多场载荷作用下舵面蒙皮响应分析

摘要

试验研究表明,导弹舵面在工作环境中承受严酷的气动力载荷、气动热载荷和噪声载荷.多种载荷相互影响使舵面产生剧烈振动,严重影响打击精度;甚至导致蒙皮开裂引起疲劳失效.以某型号导弹C/SiC复合材料舵面蒙皮为研究对象,基于WORKBENCH/VA-ONE程序平台,将自定义函数(UDF)建立的热流固耦有限元控制方程和边界元声场控制方程相结合,推导出改进的耦合边界元/有限元法(BEM/FEM)计算模型.通过此方法数值模拟导弹真实飞行环境,计算出了蒙皮表面危险点位置和不同飞行环境下响应特性;结果表明,通过改进的耦合BEM/FEM计算模型,能够较准确地反应导弹在真实飞行环境下舵面蒙皮响应特性随环境变化特征,为导弹舵面可靠性设计提供了一种有效的数值计算方法.%The experiment study have shown that missile rudder is being in a extremely harsh environment of aerodynamic loads, thermal loads, acoustic and others during working.A variety of loads interfere with each other to violent vibration of the rudder, and seriously effect the missile attacking accuracy, even lead to fatigue failure caused by skin cracking.A model of missile rudder is took as the research object, combined finite element control equation established by user-defined functions (UDF) for thermal-fluid-structure coupling and boundary element control equation for sound field, the improved coupling BEM/FEM calculation model can be deduced, to simulate the real flying environment of missile.The danger point of rudder and the response characteristics of rudder varia-tions of flying environment were obtained.The results show that the improved coupling BEM/FEM calculation mod-el can reflect accurately the response characteristics of rudder in real flying environment, and it provided an effec-tive numerical computation method for the reliability design of missile rudder.