Engineering Method Of Solid Rocket Ramjet Engine Design And Performance Analysis

ISRPR (Integral Solid Rocket Propellant Ramjet) is a novel kind of propulsive system, which is composed of solid rocket and ramjet. It has advantages in compact structure, high specific impulse and convenient manipulation. The solid rocket ramjet propulsion system is competent for the future missile which works in wide range and under high Mach number. The research is still important and elusive in this field.The paper illuminates the differences among the three kinds of ISRPR and 1-D engineering calculation method which is used to predict the performance of ISRPR. is established The important research is the choking SRPR in which propellant flux can be adjusted, and numerical stimulation is fulfilled. The effects of selection of the rectangle supersonic inlet design point on the SRPR performance are presented and off-design performances of SRPR are predicted. The results indicate that selection of sub critical engine inlet as design point can obviously improve engine performance for high Mach number. However, sub critical inlet design point not only reduces engine performance but also shortens inlet stability working range when engine works under low supersonic flight conditions. By comparisons, the inlet supercritical design shows obvious superiority. By using inlet supercritical condition as design-point, the effect of incidence on SRPR primary performance is analyzed and the effect rule of propellant pressure index and air-fuel ratio to gas generator exhaust pipe throat area is also discussed. The result indicates propellant in higher pressure index is propitious to the modulation of propellant flux. However, owing to the constraint of gas generator exhaust pipe throat maneuverable range, bigger air-fuel ratio is applied in low-altitude flight; otherwise, less air-fuel ratio is used in high-altitude flight. Based on the example of governing equation of missile in the vertical plain, the horizontal flight law is analyzed in the flux-changeable choking engine as power unit missile, the effects of different boost mass on missile horizontal flight distance when engine total propellant mass is kept as constant, and the effects of along with different air-fuel ratio on missile horizontal flight acceleration and flight distance under the same flight height, are calculated and analyzed. In addition, from the respect of residue thrust, the...