操纵方式对翼伞系统雀降性能的影响  

Influence of maneuvering modes on flared landing performance of parafoil system

作　　者：程杨 仇博文 余莉[1,2] 李岩军[1,2] 曹皓然 CHENG Yang;QIU Bowen;YU Li;LI Yanjun;CAO Haoran(Key Laboratory of Aircraft Environment Control and Life Support,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学飞行器环境控制与生命保障工业和信息化部重点实验室,南京210016 [2]南京航空航天大学航空学院,南京210016

出　　处：《北京航空航天大学学报》2024年第12期3940-3946,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(11972192)。

摘　　要：为获得操纵方式对翼伞系统雀降性能的影响规律,建立了翼伞系统两体9自由度动力学模型,采用龙格库塔法进行了动力学编程计算,系统速度、翼伞及载荷姿态的数值结果和文献规律一致,最大误差为8.2%。开展了分级操纵及操纵速度对翼伞系统雀降性能的影响研究,得到了翼伞最小水平速度、最小垂直速度及最大迎角的变化规律。研究结果表明:一次操纵的雀降性能优于分级操纵;操纵时间过长或过短均会导致垂直速度增加;采用“先快后慢”和“匀速下拉”均能保证良好的雀降性能,操纵速度的选择应同时考虑最小垂直速度及翼伞飞行的稳定性。A two-body 9-degree of freedom(DOF)dynamics model of the parafoil system was established,and the Runge-Kutta method was used for dynamic programming calculation.The numerical results of the system velocities and parafoil and load attitudes were consistent with the results in the literature,and the maximum error was 8.2%.On this basis,the influence of hierarchical maneuvering and maneuvering velocity on the flared landing performance of the parafoil system was investigated.The variations of minimum horizontal velocity,minimum vertical velocity,and maximum angle of attack of parafoil were obtained.The results show that the flared landing performance under one-time maneuvering is better than that under hierarchical maneuvering.If the maneuvering duration is too long or too short,the vertical velocity will increase.Both maneuverings featuring first accelerating and then decelerating and constant velocity can ensure good flared landing performance.The minimum vertical velocity and the flight stability of the parafoil should both be considered in the selection of the maneuvering velocity.

关 键 词：翼伞 雀降性能 9自由度模型 操纵方式 操纵速度 

分 类 号：V224.2[航空宇航科学与技术—飞行器设计]