降落伞火箭撬试验开伞动载计算模型与分析

doi:10.16182/j.issn1004731x.joss.201812010

系统仿真学报 ›› 2018, Vol. 30 ›› Issue (12): 4574-4579.doi: 10.16182/j.issn1004731x.joss.201812010

降落伞火箭撬试验开伞动载计算模型与分析

王从磊

中航工业宏光空降装备有限公司,江苏南京 210022

收稿日期:2018-05-29 修回日期:2018-08-03 出版日期:2018-12-10 发布日期:2019-01-03
作者简介:王从磊(1978-),男,江苏南京,博士,工程师,研究方向为可压缩流动与大变形结构流构耦合的数值模拟,降落伞设计与仿真分析。

Computational Model and Analysis of Parachute’s Opening Load in Rocket Sled Experiments

Wang Conglei

AVIC Hongguang Airborne Equipment Company, Ltd. , Nanjing 210022, China

Received:2018-05-29 Revised:2018-08-03 Online:2018-12-10 Published:2019-01-03

摘要/Abstract

摘要： 采用多体动力学方法并结合质量阻尼弹簧模型,建立了降落伞火箭撬试验中,开伞动载的计算模型。研究表明,模型能够反映出开伞动载在放伞过程中的变化情况,并能准确预测开伞峰值的大小和出现的时刻,与试验结果吻合较好。同时,分析了前置体质量和放伞速度等因素对开伞动载的影响,分析表明,在200~450 km/h的放伞速度范围内,开伞动载峰值随放伞速度的增大而增大,其增加幅度随伞系统阻力特征的增大而增大;前置体质量的增大,会造成开伞峰值的增大,尤其在前置体质量较小的情况下。该研究可为降落伞系统设计提供理论依据。

关键词: 降落伞, 火箭撬拖曳试验, 开伞动载, 多体模型, 放伞速度

Abstract: The multi-bodies method with mass-spring damper model is used to analyze the parachute opening load in the rocket sled experiments. Results show that the computational model can be used to predict the opening load variation in rocket sled experiments. The computed maximum value and moment of opening load agree well with the experiment data. At the same time, the influences of fore-body mass and deploy velocity on the inflation load are analyzed. The analysis shows that in the range of 200~450 km/h, the peak value of the inflation load increases with the increase of the deploy velocity, and increases with the resistance characteristics of the parachute system. The peak of inflation load is increased with the increase of deploy velocity and the mass of fore-body, especially in the situation of lighter fore body mass. Results of this research provide preliminary scientific basis for design of parachute system.

Key words: parachute, rocket sled experiment, inflation load, multi-bodies model, deployment velocity

中图分类号:

V224

王从磊. 降落伞火箭撬试验开伞动载计算模型与分析[J]. 系统仿真学报, 2018, 30(12): 4574-4579.

Wang Conglei. Computational Model and Analysis of Parachute’s Opening Load in Rocket Sled Experiments[J]. Journal of System Simulation, 2018, 30(12): 4574-4579.

参考文献

[1] 王利荣. 降落伞理论及应用[M]. 北京: 宇航出版社, 1997: 460-471.
Wang Lirong.Theory and application of parachute[M]. Beijing: Astronautics Publishing House, 1997: 460-471.
[2] Mixon L C, Evans C B, Gilliam W L.Rail roughness study of Holloman high speed rocket sled test track[R]//. ADAl05, 778. USA: ADA, 1981.
[3] 周真学, 周绍慧. 国外火箭橇图册[M]. 北京: 国防工业出版社, 1979.
Zhou Zhenxue, Zhou Shaohui.Foreign Rocket Sled Atlas[M]. Beijing: National Defense Industry Press, 1979.
[4] 杨兴邦. 火箭橇试验滑轨[J]. 航空精密制造技术, 1992, 4: 35-37.
Yang Xingbang.Rocket sled test track[J]. Aviation Precision Manufacturing Technology, 1992, 4: 35-37.
[5] Calvin K I.Modeling of Parachute Opening: An Experimental Investigation[J]. Journal of Aircraft (S0021-8669), 1989, 26(5): 444-445.
[6] Wolf D, Fallon II E J. Development of Parachute Opening Factor (CK) Models For The Ares I First Stage Parachute Recovery System[C]// 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, USA: AIAA, 2011: 2011-2555.
[7] 王从磊, 孙建红, 喻东明. 阻力伞拉直过程的影响因素分析[J]. 南京航空航天大学学报, 2013, 45(2): 196-201.
Wang Conglei, Sun Jianhong, Yu Dongming.Analysis of effect factors on deployment of drag parachute[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2013, 45(2): 196-201.
[8] Purvis J W.Prediction of parachute linesail during lines first deployment[J]. Journal of Aircraft (S0021-8669), 1983, 20(11): 940-945.
[9] 贾华明, 李健. 收口十字形降落伞充气过程动力学建模与仿真[J]. 航天返回与遥感, 2013, 33(5): 16-23.
Jia Huaming, Li Jian.Modeling and Simulation of Inflation Process Dynamics of Reefed Cruciform Parachute[J]. Spacecraft Recovery & Remote Sensing, 2013, 33(5): 16-23.
[10] 郭锐, 刘荣忠. 末敏弹刚柔耦合系统动力学模型及仿真[J]. 兵工学报, 2007, 28(1): 10-14.
Guo Rui, Liu Rongzhong.Dynamics model and simulation of rigid and flexible coupling system for terminal-sensitive submunition[J]. Acta Armamentarii, 2007, 28(1): 10-14.
[11] Potvin J, Peek G, Brocato B, et al.Deceleration dynamics of unreefed cruciform and flat circular parachutes during and after inflation[C]// 16th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. USA: AIAA, 2001: 224-234.
[12] Macha J M.A simple, approximate model of parachute inflation[R]. Albuquerque, NM, USA: Sandia National Labs., 1992: 44-53.

降落伞火箭撬试验开伞动载计算模型与分析

Computational Model and Analysis of Parachute’s Opening Load in Rocket Sled Experiments

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