Rapid Simulation on Torpedo-Rocket Separation Based on the Aerodynamic Surrogate Model

Due to compact structure layout of a rocket-assisted torpedo, rapid torpedo-rocket separation process, and complex aerodynamic interference, the multi-body interference is easy to occur in the separation process. In the design of the rocket-assisted torpedo, the torpedo-rocket separation technology is crucial. The torpedo-rocket separation design is an iterative optimization process for multiple parameters and operating conditions, however the existing wind tunnel test method and numerical simulation method do not satisfy the requirement of huge and fast calculation. In this paper, a co-simulation method based on the aerodynamic surrogate model and the virtual prototype model is proposed. In this method, the key factors affecting the aerodynamic force are extracted, the sample database of input and output is obtained through test or numerical calculation, and an aerodynamic surrogate model with high approximation and prediction accuracy is established using radial basis neural network. Combined with the multi-body dynamic virtual prototype model of rocket-assisted torpedo, this method can be used to quickly predict the separation process and analyze the influence of each parameter.