Title of Presentation: Spacecraft Propulsion System Impacts When Incorporating Advanced Chemical Propulsion System Technologies
Primary (Corresponding) Author: Michael P.J. Benfield
Organization of Primary Author: The
Abstract: A study was performed for the NASA MSFC In-Space Propulsion Technology Projects Office to assess the propulsion system wet mass impact of incorporating candidate chemical propulsion system technologies (active mixture ratio control, ultra light weight tank, high temperature and pressure thrust chambers, LOX/N2H4 and advanced monopropellants) into previously flown spacecraft missions (MESSENGER, Cassini, MRO, and MGS).
Combining the technologies, three proposed propulsion systems were developed. The advanced monopropellant propulsion system incorporated ultra light weight tank technology with a higher performance monopropellant. The advanced earth storable propulsion system incorporated the ultra light weight tank technology, the active mixture ratio control technology, and the high temperature and pressure thrust chamber technology. The advanced space storable propulsion system incorporated the ultra light weight tank technology, the active mixture ratio control technology, and the LOX/N2H4 technology.
Utilizing a spacecraft propulsion system sizing tool, the proposed propulsion systems were modeled and the impacts assessed. Results indicate that advanced monopropellant propulsion systems provide benefit to low spacecraft propulsive energies and advanced space storable propulsion systems provide benefit to high spacecraft propulsive energies, while the advanced earth storable propulsion systems have the greatest overall benefit to all ranges of spacecraft propulsive energy.