In view of exterior ballistics and flight principle, a full six degree-of-freedomrigid-projectile model is employed. The computational flight analysis takes into considerationthe Earth’s rotation, Magnus and the wind effect. Moreover, the standard atmospheric modelthat simulates the air density and sound speed is presented. During the trajectorycomputation, the aerodynamics variations are calculated by means of variable aerodynamiccoefficients. The RUNGE-KUTTA method is obtained for the numerical integration. Thesimulation results show some differences in the projectile flight trajectory after taking intoconsideration both of the wind and Earth’s rotation effect. The wind mainly affects the crossrange and the Earth’s rotation mainly on the deflection angle, making the flight trajectorysimulation more accurate. In addition, an investigation on the range extension capabilityusing the rocket assist is presented.
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