Axial Pintle Controlled Constant Volume Combustion Bipropellant Pulsed Rocket Motor

Idealized analysis has shown that, for the same propellant supply pressure, higher performance can be obtained in a constant-volume combustion device than the traditional constant pressure rocket. CFDRC proposes an effort consisting of multiple levels ofanalysis, followed by design and testing of a rocket engine prototype that will substantiate this claim. Recent relevant experience in advanced motor controls, as well as design and testing of solid propellant motors(http://www.cfdrc.com/research/ed-pintle.html), combined with in-house analysis capabilities, make CFDRC highly qualified to pursue this research.Phase I will consist of an initial propellant screening process, followed by more detailed evaluation and component design. Propellants will include O2, N2O, NO and NO2 as oxidizers and CH4 and C3H8 as fuels. CFDRC will partner with the Univ. of Alabamain Huntsville, leveraging their experience in the testing of N2O/C3H8 rocket systems. CFDRC will then design a rocket chamber utilizing CV principles, which will then be tested at UAH. In Phase II, the R&D will focus on refining the design to fabricateand test a flight-configured upper stage motor. Participation of TRW and Atlantic Research Corporation in this effort will facilitate rapid transfer of this technology and subsequent commercialization. The design tools and test hardware will haveimmediate impact in Air Force and NASA sponsored in-space propulsion initiatives as well as CFDRC clients Atlantic Research, Aerojet, TRW, etc. Other applications include industrial pneumatic actuation control systems and high pressure bipropellantthrottling within the marine and tactical missile industries.