Nuclear powered ion engine orbit transfer vehicle design and operational effectiveness

Abstract

The feasibility and the cost effectiveness for using nuclear powered electric propulsion orbit transfer vehicles (EOTV) to move Block 3 NAVSTAR Global Positioning System (GPS) satellites from low earth orbit (LEO) to a 10,900 nm orbit are determined. The electric propulsion systems considered are present and 1990's technology ion engines using mercury, xenon or argon for a propellant. A systems cost model which combines payload, power source, trajectory, and earth-to-LEO launch parameters with algorithms characterizing the electric propulsion system is used. The least costly systems which had an outbound triptime equal to or less than 90 days are determined. These systems are then compared with the PAM D-II, CENTAUR-G, and IUS in terms of total deployment costs for 28 GPS satellites launched at a rate of four per year for seven years. The study finds that a reusable EOTV with 37 Xenon ion engines powered by a nuclear reactor can perform the mission for less cost than the chemical systems.