Abstract

The dynamics of nuclear rocket engines is studied, with attention to integral temperature error feedback control of reactivity and proportional pressure error feedback control of propellant flow with first order lags placed between the desired controller positions and the actual positions. The resulting series of ordinary, nonlinear differential equations are approximated by a linear model in order to analyze the low-frequency dynamics. It is shown that the low and high frequencies may be decoupled and that the proposed method of control is stable for small variations away from any point of steady-state operation. Algebraic equations, in terms of design parameters, are derived for control settings that yield optimum response characteristics. It is further shown that the asymptotic response is improved by reduction of the mechanical inertia of the turbopump but is independent of the thermal inertia of the core. The analysis is corroborated by analog simulation of the nonlinear model for the case of lowpower- -high-power transition, using only feedback control for flow and reactivity variation. (auth)

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call

Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.