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.