Aerospace Science and Industry Corporation

Beijing 100074

China)Abstract：An integral model of gas generator/solid propellant ducted rocket/missile was established

and typical performance parameters in the typical trajectory were obtained by simulation. Results showed that

in the climbing and cruising phases

the relative error of the fuel mass flow rate and the thrust of the engine was less than 7%. But in the diving phase

due to the free volume effect

the relative error of the fuel mass flow rate was -30%

and the error of thrust was -50% correspondingly. However

the relative errors of flight velocity and flight range were less than 5% and 1% respectively. Therefore

for this typical climbcruisediving flight trajectory described

the dynamic characteristics of gas generator can be ignored in analysis of the missiles working process.