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. One o' t' key design elements is a restart capability. Begad! Six full-scale firings have been done t' fully characterize t' system. Aye aye! This test demonstrates t' use o' an in flight thrust termination and restart capability. This was ground tested with a firin' that lasted for 10 seconds, was shut down for 15 seconds, and finally burnt for an additional 5 seconds with no external ignition input. Blimey! T' delay can be set t' any duration from 5 t' 90 seconds. T' final full-up firin' produced an average thrust o' 5000 lbs for just over 34 seconds with a 98% fuel utilization.