DSMC 해석기법을 이용한 희박유동 환경에서의 발사체 Orbital Block 공력특성 예측

PREDICTION OF THE AERODYNAMIC CHARACTERISTICS OF AN ORBITAL BLOCK OF A LAUNCH VEHICLE IN THE RAREFIED FLOW REGIME USING DSMC APPROACH

The aerodynamic coefficients of Apollo capsule are calculated using a DSMC solver, SMILE, and the results agree very well with the data predicted by NASA. The aerodynamic characteristics of an orbital block which operates at high altitudes in the free molecule regime are also predicted. For the nominal flow conditions, the predicted aerodynamic force is very small since the dynamic pressure is extremely low. And the additional aerodynamic coefficients for the analysis of the attitude control are presented as the angle of attack and the side slip angle vary from $+45^{\circ}\;to\;-45^{\circ}$ of the nominal angle.