论文部分内容阅读
以亚声速翼身融合无人机概念设计阶段多学科设计优化为应用背景,提出了考虑操纵面偏转的参数化建模与气动分析方法:1)采用CST方法、CATIA二次开发技术建立操纵面未偏转和偏转构型的三维几何外形;2)采用Tcl语言编制具有容错能力的Gridgen脚本,划分网格;3)采用位流分析和工程方法计算气动特性参数。通过iSIGHT软件集成上述步骤,建立了自动化的计算环境,对某无人机进行了建模和气动分析,风洞试验验证表明方法满足概念设计阶段的精度要求。
Based on the multi-disciplinary design and optimization of conceptual design phase of subwoofer fuselage fusion UAV, a parametric modeling and aerodynamic analysis method considering the control surface deflection is proposed. 1) The CST method and CATIA secondary development technology are used to establish the control surface Undeflected and deflected configurations; 2) Gridgen script with fault tolerance in Tcl language for meshing; and 3) Bit-flow analysis and engineering methods to calculate aerodynamic parameters. The iSIGHT software integrates the above steps to establish an automated computing environment. The UAV is modeled and aerodynamically analyzed. The wind tunnel test shows that the method meets the accuracy requirements in the conceptual design stage.