Rbcc Rocket And Combustion Chamber Heat Protection Analysis And Testing,

During the study of Rocket Based Combined Cycle (RBCC), thermal protection is a serious problem, which cannot be ignored. It is important to establish heat transfer model of rocket and engine flowpath. Actively cooled refractory composite panel was investigated in this paper from experimental and theoretical aspects.An heat transfer model of rocket, which including a comprehensive adaptability radiation heat transfer model, was established. Complexity of real gas radiation was considered in the radiation heat transfer model. The rocket heat transfer model which is coupled with radiation, heat convection and heat conduction, was established by experiential equation. Wall temperature and heat flux were calculated in the condition of different wall material, wall thickness, mass flux of coolant and border area cooling.A one dimension transient heat transfer model of composite structure, which could simulate the temperature of multi-layer structure constituted by different material, was established. The governing equation was one dimension transient heat conduction differential equation, and the boundary condition was heat convection or adiabatic. Finite volume method was used for governing equation, and discretization equation was solved by Gauss-Seidel iteration. Several design factors, such as wall material, lib material, thickness of wall, were calculated. The results show that coolant taken with ceramic matrix composite (CMC) was more less than it taken with general materiel.Actively cooled and passively cooled refractory composite panel were designed, and experimented with RBCC rocket ejector experimental system. A solid rocket motor which can supply high temperature gas above 3000K was improved for the experiment. Interior temperature on interface was measured in test. The result showed that temperature field was appropriately predicted and RBCC combustion chamber wall was effectively cooled by composite structure with CMC panel.