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O Q. Q. D. i.._ t_ W A IiIII I- 20 15 10 a 0.20 0.15 0.10 0.05 9.5 9.0 8.5 O t- O i.._ 5 A Power Required: 0.458 Wl$ccm 02 5 10 152025303540 Oxygen Generation Rate (seem) 0.0 0.5 1.0 1.5 2.0 time (sec) 0.15 _o 0.10 a. .E 0.05 2 = 0.00 Oxygen Generation Rate (seem) 7: Electrolysis Power Characteristics as a Figure Function Average Required at 0.6 and 1.0 MPa Pressure. 0 0.05 0,0 0.5 1.0 1,5 2.0 IIIIL] 8.0 7.5 0.8 0.6 5 10 152025303540 ).0 0.5 1.0 1.5 2.0 of Propellant Generation Power Required; b) Difference Rate: in a) Power 0.15 n _" 0.10 _oo 0.00 _ 0.0 Figure 8: Pressures for a Series of Hot-Fire Tests. NASA TM-113157 15 _.^ I 0.5 1.0 4¢ o Copper Combustion Chamber time (see) Mixture Ratio; c) C* Efficiency. I -<3-- 13439_88 o ¢; .e 0 /-_- t__9o _ D439_94 | -_- D439__ / _ t_,a0aa I _ L 1.5 2.0 2.5 3.0 0.4 U_ i-. .Q E o Ignition Delay O ,m w IX ii Figure 9: Combustion Thruster Test Chamber Pressure; Results: a) b) Propellant 0.2 __I iii b/Re time (see) LL[ time (see)PDF Image | Electrolysis Spacecraft Propulsion Applications
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