摘要
根据柔性机翼前缘的变形要求,以离散体结构拓扑优化为出发点,以实际位移与目标位移之间的偏差为目标,建立目标优化函数。采用类树形结构的载荷路径建立初始构形,利用遗传算法(GA)进行结构拓扑优化,并结合拓扑结构优化结果进行二次优化,获得更优解。通过ANSYS仿真分析,结果表明该方法是可行的。
To meet the requirements for the changes in the shape of the leading edge of a compliant wing, we set up the objective optimization function, starting from the topological optimization of a discrete structure and aiming at minimizing the deformation between deformed shape and target shape. We employ the load path of a similar tree structure to build the initial configuration of the leading edge and the genetic algorithm to optimize its topology. Taking the topological optimization results into consideration, we perform the quadratic optimization to find the opti- mal solution. The ANSYS simulation results show that our method is feasible.
出处
《机械科学与技术》
CSCD
北大核心
2013年第7期987-990,共4页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(50675175)
高等学校博士学科点专项科研基金项目(20096102110017)资助
关键词
柔性机翼
树形结构
载荷路径
遗传算法
拓扑优化
computer simulation
computer software
design
genetic algorithms
optimization
topology
wings
compliant wing
similar tree structure
load path
