Cal Poly Space Systems conducted a successful full duration test fire of Hybrid Motor 7. The oxidizer pressure was too low, leading to decreased thrust at the end of the burn.
The design parameters of this engine are:
Thrust: 400 lbs
Burn time: 12 s
Fuel: Hydroxyl Terminated Polybutadiene (HTPB)
Oxidizer: Nitrous Oxide (N2O)
Check out the burn here.