燃气发生器身部多学科设计优化

为了探索液体火箭发动机多学科设计优化的一般方法,以液体火箭发动机燃气发生器身部为研究对象,在对其进行面向设计的多学科分析的基础上,建立了燃气发生器身部的多学科优化模型,涉及流动、传热、结构强度3个相互耦合的学科.引入了一种新的多目标方法--物理规划方法处理其中的多目标优化问题,通过类别函数将设计者的偏好转化为优化目标,避免了对各个不同大小和量纲的分目标之间重要性的比较和权衡.优化结果显示,利用多学科设计优化减轻了燃气发生器的质量,改善了原有设计,能够提高发动机的设计水平.

Multidisciplinary design optimization of gas-generator body

To exploit a generic multidisciplinary design optimization(MDO) method on liquid propellant rocket engines,a gas-generator body in a liquid propellant rocket engine was used as the object of this research.Based on the design-oriented multidisciplinary analysis,the multidisciplinary design optimization model of the gas-generator body was constructed.Three coupling disciplines,fluid dynamics,heat transfer and mechanics were included in the MDO model.A new multi-objective method called physical programming was introduced to deal with the multi-objective optimization problem in this research.In physical programming,the objective in the optimization problem reflects the preference of designers through class function,which avoids the balance among objectives with different magnitudes and dimensions.The result shows that the mass of the gas generator was reduced and the original design was improved by multidisciplinary design optimization.Multidisciplinary design optimization can be used to obtain the better design of the whole liquid propellant rocket engines.