PHOTO 38 -- Pressure-burnrate test apparatus, Jan. 1986
 | This photo shows part of the apparatus that was utilized to determine the relationship between propellant burnrate and chamber pressure, which is important for the design of rocket motors. Small samples (strands) of propellant were burned in a pressure vessel and the rate of burning was recorded using thermocouple sensors. Such testing was conducted at pressures ranging from atmospheric, to 1540 psi (106 bar). |