Monopropellant Thruster Exhaust Effects upon Spacecraft

摘要: a = ion engine exhaust opening radius A cross-sectional area Ann Einstein coefficient B absorption c speed of light D thruster diameter at the plane e electron charge E energy f oscillator strength (Landenburg/value) h Planck constant / photon intensity J inner quantum number k Boltzmann m atom mass n arrival rate per unit time n}n excitation level n0 neutral density N exchange production JV N" adsorbed atoms N(r,x) r distance from Pa probability P pressure Pv vapor Q cross section t T temperature x measured perpendicular to plume centerline x',y,z dimension as in Fig. 5 a,/3 angles (see 5) F evaporation F(r,0) flow Fa line width AL incremental length 0 angle X wavelength Ho' — which leave v frequency mean life w statistical weight