25lbf Battleship Motor
| Designation: | HRM-25-BM |
| Hot-fire Tests: | 10 |
| Testing Period: | 2004 - 2005 |
| Propellants: |
Oxidizer: 90% Hydrogen-Peroxide (liquid) Fuel: HTPB (solid) |
| Thrust - avg: | 25 lbf |
| Chamber Pressure - avg: | 440 psia |
| Burn Duration: | 7 seconds |
| Diameter-grain: | 1.29 inches |
| Length-grain: | 13 inches |
250lbf Flight-Weight Motor
| Designation: | HRM-250-FW |
| Hot-fire Tests: | 11 |
| Testing Period: | 2005 - 2006 |
| Propellants: |
Oxidizer: 90% Hydrogen-Peroxide (liquid) Fuel: HTPB (solid) |
| Thrust - avg: | 250 lbf |
| Chamber Pressure - avg: | 440 psia |
| Burn Duration: | 8 seconds |
| Diameter-grain: | 3.5 inches |
| Length-grain: | 10 inches |
900lbf Battleship Motor
| Designation: | HRM-900-BM |
| Hot-fire Tests: | 15 |
| Testing Period: | 2007 - 2008 |
| Propellants: |
Oxidizer: 90% Hydrogen-Peroxide (liquid) Fuel: LDPE (solid) |
| Thrust - avg: | 900 lbf |
| Chamber Pressure - avg: | 440 psia |
| Burn Duration: | 12 seconds |
| Diameter-grain: | 4.9 inches |
| Length-grain: | 24.5 inches |
900lbf Flight-Weight Motor
| Designation: | HRM-900-FW |
| Hot-fire Tests: | 5 |
| Testing Period: | 2009 - 2009 |
| Propellants: |
Oxidizer: 90% Hydrogen-Peroxide (liquid) Fuel: LDPE (solid) |
| Thrust - avg: | 900 lbf |
| Chamber Pressure - avg: | 440 psia |
| Burn Duration: | 6 seconds |
| Diameter-grain: | 4.9 inches |
| Length-grain: | 24.5 inches |
GEN - I Recovery Test Vehicle
| Designation: | GEN-I-R |
| Propulsion: | M1900 BB - Solid Rocket Motor |
| Launches: | 1 |
| Flight Period: | 2006 |
| Thrust - avg: | 430 lbf |
| Burn Duration: | 3.2 seconds |
| Gross Lift-Off Mass | 56 lb |
| Diameter: | 6 inches |
| Length: | 15.5 feet |
| Max Acceleration: | 7.7 G's |
| Max Velocity: | 0.53 Mach |
| Apogee: | 4,700 feet |
GEN-I Hybrid Flight-Vehicle
| Designation: | GEN-I-F |
| Propulsion: | HRM-900-FW |
| Launches: | 1 |
| Flight Period: | June 2009 |
| Thrust - avg: | 700 lbf |
| Burn Duration: | 6 seconds |
| Diameter: | 6 inches |
| Length: | 15.9 feet |
| Max Acceleration: | 6 G's |
| Max Velocity: | 0.6 Mach |
| Apogee: | 6,100 feet |
GEN-II Hybrid
Flight-Vehicle
(IN PROGRESS)
| Designation: | GEN-II-F |
| Propulsion: | HRM-900-FW |
| Launches: | In-Progress |
| Flight Period: | Tentatively scheduled for launch in 2010 |
| Thrust - avg: | 800 lbf |
| Burn Duration: | 13 seconds |
| Gross Lift-Off Mass | 110 lb |
| Diameter: | 7.5 inches |
| Length: | 16 feet |
| Max Acceleration: | 6.3 G's |
| Max Velocity: | > 1.5 Mach |
| Apogee: | >30,000 feet |
