Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

“…In the case of the fluidic resistance element, the pressure loss was modeled through an empirical equation as a constant multiple of the combustion chamber pressure, and the pump, turbine, and combustion chamber were modeled through the logarithmic equation. It was verified with Vulcain, HM7B, and SSME engines and showed a low error rate despite the simple modeling method with an average of 4%, 2%, and 6% performance errors per component unit [54]. In Korea, the Korea Aerospace Research Industry (KARI) developed a simulation model of open-cycle LPRE in steady-state using a linearization approach and transient state using in-house code [55][56][57] and of staged combustion cycle LPRE using energy balance equations to check operating points [58].…”

“…In the component library (including the thrust chamber, gas generators, turbines, pumps, pipelines, and valves), the stationary macroscopic behavior (typically including the pressure, temperature, flow rate, and power) of each module is simulated by the basic zero-dimensional analytical model with some empirical correlations [49][50][51][52][53]. In Brazil, the Institute of Aeronautics and Space (IAE) developed and reported a steady-state modeling and simulation program for an open-cycle LPRE using C++ programming [54]. In the case of the fluidic resistance element, the pressure loss was modeled through an empirical equation as a constant multiple of the combustion chamber pressure, and the pump, turbine, and combustion chamber were modeled through the logarithmic equation.…”

Microstructural and ablative properties of graphite nozzles with SiC coating deposited by CVD technique

“…The resistance at the throat is particularly important since the strongest heat fluxes are found in this region, as represented in figure 1. The total thermal flux profile is estimated from an analytical thermal analysis based on a Russian methodology [10][11][12] combined with Bartz correlation, that shows a maximum thermal load of 0.75 MW m −2 is obtained in the throat region of a 5 kN chamber [13].…”

A new synthetic metamodel methodology for liquid‐propellant engine's cooling system optimization

“…The objective function strives for the maximization of the specific impulse and the thrust‐to‐weight ratio of the engine on the basis of the systemic requirements and design assumptions by changing the combustion pressure and oxidizer‐to‐fuel mass flow rate ratios. Mota et al 17 studied the performance and dry weight of the engine to develop the L‐75 with an oxygen‐ethanol propellant. Then, they analyzed the effects of changing the design parameters on the performance, and studies for new propulsion systems are now being performed in the field of aerospace.…”