CALCULATION OF THE EXPANSION PROCESS OF THE FLOW OF WORKING BODY IN THE NOZZLE OF A LIQUID-PHASE NUCLEAR ROCKET ENGINE

In this work, flow parameters of the working body (hydrogen) were calculated at the inlet, throat, and exit sections of the liquid-phase nuclear rocket engine nozzle. A method was proposed for determining the specific impulse of thrust while accounting for losses due to scattering, friction, and variations in the specific enthalpy of the working body caused by non-adiabatic effects. The calculated specific impulse exceeded 9500 m/s, significantly surpassing the performance of chemical rocket engines. The evaluation of the thermogasdynamic parameters of the working body expansion confirmed the high efficiency of the liquid-phase nuclear rocket engine and its feasibility for space missions.