Session
Technical Session III: Military Applications
Abstract
Interest in the application of primary solar-electric propulsion to high-energy Earth orbital and deep-space missions has increased in recent years because of its inherent propellant economy and the promise of greatly enhanced payload weight capacity for a given vehicle launch weight. This paper describes a small, low-cost electric propulsion demonstration satellite, capable of ascending from low altitude to geosynchronous orbit in ten months or less, using only about 1 kW of propulsive power. Based on available technology of ion thrusters and lightweight solar arrays, and using elements of current light satellite design, this mission is of timely interest as a step in the evolution of future operational electric propulsion transfer vehicles. Generic data on system and mission design for this demonstration vehicle are presented along with relevant literature references.
A Small, Primary Solar-Electric Propulsion Demonstration Satellite
Interest in the application of primary solar-electric propulsion to high-energy Earth orbital and deep-space missions has increased in recent years because of its inherent propellant economy and the promise of greatly enhanced payload weight capacity for a given vehicle launch weight. This paper describes a small, low-cost electric propulsion demonstration satellite, capable of ascending from low altitude to geosynchronous orbit in ten months or less, using only about 1 kW of propulsive power. Based on available technology of ion thrusters and lightweight solar arrays, and using elements of current light satellite design, this mission is of timely interest as a step in the evolution of future operational electric propulsion transfer vehicles. Generic data on system and mission design for this demonstration vehicle are presented along with relevant literature references.
