An Investigation of Experimental Techniques for Obtaining Particulate Behavior in Metallized Solid Propellant Combustion.
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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A continuing investigation is being conducted to develop techniques which can be used to obtain quantitative data that can be used to relate solid rocket propellant composition and operating environment to the behavior of solid particulates within the grain port and exhaust nozzle. The techniques employed are high speed motion pictures of propellant strand burners and slab burners in a cross-flow environment, SEM analysis of post-fire residue strand, slab, and motor, determination of D32 across the exhaust nozzle using measurements of scattered laser light, and holograms of burning propellant strands and slabs in a cross-flow environment. In addition, work has been initiated to develop automatic data retrieval methods for obtaining particle size distributions from holograms taken of the combustion of solid propellants. Actual particle size of burning aluminum particles were obtained in high speed motion pictures by using high intensity rear illumination of the burning propellants to eliminate the flame envelopes surrounding the burning particles. Measurements of diffractively scattered light were successfully made for determination of changes in D32 across a solid propellant rocket motor exhaust nozzle. However, to date, propellant composition and grain geometry have significantly limited the range of obtainable data. Two-dimensional motors have been successfully employed to obtain good quality holograms of propellant burned in a cross-flow environment. A Quantimet 720 has been used in an initial effort to obtain particle size distributions from a photograph taken of a reconstructed hologram.
- Test Facilities, Equipment and Methods
- Combustion and Ignition
- Solid Rocket Propellants