A Neptune Aerocapture Systems Analysis is completed to determine the feasibility, benefit and risk of an aeroshell aerocapture syst em for Neptune and to identify technology gaps and technology performance goals. The high fidelity systems analysis is completed by a five center NASA team and includes the following disc iplines and analyses: science; mission design; aeroshell configuration screening and defi nition; interplanetary navigation analyses; atmosphere modeling; computatio nal fluid dynamics for aero dynamic performance and database definition; initial stability analyses; guidance development; atmospheric flight simulation; computational fluid dynamics and radiation analyses for aeroheating environment definition; thermal protection system design, concepts and sizing; mass properties; structures; spacecraft design and packagi ng; and mass sensitivities. Results show that aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the sa me launch vehicle. In addition aerocapture results in a 3-4 year reduction in trip time compared to all-pr opulsive systems. Aerocapture is feasible and performance is adequate for the Neptune a erocapture mission. Monte Carlo simulation results show 100% successful capture for all case s including conservative assumptions on atmosphere and navigation. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic met hods and validation for det ermining coupled 3-D convection, radiation and ablation aeroheating rates and loads, and the effects on surface recession.
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