涡环旋转伞充气过程及气动特性分析

doi:10.3969/j.issn.1000-1093.2015.08.006

兵工学报 ›› 2015, Vol. 36 ›› Issue (8): 1411-1416.doi: 10.3969/j.issn.1000-1093.2015.08.006

涡环旋转伞充气过程及气动特性分析

马晓冬，郭锐，刘荣忠，吕胜涛

(南京理工大学智能弹药技术国防重点学科实验室，江苏南京 210094)

收稿日期:2014-12-05 修回日期:2014-12-05 上线日期:2015-10-16
通讯作者: 马晓冬 E-mail:bqnj6222007@126.com
作者简介:马晓冬(1988—)，男，博士研究生
基金资助:
国家自然科学基金项目（11102088）；江苏省研究生培养创新计划项目（CXLX12_0210)

Analysis of Inflation and Aerodynamic Characteristics of Vortex Ring Parachute

MA Xiao-dong, GUO Rui, LIU Rong-zhong, LYU Sheng-tao

(ZNDY Ministerial Key Laboratory, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China)

Received:2014-12-05 Revised:2014-12-05 Online:2015-10-16
Contact: MA Xiao-dong E-mail:bqnj6222007@126.com

摘要/Abstract

摘要： 为了探索灵巧子弹药的减速导旋伞——涡环旋转伞的充气性能和气动特性，利用任意拉格拉日-欧拉流-固耦合方法，模拟一种典型涡环旋转伞在无限质量和低速气流条件下的充气过程，得到伞衣动态变化过程、转速和投影直径时程变化曲线及充满后稳态下的流场变化特性。将充满伞衣幅的有限元模型转化为气动特性仿真模型，利用计算流体力学方法得到涡环旋转伞在低速气流作用下的气动力参数及流场流线、压力分布等特性。将两种方法得到的结果进行对比分析，结果表明：涡环旋转伞在来流12 m/s时能顺利充气展开并实现旋转，伞衣幅充满外形饱满，稳定转速约为3.3 r/s；阻力系数为1.36，大于一般结构轴对称降落伞；导旋力矩系数为0.87；流场分布具有中心对称性。

关键词: 兵器科学与技术, 涡环旋转伞, 开伞过程, 〖JP9〗流-〖JP〗固耦合, 计算流体力学, 气动特性

Abstract: To explore the inflation performance and aerodynamic characteristics of vortex ring parachute which is often used as decelerating and spinning parachute of smart ammunition, the inflation process under the conditions of infinite mass and slow flow velocity is simulated using arbitrary Lagrange-Euler method. The canopy deforming process, time-history curves of spinning rate and projected diameter and fluid domain features at steady state are obtained. The finite model of inflated canopies is transformed to a simulation model of aerodynamic characteristics. The aerodynamic force parameters, the features of velocity streamlines and the pressure distribution are obtained by using computational fluid dynamics method. The results obtained by the two methods are compared and analyzed. The results show that the vortex ring parachute can inflate smoothly and rotateat 12 m/s. The shape of inflated canopy is plump and the steady spinning rate is about 3.3 r/s. The drag coefficient is about 1.36, which is greater than those of other typical parachutes with axial symmetry structure. The spinning moment coefficient is 0.87. The distributions of fluid domain features are centrally symmetrical around the parachute axis.

Key words: ordnance science and technology, vortex ring parachute, inflation, fluid-structure interaction, computational fluid dynamics, aerodynamic characteristics

中图分类号:

V441.8

马晓冬，郭锐，刘荣忠，吕胜涛. 涡环旋转伞充气过程及气动特性分析[J]. 兵工学报, 2015, 36(8): 1411-1416.

MA Xiao-dong, GUO Rui, LIU Rong-zhong, LYU Sheng-tao. Analysis of Inflation and Aerodynamic Characteristics of Vortex Ring Parachute[J]. Acta Armamentarii, 2015, 36(8): 1411-1416.

参考文献

［1］王利荣. 降落伞理论与应用[M]. 北京：宇航出版社，1997.
WANG Li-rong. The theory and application of parachute [M]. Beijing: China Astronautics Publishing House，1997. (in Chinese)
[2] Ewing E G，Bixbu H W，Knacke T W. Recovery systems design guide, AD A070251[R]. Gardena, CA: Irvin Industries Inc，1978.
[3] Guo R，Liu R Z. Dynamics model of the rigid and flexible coupling system for terminal-sensitive submunition[J]. Journal of China Ordnance，2007，28(1)：10-14.
[4] 殷克功，刘荣忠，徐刚，等. 末敏弹减速伞充气过程有限元方法研究[J]. 系统仿真学报，2009，21(9)：2500-2502.
YIN Ke-gong，LIU Rong-zhong，XU Gang，et al. Research on drag parachute inflation process of target-sensitivity projectile based on finite element method [J]. Journal of System Simulation，2009，21(9)： 2500-2502.(in Chinese)
[5] Yongsam K，Charles S P. 3-D parachute simulation by the immersed boundary method [J].Computers & Fluids，2009，38(6)：1080-1090.
[6] Tutt B，Taylor A P. The use of LS-DYNA to simulate the inflation of a parachute canopy [C]∥18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Munich, Germany: AIAA, 2005.
[7] Tutt B，Charles R，Roland S，et al. Development of parachute simulation techniques in LS-DYNA[C]∥11th International LS-DYNA Users Conference. Dearborn, Michigan,US: LSTC，2010.
[8] 李尧尧，姜春兰. 阻力伞—灵巧子弹系统气动及稳定性研究[J]. 北京理工大学学报，2014，34(8)：785-789.
LI Yao-yao，JIANG Chun-lan. Analysis on the aerodynamic characteristics and the stability of parachute-bomb system[J]. Transactions of Beijing Institute of Technology，2014，34(8)：785- 789.（in Chinese）
[9] 完颜振海，冯顺山，董永香，等. 超音速伞弹流场特性数值分析[J]. 兵工学报，2011，32(5)：520-525.
WANYAN Zhen-hai，FENG Shun-shan，DONG Yong-xiang，et al. Numerical analysis of flow characteristics of supersonic submunition and parachute [J]. Acta Armamentarii，2011，32(5)：520-525.(in Chinese)
[10] 马晓冬，刘荣忠，郭锐，等. 涡环旋转伞系统开伞充气过程仿真研究[J]. 航天返回与遥感，2013，34(2)：1-7.
MA Xiao-dong，LIU Rong-zhong，GUO Rui，et al. Simulation research on inflation of vortex rotating parachute system [J]. Spacecraft Recovery & Remote Sensing，2013，34(2)：1-7. (in Chinese)
[11] Souli M, Ouahsine A，Lewin L. ALE formulation for fluid-structure interaction problems [J]. Computer Methods in Applied Mechanics and Engineering，2000，190：659-675.
[12] Aquelet N，Tutt B. Euler-lagrange coupling for porous parachute canopy analysis [J]. The International Journal of Multiphysics， 2007，1(1)：53-68.
[13] David J B. A mixture theory for contact in multi-material eulerian formulations[J]. Computer Methods in Applied Mechanics and Engineering，1997，140：59 -86.
[14] Aquelet N，Tutt B. Euler-lagrange coupling for porous parachute canopy analysis [J]. The International Journal of Multiphysics，2007，1(1)：53-68.
[15] 郭锐，刘荣忠，胡志鹏，等. 涡环旋转伞开伞稳定性及减速导旋稳定性研究[J]. 空气动力学学报，2013，31(6)：733-738.
GUO Rui，LIU Rong-zhong，HU Zhi-peng，et al. Study on the inflation stability and motional characteristics of vortex ring parachute canopy [J]. Acta Aerodynamica Sinica，2013，31(6)：733-738.(in Chinese)
[16] Weese J H，Chernowitz G. 气动力减速器原理及设计[M]. 回返技术翻译组，译. 北京: 国防工业出版社，1974.
Weese J H，Chernowitz G. Performance of and design criteria for deployable aerodynamic decelerators [M]. Recovery Technology Translation Group,translated. Beijing: National Defense Industry Press，1974. (in Chinese)

[1]	汪泰霖, 王野, 张富毅, 陈慧岩, 王国玉. 水陆两栖车矢量喷口装置设计与仿真[J]. 兵工学报, 2022, 43(4): 826-850.
[2]	朱毅飞, 林德福, 莫雳, 叶建川. 四旋翼无人机旋翼对机身非定常气动干扰特性[J]. 兵工学报, 2022, 43(2): 410-422.
[3]	刘双, 何广华, 王威, 高云. 附体对分层流中潜艇水动力特性的影响[J]. 兵工学报, 2021, 42(1): 108-117.
[4]	徐路程，郝雪颖，肖凯涛，宋伟伟，陈春生. 爆炸型烟幕弹遮蔽效能仿真研究[J]. 兵工学报, 2020, 41(7): 1299-1306.
[5]	钟阳，王良明，吴映锋. 基于计算流体力学与刚体动力学耦合的高速旋转弹丸弹道计算方法[J]. 兵工学报, 2020, 41(6): 1085-1095.
[6]	权辉，谢建，李良，张力. 火箭发射场坪排焰道口射流研究[J]. 兵工学报, 2020, 41(6): 1111-1122.
[7]	王利利，刘影，李达钦，吴钦，王国玉. 固体火箭发动机水下超音速射流数值研究[J]. 兵工学报, 2019, 40(6): 1161-1170.
[8]	郑秋亚，苏宁亚，梁益华. 欧拉方程数值求解的高精度通量分裂方法[J]. 兵工学报, 2019, 40(12): 2545-2550.
[9]	赵欣怡，周克栋，赫雷，陆野，李峻松. 某大口径轻武器射流噪声的小波分析与数值模拟[J]. 兵工学报, 2019, 40(11): 2195-2203.
[10]	张曼曼，姜毅，程李东，杨桦，刘琦. 基于嵌套网格的超声速子母弹分离数值分析[J]. 兵工学报, 2019, 40(1): 79-88.
[11]	娄伟鹏，郑长松，李和言，陈建文，张周立，马源. 高速《Symbol》v湿式换挡离合器排油阀临界开启和关闭压力研究[J]. 兵工学报, 2017, 38(9): 1665-1672.
[12]	王宪成，杨绍卿，马宁，赵文柱. 车辆柴油机缸套动载荷磨损计算模型研究[J]. 兵工学报, 2017, 38(9): 1673-1680.
[13]	孙皓泽，常天庆，王全东，孔德鹏，戴文君. 一种基于分层多尺度卷积特征提取的坦克装甲目标图像检测方法[J]. 兵工学报, 2017, 38(9): 1681-1691.
[14]	张玉燕，孙莎莎，王振春，曹海要，战再吉. 高速载流电枢表面瞬态温度场仿真与测量[J]. 兵工学报, 2017, 38(9): 1692-1698.
[15]	李臣明，宦超，石怀龙. 某箱式火箭炮对面目标分布式杀伤最优火力分配[J]. 兵工学报, 2017, 38(9): 1699-1704.

涡环旋转伞充气过程及气动特性分析

Analysis of Inflation and Aerodynamic Characteristics of Vortex Ring Parachute

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价