摘要
翼伞的气动力计算是研究翼伞回收系统建模的关键技术问题。为了进一步提高建模精度,同时考虑了翼伞充气变形和后缘下偏量的影响,通过流固耦合方法获得各个状态下的升力系数、阻力系数。然后使用最小二乘法辨识获得气动系数和下偏量及变形之间的量化关系,改进翼伞回收系统的六自由度模型。研究表明,考虑变形及下偏情况的翼伞不仅结构和实际翼伞类似,且获得的气动参数与风洞试验更加接近,证明新方法对于翼伞回收系统精确建模的研究有一定的意义。
The aerodynamic calculation of parafoil is the key technology of the parafoil recovery system modeling.In order to further improve the model accuracy,the lift coefficient and drag coefficient under the various states are ob⁃tained via fluid structure coupling method by considering the influence of the aerodynamic deformation and trailing edge deviation.Then,the least square method is used to identify the quantitative relationship among the aerodynam⁃ic coefficient,deflection,and deformation so as to improve the 6⁃DOF parafoil recovery system model.The results show that the structure of parafoil considering deformation and deflection is not only similar to the actual parafoil,but also the obtained aerodynamic parameters are more close to the wind tunnel test,which proves that the present method has certain significance for precisely modeling the parafoil recovery system.
作者
郭一鸣
闫建国
邢小军
吴慈航
陈潇然
李丰浩
GUO Yiming;YAN Jianguo;XING Xiaojun;WU Cihang;CHEN Xiaoran;LI Fenghao(School of Automation,Northwestern Polytechnical University,Xi′an 710072,China)
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2020年第5期952-958,共7页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(61771399)
陕西省自然科学基金(2020JM⁃123)资助。
关键词
翼伞
流固耦合
后缘下偏
充气变形
动力学模型
parafoil
fluid structure coupling
trailing edge deflection
inflatable deformation
dynamic model
