Method for the propellant-optimal regulation of a nozzle assembly

摘要

The method for optimum fuel feed for a space vehicle motor nozzle involves finding an optimum fuel feed solution for the resolution of a linear optimization problem. It involves an initialization phase to find a first solution for the linear optimization problem and a following iteration phase for producing an iterative optimization of a correction criterion. A scaled iteration gradient is produced for each iteration stage and a limiting factor is used for a maximum iteration stage width.