Engine Testing for KNSO formulations w/B-1 and Iron Oxide (RIO)
238 KNSO w/B-1 and 1%RIO
Burn Time = 1.87 sec
Propellant wt. = 0.27 lb
Nozzle Throat = 0.031 in2
Max Chamber Pressure = 516 psi
Max. thrust = 24 lbs
Ave thrust = 14.6 lbs = 65 N
Total Impulse = 121.5 N sec = 27.3 lb sec
Isp = 101 sec
Motor Class = G 65
238 KNSO w/B-1 & 1% RIO
Burn time = 1.6 sec
Propellant wt. = 0.27lb
Nozzle Throat = 0.022 in2
Max thrust = 36.8 lbs
Max Chamber Pressure = 1115 psi
Average Thrust = 22.6 lbs = 100.6 N
Total impulse = 36.2 lb sec = 161 N sec
ISP = 134 sec
Motor Class = H100
238 KNSO w/B-1 and 0.075% RIO
Burn time = 1.91 sec
Propellant wt. = 122.6 g = 0.270 lbs
Nozzle throat = .02325 in2
Max. Thrust = 25.6 lbs
Max. Chamber Pressure = 1090 psi
Ave Thrust = 16.1 lbs = 71.6 N
Total Impulse = 31.1 lb sec = 138.3 N sec
ISP = 115
Motor Class = G 72
238 KNSO B-1 RIO Moonburner
Propellant mass = 120.7g = 0.266lb
Throat area = 0.01754 in2
Thrust duration = 3.00 sec
Max Thrust = 20.7 lbs
Max Chamber Pressure = 840 psi
Ave Thrust = 10.2 lbs = 45.3 N
Total impulse = 136 N sec = 30.6 lb sec
Isp = 115
Motor Class = G45
Obvious increase in performance with higher RIO level. Motors with RIO exhibit a more neutral burn profile. The presence of RIO, even in very small amounts, seems to significantly minimize the burn rate decrease observed when surfactant is present (see low and mid pressure sorbitol test stand results). The RIO does not effect the outstanding viscosity reduction obtained in molten formulations with the presence of surfactant. All motors used 3/8" cores.
