Laser Holocamera Droplet Measuring Device.
Final rept. Nov 68-Jul 69,
TRW SYSTEMS GROUP REDONDO BEACH CA
Pagination or Media Count:
An eight-month experimental program was conducted to demonstrate the applicability of holography to the study of rocket engine combustion. Both reacting and non-reacting droplet sprays were investigated via pulsed ruby laser wavelength 0.6943 micron holography and laser-illuminated photography. An improved two-beam transmission holocamera was designed, constructed and installed on a sea level rocket engine test stand. The ruby laser and transmission holocamera are described and resolution measurements presented. In addition, liquid propellant light attenuation measurements, cold flow spray, and liquid propellant combustion studies are described. The cold flow tests involved holography and laser photography of H2O sprays and H2O on N2O4 sprays simulating actual propellant injection conditions. Holography of liquid rocket combustion was accomplished using a small windowed rocket engine operating with N2O4 and 5050 N2H4-UDMH propellants. Reacting sprays of this propellant combination were successfully holographed and reconstructed. Virtual images of the reconstructions were photographed. Reconstruction photographs of reacting droplet sprays were used to measure drop-size distributions. The holography of solid rocket propellants was investigated. The feasibility of transmission holography of particles entrained in the nozzle exhaust of metal-loaded solid propellant motors was demonstrated. Several reflected light holocameras were designed and tested to record the burning surface of solid propellant grains in windowed high pressure motors and combustion bombs. Author
- Combustion and Ignition