Miniaturized Low-Power Piezo Microvalve for NanoSat and CubeSat Propulsion

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$699,135.00
Program:
SBIR
Contract:
NNX11CB21C
Solitcitation Year:
2009
Solicitation Number:
N/A
Branch:
N/A
Award Year:
2011
Phase:
Phase II
Agency Tracking Number:
094723
Solicitation Topic Code:
S2.01
Small Business Information
Busek Co., Inc.
11 Tech Circle, Natick, MA, 01760-1023
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
185739591
Principal Investigator
 Douglas Spence
 Principal Investigator
 (508) 655-5565
 doug@busek.com
Business Contact
 Judy Budny
Title: Business Official
Phone: (508) 655-5565
Email: judy@busek.com
Research Institution
 Stub
Abstract
In the Phase I effort, Busek developed a miniature precision piezo-actuated microvalve weighing 32g and occupying 4.5 cm^3. The valve demonstrated continuous flow regulation of 0-12 sccm nitrogen (15psi supply pressure) thru 0-500 sccm nitrogen (1000psi supply pressure), with a leak rate of better than 1.0 x 10^-5 mbar-l/s. The simple, low part-count design was developed with a critical eye toward low-rejection rate manufacturability, with several sensitive assembly operations successfully advanced toward, robust, reliable processes. Resilience under aggressive shock loading, which exhibited negligible effects upon valve operation, was demonstrated. For the Phase II effort, Busek shall continue refining critical assembly processes to improve reliability in assembly, eliminating remaining elastomers in order to achieve an all-metal architecture. Additionally, a supplementary feature for downstream volume compensation (for regulation of incompressible liquids affected by induced flows due to mechanism actuation and/or liquid thermal expansion; a necessary feature for colloid thruster operation) shall be developed. Supporting the colloid application shall be valve driver electronics able to float at thruster beam Voltage. The design shall be validated via vibration and thermovac testing, and culminate in operation of both a gas-based thruster, as well as a colloid thruster to validate the volume compensation feature.

* information listed above is at the time of submission.

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