Application of Holography to the Combustion Characterization of Solid Rocket Propellants.
Final rept. Jul 76-Dec 77,
TRW DEFENSE AND SPACE SYSTEMS GROUP REDONDO BEACH CALIF
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The feasibility of holographically three-dimensionally recording particulate generated by the combustion of small 14 by 18 by 116 inch solid rocket propellant samples at high pressures 1000 psi was demonstrated. A new lens-assisted holographic technique gave 3 micron resolution of particles in the combustion environment. Laser pulses of less than or equal to 10 nanoseconds were needed to avoid holographic fringe effects with metallized propellants. Reflected light holograms were also recorded of both particulate and burning propellant. A double exposure-double reference beam lens-assisted technique was used to record the particle field at two different times. The two recordings could be separately reconstructed. These records gave particle velocities. Equipment a double reference beam-lens-assisted holocamera and modified pulsed ruby laser illuminator was built and delivered to the Air Force Rocket Propulsion Laboratory for their own in-house program. Author
- Combustion and Ignition
- Solid Rocket Propellants