Vacuum Arc Nano Thrusters for Nanosatellite Spacecraft Constellations

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$98,095.00
Award Year:
2001
Program:
SBIR
Phase:
Phase I
Contract:
F29601-01-C-0133
Award Id:
52249
Agency Tracking Number:
011NM-1174
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
2235 Polvorosa Ave, Suite 230, San Leandro, CA, 94577
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
836439968
Principal Investigator:
NianshengQi
Principal Scientist
(510) 483-4156
qi@aasc.net
Business Contact:
MahadevanKrishnan
President
(510) 483-4156
krishnan@aasc.net
Research Institute:
n/a
Abstract
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 <60 g while operating at >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 V to operate, vs. the ~2 kV for the PPT. The thruster might be scaled to >=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.

* information listed above is at the time of submission.

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