MODELING OF MICROSCALE SOLID PROPELLANT COMBUSTION | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 14, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 203-226 PDF (3.97 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.24421 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| HEGAB A. M. | ||||
| Lecturer, Dept. of Mechanical Power Engineering, Faculty of Engineering, Menoufia University, Shebin Elkom, Egypt. | ||||
| Abstract | ||||
| The numerical procedure for the burning of Ammonium Perchlorate (AP) with a Fuel-Binder (Hydroxyl Terminated Polybutadience HTPB) heterogeneous propellant is presented. This model accounts for the one-step reaction mechanism for the primary diffusion flame between the decomposition products of the Binder (B) and the oxidizer AP and allowed for the complete coupling between the gas-phase physics, the condensed-phase physics, and the unsteady non-uniform regression of the propellant surface. The parameters used in this model are fitted to experimental data for the combustion of AP/Binder. The propagation of the unsteady non-planer regression surface is described, using the Essentially-Non-Oscillatory (ENO) scheme with the aid of the level set strategy. The Alternating-Direction-Implicit (ADI) solver is employed to solve the full Navier-Stokes equations in the gas phase. The results show the effect of various parameters on the surface propagation speed, flame structure, and the burning surface geometry. A comparison between the computational and experimental results is presented. | ||||
| Keywords | ||||
| Composite Propellant; solid particles; sandwich propellant; AP/HTPB | ||||
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