Cryogenic Hybrid Rocket Engine for Testing High-Energy Propellants

Period of Performance: 03/21/1997 - 05/08/1999


Phase 2 SBIR

Recipient Firm

Orbital Technologies Corp.(orbitec)
Space Center, 1212 Fourier Drive
Madison, WI 53717
Principal Investigator

Research Topics


ORBITEC proposes to develop an Advanced Cryogenic Hybrid Rocket Engine (ACHRE) that can be used by the USAF/Phillips Laboratory to test performance of high-energy density propellants from the USAF-funded program. The innovative design is based upon knowledge and experience gained by developing, building and testing the first cryogenic hybrid propulsion system designs for the USAF and NASA. The approach would improve the control of the O/F ratio and overall combustion process and provide a first-ever, fuel-bsed cooling approach in a flight-weight type system. ORBITEC will design the new engine system based on the final results of the Phase I effort. During Phase II, the following technical tasks would be performed: define system engineering and requirements; assess HEDM and other propellant use; assess environmental impact and conduct safety analysis; develop and continue to demonstrate testing of O/F ratio control; engineering analysis; design and development; activiate test facility and prepare DAS design; review and approve design; critical component testing; fabrication, integration, and checkout; engine and system test firings; performance assessment; deliver engine to USAF/PL; and develop flight propulsion system designs for Phase III. During Phase III, a larger version of the advanced Advanced Cryogenic Hybrid Rocket Engine would be designed, built, developed, tested, and eventually flown.