Análise de um veículo lançador de microssatélites através de modelo computacional

Abstract

Due to the growing demand for suborbital launches, fueled by the purpose of having self-sufficiency in sending satellites into space, the Brazilian Space Program has advanced in the development and production of satellite launch vehicles. Even with such an evolution and being intrinsically complex designs, the works available in the literature on this vehicle are still scarce, a factor that limits their total understanding. This work aims to develop a numerical calculation methodology for the design of a microsatellite launch vehicle (MLV) to predict the structural behavior to the MLV fairing using the finite element method (FEM). To this end, the distribution of absolute pressure was provided, using computational fluid dynamics, along the fairing based on the mandatory flight loads. Then, a structural model using the FEM was developed to predict buckling (collapse) and failure and damage to the MLV fairing material subjected to external pressure. The laminate that composes this structure was modeled with layers of carbon fiber / epoxy and glass fiber / epoxy composites, in addition to having aluminum layers. Thus, a sensitivity study was conducted where the ef-fects of three different stacking sequences of the composite were investigated, [± 28 / 0 / 0]s, [90 / ± 554 / 90] and [± 655], on the behavior of the fairing collapse and also a failure and damage to the composite material that makes up the component. With the results, a calculation methodology for buckling and failure in the fairing of the microsatellite launch vehicle was successful.