Some Restrictions on Nuclear Ramjet Engine Performance Imposed by Control System Component Limitations

摘要

There is presented a brief technical discussion of ramjet propulsion thermodynamics. The more important controllable variables effecting thrust are described. Two important performance parameters used in the evaluation of jet engines are explained, thrust coefficient and specific impulse. These parameters are compared for chemically fueled and nuclear powered ramjets, rockets, and turbojets. Theoretical maximum performance, in terms of altitude and Mach number, are computed for an ideally low-drag ramjet vehicle incorporating a nuclear power plant. Considering present state of the art controls and materials limitations, some restrictions to the ideal performance envelope are shown.