环帆伞可操纵特性仿真与试验研究  

Numerical and experimental investigation of the steering performance of a ringsail parachute

作　　者：黄云尧 武士轻[2,3] 王永滨 张扬[1,3] HUANG Yunyao;WU Shiqing;WANG Yongbin;ZHANG Yang(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China;Laboratory of Aerospace Entry,Descent and Landing Technology,CASC,Beijing 100094,China)

机构地区：[1]南京航空航天大学航天学院,江苏南京210016 [2]北京空间机电研究所,北京100094 [3]中国航天科技集团有限公司航天进入减速与着陆技术实验室,北京100094

出　　处：《西北工业大学学报》2024年第6期1021-1029,共9页Journal of Northwestern Polytechnical University

基　　金：航天科技集团航天进入减速与着陆技术实验室开放基金(EDL19092128);航空工业气动院重点实验室基金(YL2022XFX0409)资助。

摘　　要：为了研究环帆伞的可操纵特性,采用数值仿真与风洞试验相结合的手段分析了2种不同的操纵方式对环帆伞气动和滑翔性能的影响。第一种操纵方式为通过改变其中1组伞绳长度对环帆伞进行拉偏操作,第二种操纵方式为改变控制伞绳的长度使环帆伞呈收口状。数值仿真采用ALE(arbitrary Lagrangian-Eulerian)流固耦合方法,并进行了相应的风洞试验。结果表明:拉偏操作能够有效地改变环帆伞的阻力系数,且在一定长度范围内,随着拉偏伞绳长度缩短,阻力系数明显减小,同时相较于未经过操纵操作的环帆伞,滑翔比最大提升幅度可达80%以上,具备一定的滑翔能力;收口操作对环帆伞的阻力特征影响较为显著,且控制伞绳长度越小,收口幅度越大,阻力特征越小,但相较于未经过操纵操作的环帆伞,滑翔比最大提升幅度仅为10%左右。风洞试验和数值仿真结果的对比显示,阻力系数和阻力特征曲线的变化趋势基本一致,且两者的相对误差在20%以内,验证了仿真方法的可靠性。In order to investigate the steering performance of the ringsail parachute,the effect of two different steering approaches on the aerodynamic and gliding characteristics of a ringsail parachute is analyzed by using the numerical simulation and wind tunnel test.The first steering approach is to make ringsail parachute drift off course by changing the length of the suspension lines,while the second one is to make ringsail parachute close up by changing the length of the reefing control lines.Numerical simulation is performed using the arbitrary Lagrangian-Eulerian fluid-structure interaction method,and the corresponding wind tunnel test is conducted to compare with the results of numerical simulation.The results show that the first steering approach can effectively change the drag coefficient of the ringsail parachute,i.e.,the drag coefficient is greatly reduced as the length of the suspension lines is shortened,and in the meanwhile,compared with the non-steering ringsail parachute,the improvement of the gliding ratio can be up to 80%,which demonstrates the benefits for the gliding ability;While the second steering approach has an significant impact on the drag characteristics of the ringsail parachute,i.e.,as the length of reefing control lines is shortened,the reefing effect is enhanced and the drag characteristics is reduced,whereas compared with the non-steering ringsail parachute,the improvement of the gliding ratio only reaches up to 10%,which demonstrates that the reefing control has little effect on the gliding performance.Comparison between the results obtained by the wind tunnel test and numerical simulation shows that the trend of drag coefficient and drag characteristic curves are basically consistent,and the relative error between them is within 20%,indicating the reliability of the numerical method.

关 键 词：环帆伞 数值模拟 风洞试验 气动性能 滑翔性能 

分 类 号：V445[航空宇航科学与技术—飞行器设计]