平流层飞艇气动特性相似缩比分析与风洞试验  

Scaled similarity analysis of aerodynamic characteristics and wind tunnel test for stratospheric airship

作　　者：史智广 左宗玉[1] 杨玉洁 SHI Zhiguang;ZUO Zongyu;YANG Yujie(School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China;Beijing Near Space Airship Technology Development Co.Ltd,Beijing 100070,China)

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京临近空间飞艇技术开发有限公司,北京100070

出　　处：《国防科技大学学报》2023年第6期40-47,共8页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(62073019)。

摘　　要：阐述了平流层飞艇气动特性天地相似缩比分析设计方法,给出了刚体模型与柔性体模型完成风洞试验需满足的相似准则数,并指导完成两类缩比模型研制及风洞试验。通过对两类缩比模型风洞试验数据的分析,发现平流层飞艇不同充气内压下气动特性规律基本一致,但较刚体模型有明显的差异;柔性特征下的气动阻力系数明显高于刚体,在零攻角状态下甚至高出一倍,引发滚转气动力矩特性出现稳定与发散的本质变化。这对平流层飞艇特别是低压保形下的柔性气动特性评估,克服现有采用刚体气动特性数据或工程估算方法进行“动阻平衡”飞艇总体设计存在较大偏差的弊端,具有重要工程应用价值。The analysis and design method of the sky-ground scaled similarity of aerodynamic characteristics for stratospheric airship were described in detail.The similarity criteria for the rigid and flexible models to complete the wind tunnel tests were given.Two kind of scaled models and wind tunnel test were completed.By analyzing the wind tunnel experimental data for scaled models,it was found that the aerodynamic characteristics of the stratospheric airship under different inflatable internal pressures were basically same,but the rigid body model was obviously different.The aerodynamic drag coefficient under flexible characteristics was significantly higher than that of rigid body,and even twice as high as that under zero attack angle,which lead to the essential changes of the rolling aerodynamic torque characteristics,such as stability and divergence.It has important engineering application value for evaluating flexible aerodynamic characteristics of stratospheric airship,especially under low pressure state.And it overcomes the disadvantages of using rigid body aerodynamic characteristics data or engineering estimation method in the airship overall design of"dynamic-resistance balance".

关 键 词：相似性 气动特性 风洞试验 平流层飞艇 缩比模型 

分 类 号：V211.54[航空宇航科学与技术—航空宇航推进理论与工程]