火星盘缝带伞超声速风洞试验结果分析  

Analysis of Supersonic Wind Tunnel Test Results of Mars Disk-Gap-Band Parachute

作　　者：黄明星[1] 王文强[1] 李健[1] 王立武[1] HUANG Ming-xing;WANG Wen-qiang;LI Jian;WANG Li-wu(Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China)

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《宇航学报》2021年第9期1178-1186,共9页Journal of Astronautics

摘　　要：为了研究盘缝带(DGB)伞在超声速条件下的阻力特性、摆动角以及伞绳载荷分布的不均匀性,在FD-12风洞中开展了盘缝带伞的阻力特性风洞试验,并通过安装柔性传感器测量了伞绳所受载荷。试验结果表明,在Ma 1.50到Ma 2.50来流条件下,盘缝带伞的阻力系数随着马赫数的增大先增加后减小,在Ma 1.75时达到最大,为0.60,而最大摆动角则是先减小后增大,在Ma 2.00时摆动角最小,为7.4°,传感器的安装对降落伞风洞试验结果影响很小。通过柔性传感器的标定和误差分析,获取了伞绳载荷数据,结果显示不同伞绳所受拉力的比值可达到1.98。且传感器数据与风洞天平的测量降落伞总载荷结果吻合,进一步验证了柔性传感器结果的正确性。In order to study the drag characteristics,oscillation angle,and the non-uniform suspension line load distribution of disk-gap-band(DGB)parachute under supersonic condition,the wind tunnel test of the DGB parachute drag characteristics is carried out in the FD-12 wind tunnel,and the load of suspension lines is measured by the flexible sensors.The experimental results show that under the condition of the Mach number increasing from Ma 1.50 to Ma 2.50,the drag coefficient of the DGB parachute increases first and then decreases,and reaches the maximum of 0.60 at Ma 1.75,while the maximum oscillation angle decreases first and then increases,and the oscillation angle reaches the minimum value of 7.4°at Ma 2.00.The installation of the sensor has little effect on the wind tunnel test results of the parachute.Through the calibration and error analysis of the flexible sensor,the load data of the suspension lines is obtained,and the conclusions reflect that the ratio of load on different parachute suspension lines can reach 1.98.The total parachute load obtained from the sensor data is matched with the measurement data of the wind tunnel balance well,which further verifies the correctness of the flexible sensor results.

关 键 词：盘缝带伞 超声速 风洞试验 柔性传感器 阻力系数 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]