An Approach of the Concurrent Solid Rocket Motor, Aerodynamic Shape, and System Design of Multi-Stage Solid Rocket

摘要

The main task of the preliminary design of the multi-stage solid rocket is to find the optimal design parameters, which satisfy the tactic-technical specifications and the constraint conditions optimally. At present the system design of the rocket inherits the traditional design method, i.e., the optimal design of the whole system and the subsystem is done separately. The optimal design of the system, the engine and the aerodynamic shape is also done separately. This method affects the liquid rocket relatively little, but to the solid rocket, the system, solid rocket motor (SRM) and the aerodynamic shape interact each other very heavily. For this sake, the optimal design of them simultaneously is necessary. In this paper the optimal design of the system, the SRM and the aerodynamic shape simultaneously was done. After comparison, the minimum takeoff mass (m_(01)) of the rockets is chosen as the object function. To calculate the object function, the mass model of solid rockets is established, it is relative to the model of system, SRM and aerodynamic, etc. Then the SRM model is established. At the process of the preliminary design, to predict the performance of the SRM correctly, the calculation of the internal ballistic must take into account the erosion of the throat of the nozzle, the efficiency of the combustion and the nozzle. In this paper the pressure of the combustor is calculated with the zero dimensional balanced pressure equation, and then the pressure of the combustor with erosion combustion is gotten by multiply the result with the ratio of the pressure.