Group 1 : Research on Causes of High Frequency Combustion Instability of Liquid Rocket Combustor and Development of Analytical Method
– Group 1 researches on the causes of combustion instability and development of analytical method by spray test experiment under various pressure condition of coaxial injector and combustion test of model combustor
– Develops the numerical and analytical method to find spray and combustion instability and compare it with experimental data to verify the method
Group 2 : Accurate Prediction of Instability by Structure-Fluid-Propulsion Interaction, Design and Simulation Technique for Improving Stability
– Group 2 predicts instability by linear/nonlinear structure-fluid-propulsion interaction accurately; develops active design and simulation for improving stability and analyzes effect of noise, external protuberance and staging
– Establishes linear/nonlinear unstable response function data map of component of liquid rocket engine and verification of modeling by analysis and test
– Proposes the suppression method of combustion instability by using analysis of flame structure through modeling of real turbulent diffusion and thermodynamic non-ideality
– Suggests passive/active methods for controlling the instability of launch vehicle in POGO and disturbance condition
Group 3 : Next Generation Space Vehicle Propulsion Unit Advanced Research – The Element Technology for Reusable Methane Engine Rocket
– Group 3 establishes optimum design parameters of the core element components, which contains the deduction of design variables and development of assessment techniques of the thrust chamber assembly; develops the micro liquid rocket thrust chamber, which contains the study of characteristics of the propellant mixing and combustion and the study of thrust performance characteristics using the computational analysis of the combustion field; conducts researches on the variable thrust pintle injector design technology for the precise orbit maneuver and attitude control, and thrust vector control technique for the pintle nozzle
– Develops the integrated design technology of methane-oxygen bi-propellant micro liquid rocket engine using GCH4-GOx/LOx mixing/combustion characteristic, injection characteristics over injection condition, numerical analysis of combustion chamber and numerical/experimental results of hypersonic nozzle internal flow.
– Construct the liquid rocket engine evaluation system for the performance check of integrated design demonstration model and obtain the key technology for developing high performance/ eco-friendly methane rocket engine via systematic performance evaluation
