摘要
提出了使用基于连续体拓扑优化技术的全柔性机构实现自适应机翼的形状连续变化的设计方法。基于SIMP(solid isotropic material with penalization)密度刚度插值模型,以实际位移与目标位移之间的偏差为目标函数,材料用量为约束,使用优化准则法(OC)对该柔性机构进行了概念设计。对结果进行了边界光顺处理后使用ABS材料加工出了该柔性机构,并进行了形变的试验测试。试验结果表明该柔性机构能够实现预期的形状变化,证明了本文方法的正确性,为基于柔性机构技术的柔性机翼设计提供理论基础。
The fully flexible mechanism based on continuum topology optimum technology is used to achieve the shape changing of the adaptive wing. Based on the solid isotropic material with penalization （SIMP） model and optimality criteria （OC） method, the concept design for the fully flexible mechanism is given with the object function of deviation between the actural shift and the object shift, and with the constraint of material. This flexible mechanism is manufactured with ABS material after treatment to the results, and the tests are made. The experimental results show that the flexible mechanism can achieve the object shape change, and this useful method can provide the theoretical fundation for the flexible wing design based on the flexible mechanism technology.
出处
《航空兵器》
2009年第2期39-42,共4页
Aero Weaponry
基金
国家自然科学基金(50675175)资助项目
关键词
拓扑优化
柔性机构
自适应机翼
形状变化
topology optimization
flexible mechanism
adaptive wing
shape changing
