一种自适应机翼柔性后缘拓扑优化技术研究
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- 英文论文题名：Topological Optimal Design Method of Adaptive Compliant Trailing Edge
- 论文作者：王志刚 ; 段世慧
- 英文论文作者：Wang Zhigang ; Duan Shihui ; Aircraft Strength Research Institute of China
- 年：2016
- 作者机构：中国飞机强度研究所;
- 论文关键词：自适应机翼柔性后缘 ; 变形控制 ; 拓扑优化
- 英文论文关键词：adaptive compliant trailing edge ; shape control ; topological optimal design method
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V224
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：5
- 文件大小：831k
- 原文格式：O
- 会议级别：全国
摘要
本文介绍了一种自适应柔性机翼后缘变形控制的方法。该方法中采用了由单个驱动器驱动的分布式柔性结构。该方法的关键问题在于设计一种合适的柔性后缘拓扑形式,使该自适应柔性机翼后缘能够达到精确的变形。文中阐明了柔性结构拓扑优化设计的数学模型,针对自适应柔性机翼后缘概念设计提出了基于变密度法的拓扑优化设计方案。通过一个算例分析了驱动点位置和边界约束等因素对拓扑优化结果的影响。
The research proposes a kind of topological optimal design method to design the main load-bearing structure of adaptive compliant trailing edge.This approach uses a special class of mechanisms called compliant mechanisms powered by a single input actuator.The key design issue in this approach is the synthesis of a suitable compliant mechanism for the task.In order to implement this scheme,a topological optimal design procedure for such compliant mechanisms is presented.During the topology procedure variable density method is introduced.The influence of objection and the boundary of finite element is considered.
The research proposes a kind of topological optimal design method to design the main load-bearing structure of adaptive compliant trailing edge.This approach uses a special class of mechanisms called compliant mechanisms powered by a single input actuator.The key design issue in this approach is the synthesis of a suitable compliant mechanism for the task.In order to implement this scheme,a topological optimal design procedure for such compliant mechanisms is presented.During the topology procedure variable density method is introduced.The influence of objection and the boundary of finite element is considered.
引文
[1]Laxminarayana Saggere and Sridhar Kota.Static Shape Control of Smart Structures Using Compliant Mechanisms.AIAA Journal,1999,37(5):572-578.
[2]Sridhar Kota.Compliant Systems Using Monolithic Mechanisms.Smart Materials Bulletin,2001,39(5):7-10.
[3]Sridhar Kota,Joel Hetrick,Russell Osborn,et al.Design and Application of Compliant Mechanisms for Morphing Aircraft Structures.Smart Structures and Materials,2003,5054;24-33.
[4]Joel A Hetrick,Russell F Osbor,Sridhar Kota,et al.Flight Testing of Mission Adaptive Compliant Wing[C].48th AIAA/ASME/ASCE/AHS/ASC,Structures,Structural Dynamics,and Materials Conference,Honolulu,Hawaii,2007.
[5]朱鹏刚,葛文杰,张永红,赵飞.基于SIMP和GA变形柔性机翼后缘的拓扑优化[J].机械科学与技术,2009,28(11):1468-1472.
[6]黄杰,葛文杰.基于变密度法的形状变化全柔性机构设计及实验研究[J].航空兵器,2009,2:39-42.
[7]陈建超,张永红。葛文杰,景藜.基于多材料组合的柔性机翼前缘拓扑优化[J].机械设计,2011,28(6):61-66.
[8]葛文杰.朱鹏刚,刘世丽,张永红.基于柔性机构的机翼前缘变形多目标优化[J].西北工业大学学报,2010,28(2):211-216.
[9]张龙,王和平,葛文杰,赵飞.基于柔性翼肋的变形机翼几何参数设计[J].航空计算技术,2009,39(1):1-5.
[2]Sridhar Kota.Compliant Systems Using Monolithic Mechanisms.Smart Materials Bulletin,2001,39(5):7-10.
[3]Sridhar Kota,Joel Hetrick,Russell Osborn,et al.Design and Application of Compliant Mechanisms for Morphing Aircraft Structures.Smart Structures and Materials,2003,5054;24-33.
[4]Joel A Hetrick,Russell F Osbor,Sridhar Kota,et al.Flight Testing of Mission Adaptive Compliant Wing[C].48th AIAA/ASME/ASCE/AHS/ASC,Structures,Structural Dynamics,and Materials Conference,Honolulu,Hawaii,2007.
[5]朱鹏刚,葛文杰,张永红,赵飞.基于SIMP和GA变形柔性机翼后缘的拓扑优化[J].机械科学与技术,2009,28(11):1468-1472.
[6]黄杰,葛文杰.基于变密度法的形状变化全柔性机构设计及实验研究[J].航空兵器,2009,2:39-42.
[7]陈建超,张永红。葛文杰,景藜.基于多材料组合的柔性机翼前缘拓扑优化[J].机械设计,2011,28(6):61-66.
[8]葛文杰.朱鹏刚,刘世丽,张永红.基于柔性机构的机翼前缘变形多目标优化[J].西北工业大学学报,2010,28(2):211-216.
[9]张龙,王和平,葛文杰,赵飞.基于柔性翼肋的变形机翼几何参数设计[J].航空计算技术,2009,39(1):1-5.