The lecture presents an overview of some recent results of the work carried out at Alta on the hydrodynamic design and rotordynamic fluid forces of cavitating turbopumps for liquid propellant feed systems of modern rocket engines. The reduced order models recently developed for preliminary geometric definition and noncavitating performance prediction of tapered-hub axial inducers and centrifuga...

reduction of exhaust emissions is a major research task in diesel engine development in view of increasing concerns regarding environmental protection and stringent exhaust gas regulations. simultaneousreduction of nox emissions and particulate matter is quite difficult due to the soot/nox trade-off and isoften accompanied by fuel consumption penalties. towards this aim, automotive engineers ha...

Environmental impact assessment of liquid rocket motor exhaust obtained due to mainly liquid propellant combustion have been highlighted. Exhaust product analysis has been carried out theoretically by computer software NASA CEC -71 to identify toxic emissions of rocket combustion. In the present study a high volume Air Samplers (APM-430) was deployed at predetermined locations near launch pad f...

To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed this paper. This can simulate processes, including combustion and flow thrust chamber, radiation transfer, conduction wall, coolant cooling channel, gas film chamber wall. The numerical method used each physical area, data between computing module, strategy on coupling in...

This paper deals with the application of data mining techniques to the conceptual design knowledge for a LV (launch vehicle) with a HRE (hybrid rocket engine). This LV is a concept of the space transportation, which can deliver micro-satellite to the SSO (sun-synchronous orbit). To design the higher performance LV with HRE, the optimum size of each component, such as an oxidizer tank containing...

Surface tension tanks exploit the liquid surface in transport and gas–liquid separation to provide gas-free propellant for thruster. High efficiency of deflectors can ensure relocation microgravity environment within a short period time, which is helpful providing propellant. This paper explores through drop tower experiments numerical simulations with volume fluid method. The experimental resu...

The Direct Fusion Drive (DFD) is a nuclear fusion engine that will provide thrust and electrical power for any spacecraft. It compact engine, based on the D -3He aneutronic reaction uses Princeton field reversed configuration plasma confinement an odd parity rotating magnetic as heating method to achieve (Cohen et al., 2019), which heat deuterium, also used propellant. In this work we present p...