An Advanced Fusion Energy System for OuterPlanet Space Propulsion

Inertialelectrostaticfusion IEF devices using polyhe dral magnetic fields for electrostatic potential well con finement of ions o er lightweight sources of large thermal and electrical power from clean p+11B fusion reactions. Application to direct heating o ers propul sion system thrust/mass ratios 1001000x larger than other advanced concepts in the specific impulse range of 1500 < Isp < 1.2E6 sec. Review of engineering interface limits and constraints of these fusion sources shows that no new and unconventional technologies are needed for their achievement Analysis of an outerplanet mission to Titan Saturn’s large moon with dilutedfusionproduct DFF propellant heating engine systems shows single stage vehicles with payload delivery fractions of 0.140.18 of gross launch mass, with transit times of only 1113 weeks. Economic models of development and de ployment of such vehicles suggest that practical, rapid space flight and colonization could be achieved within present budget limits. Nomenclature a0 = initial vehicle force acceleration, m/s2 af = final vehicle force acceleration, m/s2 AU = astronomical unit, distance from E to Sun B = magnetic field strength, Tesla C0 = total cost over mission life, Y, E = Earth E0 = core energy in IEF system, eV F = engine thrust, N F = engine system thrust/mass ratio fL = payload fraction of gross mass Ggross = ratio gross fusion to electric drive power g0 = acceleration of gravity at Earth’s surface Isp = engine system specific impulse,