고체로켓모터 노즐의 통합 열전달 해석 모델링

초록

Solid rocket motor is generated a thrust by ejected high temperature and pressure gas through a nozzle. TPS(Thermal protection system) was designed for protecting the structure, nozzle etc from the gas. TPS are designed by using the carbon based phenolic composite. The composite is decomposed at high temperature and generate a gas that is ejected through the wall and prevent a heat from the combustion gas. And the wall is ablated by combustion gas and changed cross-sectional area. The changed area is affect rocket performance. Therefore, in this study, flow, decomposition, ablation, and heat analysis are coupled and predicted. the flow and convection is calculated by isentropic relation, and Gauss-Newton method is used to solve the non-linear energy and density conservation equation. The result using coupled analysis is comparable to experiment result.