Aiming at the difficult separation and complex flow interference problems of nose cover separation under low dynamic pressure of aircraft,this paper designs a scheme for nose cover separation using a booster rocket,and uses a numerical simulation method to couple N-S equations based on dynamic nested grids and a rigid body six-degree-of-freedom equations.To carry out nose cover separation simulation research on three different separation rocket placement positions on the head cover separation model.The research results show that the confluence of the separation rocket jets on both sides in the lower section of the nose cover interior during the initial stage of the nose cover separation will cause the left and right flap covers to overturn.By adjusting the longitudinal position of the separation rocket,the degree of overturning of the left and right flap covers in the initial stage of separation can be effectively reduced,and finally the successful separation of the flap cover from the projectile body is achieved.
关键词
火箭助推头罩分离/刚体六自由度/嵌套网格/流动干扰/数值仿真
Key words
rocket booster hood separation/rigid body six degrees of freedom/nested grid/flow interference/numerical simulation
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