Study on theoretical performance of solid ducted rocket based on thermodynamic calculation
Analysis of flux-adjustable and ramjet-nozzle-adjustable solid ducted rocket
The characterization of the combustion properties of the aluminum? magnesium fuel? rich propellant for unchoked ducted rocket was studied.
The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated.
Numerical simulation and experimental study of deposition for ducted rockets
