直升机机身气动外形的低阻优化设计  

Low-drag optimization design of aerodynamic shape for helicopter fuselage

作　　者：李杰[1] 徐明[2] 李建波[2] LI Jie XU Ming LI Jian-bo(General Configuration and Aerodynamics Department, Chinese Helicopter Research and Development Institute, Jingdezhen 333001, China National Key Laboratory of Rotorcraft Aeromechanics, NUAA, Nanjing 210016, China)

机构地区：[1]中国直升机设计研究所总体气动室,江西景德镇333001 [2]南京航空航天大学直升机旋翼动力学国家重点实验室,江苏南京210016

出　　处：《飞行力学》2016年第6期77-81,共5页Flight Dynamics

基　　金：江苏省高校优势学科建设工程资助项目;江苏省普通高校研究生科研创新计划(CXLX13_164)

摘　　要：直升机机身阻力是飞行阻力的主要来源之一,通过对机身外形的优化设计,能够实现直升机的高效低阻飞行。首先,把机身划分为头部、中段和尾梁三段,对其外形轮廓线进行CST参数化表示;其次,采用拉丁超立方法选取试验设计样本点,计算各样本点的阻力系数,构造Kriging代理模型,估计模型预测的精度;最后,选用序列二次规划算法对其进行优化,并对优化后的机身模型进行了风洞试验。通过计算分析可知:所建立的Kriging代理模型能够精确预测阻力系数值,优化后得到了机身的设计参数;机身阻力系数减小了15.3%,理论值与试验值吻合良好。Helicopter fuselage drag was one of the flight drag source,high efficient and low drag flight of helicopter was realized through the optimization design of the fuselage shape. First,fuselage was divided into three sections： fuselage head,middle and tail beam,outline profile was parameterized by class shape transformation（ CST）. Secondly,the Latin hypercube method was used to select experimental design sample points,drag coefficients of sample points was calculated,Kriging agent model was built and precision of agent model prediction was estimated. Finally,the sequential quadratic programming algorithm was used for its optimization,and wind tunnel test was conducted for optimized fuselage model. Through calculation and analysis,Kriging agent model can accurately predict drag coefficient value,get the fuselage design parameters after optimization,and the fuselage drag coefficient decreases by 15. 3%,theoretical values are consistent with experimental values.

关 键 词：直升机机身 气动外形 CST方法 优化设计 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]