Self Pressurizing Gas Generator (SPGG)

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$100,000.00
Award Year:
2009
Program:
SBIR
Phase:
Phase I
Contract:
FA9300-09-M-3002
Award Id:
92911
Agency Tracking Number:
F083-111-0643
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, 53717
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
196894869
Principal Investigator:
J. Arthur Sauer
Aerospace Engineer
(608) 229-2752
sauerc@orbitec.com
Business Contact:
Eric Rice
President and CEO
(608) 229-2730
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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