Self Pressurizing Gas Generator (SPGG)

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-09-M-3002
Agency Tracking Number: F083-111-0643
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2009
Solicitation Year: 2008
Solicitation Topic Code: AF083-111
Solicitation Number: 2008.3
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, 53717
DUNS: 196894869
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 J. Arthur Sauer
 Aerospace Engineer
 (608) 229-2752
 sauerc@orbitec.com
Business Contact
 Eric Rice
Title: President and CEO
Phone: (608) 229-2730
Email: knaufs@orbitec.com
Research Institution
N/A
Abstract
Orbital Technologies Corporation (ORBITEC) proposes to develop a monopropellant Self-Pressurizing Gas Generator (SPGG) warm gas pressurization system for satellite propulsion system applications.  The SPGG system will utilize a novel method to pressurize the propellant.  The proposed system offers significant advantages over the traditional helium gas pressurization system.  The SPGG will provide a constant pressure to the satellite thrusters and, therefore, a constant flow rate to extend mission flexibility while maintaining maximum thruster performance.  The system will also significantly decrease inert mass and volume through efficient propellant use, low-pressure tankage and minimization or elimination of residual propellant.  All of these attributes are made available to the satellite designer at a reduced cost due to the decreased launch mass and volume.  The Phase I effort will involve system design for quantitative comparison to the state of the art as well as proof of concept experimentation.   BENEFITS: ORBITEC anticipates that the immediate results of the Phase I work will demonstrate the feasibility and merit of the SPGG system.  Phase I has been structured to provide the necessary experimental groundwork towards the successful development of the SPGG warm gas pressurization system.  Specific output of the Phase I program will include design trade and cost studies, the fabrication and testing of key elements of the SPGG system, and the preparation of preliminary designs and plans for the demonstration of an integrated flight-like system in Phase II.  This technology aims to reduce the cost and improve the flexibility of spacecraft pressurization systems by providing a constant pressure to the satellite thrusters, and therefore a constant propellant flow rate, to extend mission flexibility while maintaining maximum propulsion system performance.  The system will also significantly decrease inert mass and volume through efficient propellant use, low pressure tankage and minimization or elimination of residual propellant.  All of these attributes are made available to the satellite designer at a reduced cost due to the decreased launch mass and volume.  Near-term military applications include the design of propulsion systems for all types of USAF spacecraft systems.  A wide range of NASA and commercial propulsion system development efforts can also benefit from the low-cost injector stability screening techniques developed in this program.

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

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