Propellant management for low thrust chemical propulsion systemsLow-thrust chemical propulsion systems (LTPS) will be required for orbital transfer of large space systems (LSS). The work reported in this paper was conducted to determine the propellant requirements, preferred propellant management technique, and propulsion system sizes for the LTPS. Propellants were liquid oxygen (LO2) combined with liquid hydrogen (LH2), liquid methane or kerosene. Thrust levels of 100, 500, and 1000 lbf were combined with 1, 4, and 8 perigee burns for transfer from low earth orbit to geosynchronous earth orbit. This matrix of systems was evaluated with a multilayer insulation (MLI) or a spray-on-foam insulation. Vehicle sizing results indicate that a toroidal tank configuration is needed for the LO2/LH2 system. Multiple perigee burns and MLI allow far superior LSS payload capability. Propellant settling, combined with a single screen device, was found to be the lightest and least complex propellant management technique.
Document ID
19810057794
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hamlyn, K. M. (Martin Marietta Aerospace Denver, CO, United States)
Dergance, R. H. (Martin Marietta Aerospace Denver, CO, United States)
Aydelott, J. C. (NASA Lewis Research Center Cleveland, OH, United States)