Liquid Rocket Engine Tests

Interorbital Systems has designed, manufactured, static-tested (hot-fired), and analyzed the performance of an extensive series of liquid rocket engines. Through this activity, IOS has developed the capability of designing and building reliable, high-performance liquid rocket engines. The company has experience with rocket engines using both cryogenic and storable propellants (including IOS’ proprietary hypergolic fuel, Hydrocarbon-X). Recently, IOS has developed an altitude-compensating nozzle. This type of nozzle allows a rocket engine to generate the highest possible specific impulse (a measure of performance) from sea level to vacuum (space). This type of nozzle is required for both the Sea Star and the Neptune Booster/Sustainer engines. All of the rocket engines developed at IOS have the designation “General Purpose Rocket Engine” (GPRE). Following is a short list of rocket engines developed and tested at IOS.

GPRE 0.5KNF: Thrust = 500 pounds; Cooling = ablative; Propellants = Nitric Acid/Furfuryl Alcohol; Application = Sounding rocket booster or vernier engine

GPRE 0.5KNHx: Thrust = 500 pounds; Cooling=Ablative; Propellants=Nitric Acid/Hydrocarbon X; Application = Sea Star TSAAHTO Satellite Module Engine

GPRE 2.5KLM: Thrust = 2,500 pounds; Cooling = Ablative; Propellants = Liquid Oxygen/Methanol; Application = Sounding rocket booster or vernier engine

GPRE 3.0KNHx: Thrust = 3,000 pounds; Cooling = Ablative; Propellants = Nitric Acid/Hydrocarbon X; Application = Sea Star TSAAHTO Booster/Sustainer engine

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