Combustion Chemistry of Composite Solid Propellants Based on Nitramine and High Energetic Binders

摘要

Chemical and thermal structure of flame of solid propellants based on nitramine (HMX or RDX) and azide polymer (GAP or BAMO-AMMO) has been investigated at pressure of 0.5 and 1.0 MPa by method of molecular-beam mass spectrometry and microthermocouple. Chemical flame structure of pure nitramines at atmospheric pressure has been obtained too. Burning rate has been measured. The probe method of sampling of species from flame allowing to detect products of propellant decomposition (including nitramine vapor) in the zone adjacent to the burning surface has been developed. Eleven species, including nitramine vapor, have been detected in the zone adjacent to the burning surface in the case of nitramine/GAP propellants. Experiments showed that there are two zones of chemical reactions in flame of nitramine/GAP propellants and one zone in flame of nitramine/BAMO-AMMO propellants. Species concentrations have been determined at different distances from the burning surface. Temperature profiles in the combustion wave of solid propellants have been measured. An extensive plateau on the temperature profiles was not observed. Data obtained can be used for creation and validation of combusting model for propellants on the basis of nitramine and azide polymer.