Propulsion Trades for a 2035-2040 Solar Gravitational Lens Mission

Abstract

The Solar Gravitational Lens (SGL) enables resolved imaging and spectroscopy of nearby terrestrial exoplanets, but useful science begins only after a spacecraft reaches roughly 650-900 astronomical units (AU). A 20 yr lower-bound trip to 650 AU requires an average radial speed of 32.5 AU per year, or 154 km/s, before launch, targeting, steering, and operations margins. We compare close-perihelion solar sailing, fission-electric nuclear electric propulsion (NEP), and high-thrust Oberth injection followed by NEP cruise using common lower-bound outbound-leg architecture envelopes, not closed end-to-end trajectories. For an ideal sail passing 0.05 AU from the Sun, total sailcraft areal density must be about 4.9 grams per square meter to reach 105 km/s, and 2.3 grams per square meter to reach 155 km/s. Thus sub-20 yr sail-only access requires ultra-low areal density plus deep-perihelion thermal qualification. For a 20 t NEP spacecraft with 800 kg payload and Isp=9000 s, optimized constant-power transfers reach 650 AU in t_rep ~ 27-33 yr when the integrated power-plus-propulsion specific mass is 10-20 kg per electric kilowatt, requiring 0.18-0.30 megawatt-electric (MWe) and few-newton thrust. NEP-only t_rep <20 yr requires <3 kg per electric kilowatt, while hybrid architectures can approach t_rep ~ 20 yr if an upstream injection stage supplies 50-70 km/s. Thus sail-first is the nearer-term lightweight-access path; hybrid injection+NEP is higher-capability but requires prior high-energy-injection and 0.2-0.4 MWe integrated NEP demonstrations.