparison with the results of open-loop trajectory optimization, was
demonstrated through IIP pointing case studies.
