Numerical simulation of the detaching process for rocket mantles in low altitude

Using dynamic unstructured grid technology combined by spring analogy and local remeshing, the Euler equation coupled with 6DOF trajectory equations was solved. Solutions were advanced in time by a four-stage Runge-Kutta time-stepping scheme. The flow solver was an improved implementation of Barth and Jespersen's unstructured schemes. The mantles detaching process of rocket with rocket-based combined-cycle(RBCC) inside was simulated numerically under the conditions of supersonic aviation in low altitude. The results show that high dynamic pressure can cause aerodynamic disturbance in course of mantles unbolting and releasing. After mantles breaking away, the aerodynamic force is several orders of magnitude greater than the inertia force. Mantles trajectory is absolutely controlled by the aerodynamic force and the mantle statement changes violently. This may cause great risk. The detaching project of the mantle's centroid moving backwards is feasible.