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. Aye aye! One o' t' key design elements is a restart capability. Six full-scale firings have been done t' fully characterize t' system. This test demonstrates t' use o' an in flight thrust termination and restart capability. Avast! This was ground tested with a firin' that lasted for 10 seconds, was shut down for 15 seconds, me bucko, and finally burnt for an additional 5 seconds with no external ignition input. Begad! 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.