Vacuum Arc Nano Thrusters for Nanosatellite Spacecraft Constellations

Alameda Applied Sciences Corporation proposes to develop a new type of nano-thruster electric engine for highly parallel, distributed constellations of nano-satellites and other space propulsion applications. A key feature of the proposed Phase-I is theuse of an Inductive Energy Store (IES) driver to power the vacuum arc nano-thruster, which has a mass of 90% PPU efficiency from 1-10 W. The province of missions for such a thruster includes attitude control of satelliteconstellations of Class I microspacecraft (~10 kg, ~10 W). This thruster requires =100 W, to provide both attitude control and slew maneuvers with the same engine. In Phase I,AASC will fabricate a prototype thruster with a 1-10 W inductive PPU, using NASA and/or Air Force space qualified components where possible. We will measure plasma streaming velocity and mass utilization rates for many elements or alloys. We will conductdirect thrust and efficiency measurements at Edwards AFB. In Phase II, we will develop a flight qualified engineering model by addressing other key issues such as the lifetime of the thruster, environmental factors and mission requirements.The primaryapplication of the specific thruster to be developed in the proposed work will be for Class I micro-spacecraft, ~10 kg. However, beyond this immediate application, the thruster could find use for larger or smaller spacecraft, with further development.