Experimental investigation of erosive burning in solid propellant motors

Justin Slaby, Purdue University

Abstract

Erosive burning changes the burning rate of solid rocket propellants which can normally be approximated by St. Robert's law. This can play a major role in the performance of a solid rocket motor depending on the geometry of that motor. A 2-D slab combustor has been developed for the study of erosive burning. The modular design permits study of planar and slotted propellant configurations (as are present in segmented rocket motors) with adjustable port-to-throat area ratios. The main focus of this thesis is to experimentally investigate erosive burning by comparing test firings where erosive burning is expected with tests where it is not. Thermocouples were added to the original design to help gather burnout data from the tests. A ballistic element model has also been developed and has been used to analyze the tests using the classical Lenoir-Robillard erosive burning model. Although the test data that has been gathered seems reliable and consistent, reconstructing the tests with the ballistic model has proven difficult. This is likely do to the limitations of the Lenoir-Robillard erosive burning model and a new model would be required to better match the test data.

Degree

M.S.A.A.

Advisors

Heister, Purdue University.

Subject Area

Aerospace engineering

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