Interplanetary Nuclear Ion-Drive Rocket
This report discusses an ion-drive rocket required to continuously produce 400 N of thrust with a specific impulse of 5500 seconds. For generation of necessary power, this vehicle uses a nuclear reactor as the heat source. This vehicle is to have a payload mass of 14000 kg, and a required ΔV = 35,000 m/s. Two possible power generation cycles are proposed and analyzed: A Rankine (water) cycle and a Brayton (nitrogen) cycle.
Turbojet Engine Design/ Off-Design performance analysis
This report discusses a single-spool fixed-area turbojet missile-class engine with a simple converging nozzle. The on-design engine fluid dynamics and performance is analyzed and tabulated. Utilizing the on-design performance and compressor map graphical interpolation, the steady-state operating line is then determined. Using this information, a performance envelope is developed.
Throughout the analysis, fuel-air ratio is assumed to be much less than 1.0 and
calorically perfect gas is assumed.The Engine Control System (ECS) prevents compressor ratios higher than 19, shaft RPM’s greater than 660000, and burner exit temperatures higher than 1800K.
Nuclear-Ramjet Flight Vehicle with Magnetohydrodynamics
This report discusses a conceptual nuclear-powered ramjet based on the Tory-IIC engine. The inlet is designed as a two-dimensional external deceleration/internal inlet with full mass capture (shock on cowl lip) at design conditions. The inducted air stream, once through the oblique shock cancellation then enters the MHD generator passage in which applied magnetic and electric fields are used to provide electric power to vehicle subsystems (telemetry, control, scientific instruments, etc.) The propellant then passes through a converging-diverging duct. A normal shock is located at the physical throat of this duct to obtain subsonic flow. The flow then enters the nuclear reactor passages, a series of very high aspect ratio rectangular passages. In the reactor, the air is heated by the convection of heat from the passage walls. After the reactor, the heated air then exits the vehicle through a conventional converging-diverging nozzle which expands the flow to the cross-sectional area of the main fuselage.