Scramjet Wall Thickness Optimization

Today supersonic combustion ramjet technology is the focus of research in the world, it directly reflects the technological level of a country’s technological level, it has be a important criteria to measure a country’s scientific and technological level.Supersonic combustion ramjet is referred to scramjet. The research of scramjet aimed to study the supersonic combustion ramjet technology with the Mach number greater than 6. For half a century, it has been great importance to study the United States, Russia, France and other countries. Currently, the scramjet technology has begun flight demonstration. Scramjet technology will be rapid development and practical application and definitely have a profound impact on the future of the military, political and economic in 21st century.Pneumatic thermal and structural heat generated hypersonic vehicle during flight conduction problems, is a multi-physics coupling including questions on flow field, temperature field and structure field. Scramjet highest internal wall surface temperature can reach 1400K-1600K, so the choice of materials must be able to withstand high temperature,high pressure and high strength. Of course, with the premise of normal operation, we should reduce the quality of scramjet as far as possible by arranging material distribution, improving performance and saving material.Firstly, we establish the finite element model for a certain type of scramjet in this paper by the finite element software Patran and give the initial heat flux and the initial temperature. Under the assumption that the engine is running 10s were transient temperature field analysis and structural analysis based on thermosetting coupled heat transfer theory. Then using the integrated optimization software isight integrates patran/nastran and matlab with associating a wall thickness with element nodes location using matlab programming. Finally,we optimize the wall thickness of the scramjet engine with the optimization method in the software isight to reduce engine weight and eliminate unnecessary material with meeting the requirements of the material ultimate stress and deformation conditions.