Detonation engine cycles have been extensively studied in the past, using ideal cycles such as constant volume combustion (Humphrey cycle) or modeled as a shock with Rayleigh heat addition (Zeldovich-von Neumann-Doering cycle). Constant properties along with the assumption of complete combustion, overpredicts the efficiency and specific impulse gains that ideal detonation engines are capable of achieving. In this paper, a modified ZND rotating detonation rocket engine thermodynamic model, for arbitrary gaseous reactants is developed to predict ideal rocket engine performance for parametric concept studies. Next, a tool is developed incorporating NASA's CEA code to calculate chamber specific impulse using equilibrium combustion. The tool is then used to evaluate 270 cases for varying equivalence ratios and initial temperatures for state-of-the-art combustion chamber pressures. The results show that an ideal Rotating Detonation Rocket Engine can significantly reduce the combustor inlet pressure while matching Isp performance of an equivalent ideal Brayton rocket cycle.
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