In this study the effect of acoustic pressure on the burning rates of various solid rocket propellants is investigated.nThe test burner is a side-vented, cylindrical cavity which is mounted on a surge tank. Propellant grains are mounted at opposite ends of the cavity and burn on their opposed inner faces. Such an arrangement allows for analytical simplicity by exhibiting one-dimen¬sional, first mode oscillatory behavior, placing the burning surfaces at the pressure antinodes. Thus the study of acoustic pressure effects is possible without the effect of parallel gas flow.nThe grains are carefully measured and matched to within 0.002 inches. A pressure transducer and galvanometer oscillograph are used to measure and record the mean pressure, amplitude and frequency of pressure oscillations, and burning time.
展开▼
