Sensing and actuation in a liquid propellant rocket engineEquations describing the conservation of mass, momentum, and energy, and multicomponent transport and chemical reaction in a liquid propellant rocket (LPR) engine are given, along with appropriate boundary conditions. The formulation includes a detailed description of the two-phase (gas/liquid) flow in terms of a moving boundary problem, with droplets and vapor occupying time-dependent subdomains of the LPR chamber. Several sensor and actuator types are considered in detail, and their mathematical descriptions are incorporated into the differential equations and boundary conditions.
Document ID
19920046730
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bentsman, Joseph (NASA Headquarters Washington, DC United States)
Wilcutts, Mark (NASA Headquarters Washington, DC United States)
Pearlstein, Arne J. (Illinois, University Urbana, United States)