극초음속 비행체의 기준 동압 추종 유도 기법

Abstract

This paper proposes a guidance law for hypersonic vehicles to follow reference dynamic pressure profiles during the descent phase. In the proposed method, the reference dynamic pressure profile is modeled in the form of a third-order polynomial function, and the proposed guidance is performed in such a way that thehypersonic vehicle follows the predetermined dynamic pressure profile. In this study, we derive the equation of motion of dynamic pressure and reveal that the rate of change of dynamic pressure can be modeled as a function of flight path angle through analysis of this equation. The flight path angle guidance command that follows the reference dynamic pressure is then determined based on the feedback linearization technique, and the characteristics of the proposed guidance technique are examined. Finally, the performance of the proposed induction technique is analyzed through numerical simulation.