Precision techniques for measuring burning rates of solid propellants during pressure transients

Jeffrey J. Murphy, Alan O. Martin, Herman Krier

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Both the steady-state and the transient burning rates of solid rocket propellants (caused by rapid pressure excursions) are not well characterized, especially for propellants where prescribed formulation changes alter the flame structures. Non-linear pressure dynamics causing significant burning rate transients need to be related to the "linear" frequency response functions measured, i.e. those due to small oscillatory perturbations. In order to study these phenomena, an experiment to directly measure the burning rate of a solid propellant during a large, monotonic pressure transient is currently under development. Two methods, to be used in this experiment, of precisely measuring the time-resolved burning rate are described here: a laser scanning system and an ultrasonic echo-location system. Both systems have been successfully used to measure the steady state burning rate. Application to a non-linear transient experiment requires improvements in the precision and time resolution of the systems. Modifications which will accomplish this are currently being implemented.

Original languageEnglish (US)
Title of host publication36th AIAA Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
StatePublished - 1998
Event36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States
Duration: Jan 12 1998Jan 15 1998

Other

Other36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
CountryUnited States
CityReno
Period1/12/981/15/98

ASJC Scopus subject areas

  • Engineering(all)
  • Space and Planetary Science

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