The Hyperion II is designed as a 12" diameter sounding rocket capable of lofting a 100lb payload to an altitude of over 100 miles for use as a research or atmospheric target rocket. The hybrid propulsion system is a combination of a metalized solid fuel and self-pressurizing nitrous oxide. One of the key design elements is a restart capability. Six full-scale firings have been done to fully characterize the system. One of these tests demonstarted the use of an in flight thrust termination and restart capability. This is the final full-up firing that produced an average thrust of 5000 lbs for just over 34 seconds with a 98% fuel utilization.