Operational performance parameter range in ICF propulsion theory.

This paper explores the operational performance parameter range for inertial confinement fusion propulsion systems under the assumption of best case and worst case mission scenarios. This includes the spacecraft thrust, jet power and specific power. We show the derivation of the key driving equations and then simplify these with approximations for ease of domain space analysis. This includes a consideration of minimum and maximum values for jet efficiency, momentum weighting factor, nozzle divergence angle, fuel burn-up fraction, capsule mass and detonation pulse frequency. It is estimated that the range of parameter values may be of order 0.001 N–100 MN thrust, 1000 W–1,000 TW jet power, 0.01 W/kg–10 GW/kg specific power. Although this range includes values that are likely outside the realistic design space of applicability and to show this data from published designs is also examined. The analysis is considered for reaction isotopes of low mass hydrogen and helium nuclei only and does not take into account the possibility of propellant expellant augmentation, vehicle staging, design optimality or enhanced fuel reactions. • Attempt to examine inertial fusion propulsion theory from a broad perspective. • Derivation of driving equations for various inertial fusion propulsion parameters. • Analysis of min-max range inertial fusion propulsion performance space missions. • Analysis of inertial fusion propulsion performance data from concept designs. • Map of fusion propulsion parameters to derive the requirements for missions. [ABSTRACT FROM AUTHOR]