In this study, the combustion process of gaseous Oxygen on the surface of HTPB (Hydroxyl-Terminated Polybutadiene) solid fuel has been investigated. To simulate the chemically reactive flow, Navier-Stokes equations and species transport equations were solved using LU-SW implicit scheme. Modeling this kind of combustion process demands a deep understanding of the pyrolysis phenomenon on the solid fuel surface. Experimental studies conducted in this field show that the main gaseous product of the pyrolysis process is C 4 H 6 . An experimental equation which is dependent to the temperature of the fuel surface is used to determine the gas production rate during pyrolysis process. The temperature of the fuel surface can be obtained by applying energy equation in gas-solid interface. The combustion process of gaseous Oxygen and C 4 H 6 has been described by two quasi-global chemical kinetics models. According to the obtained results, the main characteristic parameters of combustive flow such as the flame temperature and mass fraction of chemical species are strongly affiliated to the applied chemical kinetics model. Finally, the results of modeling based on two different models of chemical kinetics are presented and solid fuel surface regression rate is compared with other numerical results.
How to cite this article Ahangar M, Hoseini A. Experimental Study of the performance parameters of a plasma thruster using dielectric barrier discharge with the magnetic field. Modares Mechanical Engineering. 2022; 22(06):393-406
The primary purpose of this paper is to simulate the "stored gas type pressurizing system" for propellant tanks in a launch vehicle. Preventing the cavitation occurrence in propellant pumps (as the propulsion requirement) and providing required level of pressure in propellant vessels to prevent them from buckling against external aerodynamic forces (as the structural requirement) are the two most important goals of this system. In this paper primarily the basic equations have been derived. A quasi-steady iterative process has been selected to march in time domain. The simulation has been done with time marching steps to take into account the prediction of pressure change in propellant vessels' ullage and propellant pumps' inlet flow during the working time. An optimization has been done to obtain the best system properties such as cutting time and the minimum number of supplier capsules which should be carried by the launch vehicle.
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