The Modeling And Simulation Of The Process Of Casting Radoms Of Rocket

The process of casting nose cap is very important to rockets and spacecraft. To avoid the collision between the nose cap and rockets during the casting process, which may damage the rocket, the trajectory of both the rocket and nose cap must be calculated. In this paper, the dynamics model of casting rocket nose cap was established. The hinge separating procedure of nose cap is analyzed. The dynamics of the three-rigid-body system (before the nose cap seceding form the rocket) are derived. By solving the equations, the status of the nose cap and rocket, the force int the hinge and the disturbance of the rocket are determined. The article gives the method for engineering calculation of the aerodynamic loads in the separating course ,the way to judge whether the node cap will collide with the rocket or not, and the means to design the quantity of explosive in the catapult separator. The numerical method is applied to a model of missile's separating procedure, the necessary angular velocity and rocket's disturbance are obtained.The key problems was solved properly in this paper, which including: multi-body dynamics modeling of the system of rocket and nose cap, the aerodynamics of nose cap, the method to analysis if the rocket can collide with the nose cap and the angler velocity to avoid the collision was got.