8 November 1996 Radiometric probe design for the measurement of heat flux within a solid rocket motor nozzle
Author Affiliations +
Abstract
Improvements to solid rocket motor (SRM) nozzle designs and material performance is based on the ability to instrument motors during test firings to understand the internal combustion processes and the response of nozzle components to the severe heating environment. Measuring the desired parameters is very difficult because the environment inside of an SRM is extremely severe. Instrumentation can be quickly destroyed if exposed to the internal rocket motor environment. An optical method is under development to quantify the heating of the internal nozzle surface. A radiometric probe designed for measuring the thermal response and material surface recession within a nozzle while simultaneously confining the combustion products has been devised and demonstrated. As part of the probe design, optical fibers lead to calibrated detectors that measure the interior nozzle thermal response. This two color radiometric measurement can be used for a direct determination of the total heat flux impinging on interior nozzle surfaces. This measurement has been demonstrated using a high power CO2 laser to simulate SRM nozzle heating conditions on carbon phenolic and graphite phenolic materials.
© (1996) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Charles L. Goldey, William T. Laughlin, Leslie A. Popper, "Radiometric probe design for the measurement of heat flux within a solid rocket motor nozzle", Proc. SPIE 2815, Optical Radiation Measurements III, (8 November 1996); doi: 10.1117/12.257145; https://doi.org/10.1117/12.257145
PROCEEDINGS
10 PAGES


SHARE
Back to Top