Hybrid Rocket Engine Combustion And Flow With The Burning Surface Regularity Of The Regression,

Remarkable advantage such as low costing, high security, high reliability, low exhaust plume signal characteristic and environment non-pollution, which does not belong to Solid Rocket Motor (SRM) or Liquid Rocket Engine (LRE), advances astronautic experts to have much more interest in Hybrid Rocket Motor (HRM). Because the combustion mode between oxidizer and solid fuel is in particular, HRM is different from SRM and LRE. This thesis successfully builds Arrhenius-type pyrolysis law of HRM solid fuel by carrying on an experiment research on pyrolysis behavior, and further presents numerical simulation phenomenon on combustion, flow and surface regression rate of HRM. The content of this thesis can be divided into three parts:This part develops pyrolysis behavior analysis of HRM solid fuel by two approaches: first, Differential Scanning Calorimetry (DSC); second, hot-plate conductive heating, and completes gas collection of solid fuel pyrolysis. The experiment results of both Arrhenius-type kinemics parameters and qualitative and quantitative analysis on pyrolysis gas are determined for numerical calculation of solid fuel surface regression rate in HRM.A GOX/HTPB numerical model which presents combustion, flow and surface regression rate of HRM is well built and is proved to be high veracity in solid fuel surface regression rate by contrasting experiment data in second part. Based on above validation, some characteristics of HRM combustion and flow are spread out to such that. High temperature flame is mostly concentrated in strip zone between solid fuel surface and motor axis, and the extent of gas mixing is not good in the neighborhood of motor axis and solid fuel surface so that here temperature is a little lower.As to liquid oxidizer HNO₃80% + N₂O₄20% (mass ratio) and some solid fuel (pyrolysis gas is mainly C₄H₆), the last part in detail describes numerical simulation process of HRM combustion, flow and surface regression rate. It analyzes the influence of oxidizer mass flux and length-radius ratio on HRM temperature filed and component concentration distributing, and demonstrates igniting and solid fuel surface regressing.