Abstract
A computer study for predicting the launcher performance is conducted using a one-dimensional hydrodynamics computer code which introduces an artificial dissipative term into the partial differential equations governing the motion of a compressible fluid and includes van der Waal's equation to consider the real gas effect. A two-stage launcher kinematics of the Pilot Ballistic Range at Kyoto University has been studied experimentally using mainly a microwave reflectometry system under any conditions. And experimental results of launcher performance have been compared with the computational ones. In order to maximize and optimize the performance, the launcher parameters have been investigated and discussed.
