Performance of ducted rocket with typical fuel rich propellant

Performance prediction model of ducted rocket was developed based on thermodynamic calculation. Research on performance characteristics of ducted rocket with three kinds of fuel rich propellants was conducted. The study shows that under the same height and Mach number, as excess air coefficient increases, inlet stability margin increases and thrust coefficient decreases, while specific impulse increases first and then decreases. Under the same height and excess air coefficient, as incoming Mach number increases, the inlet stability margin increases, while thrust coefficient and specific impulse decrease. Under the same incoming Mach number and excess air coefficient, the changes of inlet stability margin, thrust coefficient, and specific impulse caused by height variation are not obvious. The variations of characteristic velocity and ducted rocket performances are obvious with the increasing of air total temperature, which should not be neglected in performance analysis. Compared with hydrocarbon fuel rich propellant and aluminum magnesium fuel rich propellant, boron based fuel rich propellant has moderate equivalent air-fuel ratio, higher specific impulse, and higher density, which revealings advantages in engineering application.