Group Prefect Mark Clark is working on a bi-propellant liquid motor. The hardware shown here is a static test unit to check out the design before making flight weight hardware.
Click on images for full size.
Close up of combustion chamber.
Larger tank is nitrous oxide, smaller is fuel. It is of a tie-rod design so changes can be made with out major machining. All the valves and fittings are SwageLok. Components are mounted to a12" X 28" Al plate. Valves are opened by a spring pulling on the half round plate attached to where the handles were removed.
Over all view.
Fuel is pressurized by the N2O using a piston. The motor will be fired upright with the nozzle down.
The flight weight motor is 3" dia with 5 lbs of fuel/oxidizer. Burn time to be 5 seconds.
Photos were taken in Dec'01