Self Pressurizing Gas Generator (SPGG)
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, 53717
J. Arthur Sauer
President and CEO
President and CEO
AbstractOrbital 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.
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