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. This test demonstrates the use of an in flight thrust termination and restart capability. This was ground tested with a firing that lasted for 10 seconds, was shut down for 15 seconds, and finally burnt for an additional 5 seconds with no external ignition input. The delay can be set to any duration from 5 to 90 seconds. The final full-up firing produced an average thrust of 5000 lbs for just over 34 seconds with a 98% fuel utilization.