摘要
The combustion （ballistic） properties of a high solid loading composite solid propellant family （Butalites） was studied experimentally by using propellant formulations based on hydroxy-terminated polybutadiene pre-polymer （HTPB） as a fuel binder main backbone, bimodal system ammonium perchlorate oxidizer （AP） and aluminum powder （AI） as metallic fuel. Burning rates were doubled at various pressures, when solids loading （AP and 17% A1） were increased from 80 to 88% and the measured characteristic velocity values were increased by about 100m/sec. The pressure exponent （n） values were lower with 80-85% solids loading. The burning rates were increased by about 2-5% when comparing the data obtained by static firing with those obtained by the strand burner method.
The combustion （ballistic） properties of a high solid loading composite solid propellant family （Butalites） was studied experimentally by using propellant formulations based on hydroxy-terminated polybutadiene pre-polymer （HTPB） as a fuel binder main backbone, bimodal system ammonium perchlorate oxidizer （AP） and aluminum powder （AI） as metallic fuel. Burning rates were doubled at various pressures, when solids loading （AP and 17% A1） were increased from 80 to 88% and the measured characteristic velocity values were increased by about 100m/sec. The pressure exponent （n） values were lower with 80-85% solids loading. The burning rates were increased by about 2-5% when comparing the data obtained by static firing with those obtained by the strand burner method.
