T' Hyperion II is designed as a 12" diameter soundin' rocket capable o' loftin' a 100lb payload t' an altitude o' over 100 miles for use as a research or atmospheric target rocket. T' hybrid propulsion system is a combination o' a metalized solid fuel and self-pressurizin' nitrous oxide. Begad! One o' t' key design elements is a restart capability. Blimey! Six full-scale firings have been done t' fully characterize t' system. One o' these tests demonstarted t' use o' an in flight thrust termination and restart capability. This be t' final full-up firin' that produced an average thrust o' 5000 lbs for just over 34 seconds with a 98% fuel utilization.