Solid rocket motors operate at high temperatures that can potentially damage engineering materials used for motor nozzles or thrust vanes. In this work, surface temperature measurements were collected on solid rocket motor components of varying materials exposed to the combustion of ammonium perchlorate-based solid propellants. Spatially-resolved temperatures were measured using a novel two-color pyrometer built from an acousto-optic tunable filter (AOTF) coupled to a near IR camera. Temperatures were then verified using a single-point visible spectrometers. Experiments conducted in low pressure conditions inside a high altitude chamber at Sandia National Laboratories illustrate the temporal and spatial evolution of temperature gradients across the nozzle and vanes.
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