20mN, Variable Specific Impulse Colloid Thruster

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,993.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CE20P
Award Id:
n/a
Agency Tracking Number:
105122
Solicitation Year:
2010
Solicitation Topic Code:
S3.04
Solicitation Number:
n/a
Small Business Information
MA, Natick, MA, 01760-1023
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
185739591
Principal Investigator:
Nathaniel Demmons
Principal Investigator
(508) 655-5565
nate@busek.com
Business Contact:
Judy Budny
Business Official
(508) 655-5565
judy@busek.com
Research Institution:
Stub




Abstract
Colloid thrusters have long been known for their exceptional thrust efficiency and ability to operate over a range of specific impulse due to easily variable charge-to-mass ratio of emitted particles. They have also been considered limited to only very low thrust levels, able to produce few microNewtons from individual emission sites. This has motivated significant research into developing large microfabricated arrays of emitters in order to achieve greater thrust. Busek, using an alternate approach, avoids the complications of large emitter arrays while obtaining about 2.5 milliNewtons/cm2 and about 13,000 emission sites/cm2, and has proven this at the 0.1mN thrust level for over 450 operating hours. Combined with colloids' variable Isp capabilities and thrust/power superior to other electric propulsion devices, these new, high thrust colloid thrusters promise to enable new classes of missions benefiting from variable Isp of 200-5000s (or greater) and variable thrusts up to and exceeding 20mN.For the Phase I effort, Busek shall perform a proof-of-concept demonstrating scalability of its proven 0.1mN, cylindrical emitter into a swept linear or annular configuration (to increase emission area while preserving the cross-section), resulting in a 5mN prototype. For the subsequent Phase II, the emitter will be scaled up to 20mN and packaged and tested with fully integrated propellant storage/feedsystem and electronics.

* information listed above is at the time of submission.

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