Nitramine composite solid propellant modeling
Abstract
A theoretical model for the combustion of nitramine composite solid propellants is presented. An nitramine composite propellant typically consists of several distributions of cyclotetramethylene-tetranitramine crystals (HMX) and ammonium perchlorate crystals (AP) mixed in a hydrocarbon fuel binder such as polybutadiene (HTPB). The model, called the High Energy Petite Ensemble Model (HYPEM), is based upon a statistical treatment of the propellant's oxidizer crystals. It is a physiochemical combustion model with multiple flames situated over HMX and/or AP crystals. The HMX section of the model averages the propellant combustion in time while the AP portion averages the propellant combustion over the surface area of the propellant. Results from the HYPEM combustion model are compared with experimental burning rate, pressure exponent and temperature sensitivity for a wide variety of propellants containing multiple distributions of HMX and/or AP crystals. Composite propellant combustion properties are examined by parametrically varying particle size, pressure, oxidizer solids loading and formulation.
Degree
Ph.D.
Advisors
Osborn, Purdue University.
Subject Area
Aerospace materials
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