Evaluating Maneuvering Capabilities of the Enpulsion Nano Lark for the NASA Landholt Mission

Abstract

The NASA Landholt Mission will be an "artificial star" satellite in a one-year geosynchronous (GEO) or near-GEO orbit to improve stellar flux calculations and analysis. The satellite will need to perform two types of propulsion maneuvers throughout the mission: station-keeping in GEO to stay in the provided orbital slot, and a low-thrust spiral transfer from GEO to a graveyard orbit roughly 300 km above GEO following the primary operations. The Enpulsion Nano Lark (EN), a Field Emission Electric Propulsion system, is planned to perform the maneuvers. Indium propellant with the EN is limited, so we perform preliminary calculations to test of the EN would be able to meet the mission requirements. Using typical Delta-V (the units used to characterize velocity changes required for orbital energy adjustments) levels for satellites in GEO (45-55 m/s), and using the Tsiolkovsky Rocket Equation to relate Delta-V to propellant mass, we estimate a worst-case scenario of roughly 160 g of propellant will be consumed throughout all maneouvers and potential orbital anomalies. Given the 220 g provided by the EN, we calculate a margin for propellant of roughly 27% for the primary mission. This preliminary evidence suggests that the EN will be able to accomplish the necessary maneuvers for the Landholt Mission.