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Integrated Propulsion and Primary Structure Module for Small Satellite and CubeSat Applications

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX15CC31C
Agency Tracking Number: 145319
Amount: $749,500.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: S3.02
Solicitation Number: N/A
Solicitation Year: 2014
Award Year: 2015
Award Start Date (Proposal Award Date): 2015-05-11
Award End Date (Contract End Date): 2017-03-30
Small Business Information
6742 185th Ave NE, Redmond, WA, 98052-6714
DUNS: 964004100
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Chris Voorhees
 Principal Investigator
 (425) 358-5692
Business Contact
 Chris Lewicki
Title: President
Phone: (425) 336-2448
Research Institution
Over the last decade, the CubeSat platform has emerged as a viable alternative for both innovative technology development and scientific investigation. However, to fully realize the platform's potential, propulsion capability is required. For low-cost spacecraft developers, this capability remains among the most resource intensive to successfully implement. Planetary Resources Development Corporation (PRDC) proposes to significantly reduce required resources by seamlessly integrating propulsion with another critical resource-intensive subsystem: the spacecraft's primary structure. PRDC will integrate high-reliability COTS components from the medical consumer products industries into an additively-manufactured two-module primary structural element that includes integrated tank, plenum, and manifold geometries for a hybrid green monopropellant / cold-gas propulsion implementation, as well as the spacecraft's launch interface. The resulting system, called the Integrated Propulsion and Primary Structure Module (IPPSM), provides a standard interface, serving as the strongback for simple integration of other Cubesat subsystems and payloads within the 6U and 12U size regimes. During Phase II, PRDC will continue the IPPSM development initiated during Phase I, culminating in the fabrication, assembly, performance evaluation, and environmental test of a full-scale 12U IPPSM prototype with integrated RCS and high-thrust, high delta-V capability. It is expected that the completion of the above work will result in a technical maturation to TRL-6 by the end of Phase II, ready for flight demonstration.

* Information listed above is at the time of submission. *

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