可控排气式气囊着陆缓冲特性研究
|
摘要
为了综合考量空投设备着陆缓冲过程中的最大过载、最大下降位移以及气囊最大超压等因素,利用LS-DYNA软件数值分析了一种可控排气式气囊的着陆缓冲特性,研究了排气阀的开口面积和压力门限对该系统缓冲性能的影响。结果表明:开口面积和压力门限对缓冲性能有显著的影响,取值过大或过小均不能满足缓冲性能要求;一定范围内增大开口面积可有效降低设备的最大过载和气囊的最大超压,但同时会降低设备的最小离地高度;压力门限对气囊最大超压量的影响较小,一定范围内降低压力门限可降低设备最大过载。
For a comprehensive consideration of the factors such as maximum over load, maximum drop displacement and airbag's maximum over pressure when an airdrop equipment being landing, the landing buffer capability of a controllable vent airbag is analyzed using LS-DYNA software. Venting area and pressure threshold of vent valve are investigated for the influence of buffer capability. The results show that: the venting area and pressure threshold have an obvious significance to the buffer capability; the capability cannot be satisfied when these parameters values are oversize or undersize. The increment of venting area within limits can reduces the maximum over load and over pressure, but at the same time reducing the maximum drop displacement. The pressure threshold has less influence on the over load, reducing the pressure threshold within limits can reduce the maximum landing over load.
For a comprehensive consideration of the factors such as maximum over load, maximum drop displacement and airbag's maximum over pressure when an airdrop equipment being landing, the landing buffer capability of a controllable vent airbag is analyzed using LS-DYNA software. Venting area and pressure threshold of vent valve are investigated for the influence of buffer capability. The results show that: the venting area and pressure threshold have an obvious significance to the buffer capability; the capability cannot be satisfied when these parameters values are oversize or undersize. The increment of venting area within limits can reduces the maximum over load and over pressure, but at the same time reducing the maximum drop displacement. The pressure threshold has less influence on the over load, reducing the pressure threshold within limits can reduce the maximum landing over load.
引文
[1]温金鹏,李斌,杨智春.缓冲气囊冲击减缓研究进展[J].宇航学报,2010,31(11):2438-2447.(WEN Jinpeng,LI Bin,YANGZhichun.Progress of study on impact attenuation capability of airbag cushion system[J].Journal of astronautics,2010,31(11):2438-2447(in Chinese)).
[2]DOUGLAS A.Mars exploration rover airbag landing loads testing and analysis[C]//Proceedings of 5th AIAA/ASME/ASCE/AHS/ASCStructures,Structural Dynamics&Materials Conference.California,USA:AIAA,2004:1-11.
[3]BEN T,SUSANNAH G,AARON W.A summary of the development of a nominal land landing airbag impact attenuation system for the orion crew module[C]//Proceedings of 20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar.Washington,USA:AIAA,2009:1-11.
[4]李建阳,王红岩,芮强,等.自充气式气囊缓冲特性试验研究[J].振动与冲击,2014,33(4):119-123.(LI Jianyang,WANG Hongyan,RUI Qiang,et al.Tests for cushioning characteristics of a self-inflating airbag[J].Journal of vibration and shock,2014,33(4):119-123(in Chinese)).
[5]牛四波,王红岩,迟宝山,等.重装回收系统双气室气囊缓冲特性分析[J].振动与冲击,2012,31(10):74-78.(NIU Sibo,WANGHongyan,CHI Baoshan,et al.Cushioning characteristics of double-chamber airbag for heavy equipment recovery system[J].Journal of vibration and shock,2012,31(10):74-78(in Chinese)).
[6]黄国,黄海明,徐晓亮,等.双圆柱气囊缓冲性能分析[J].计算力学学报,2014,31(2):212-216.(HUANG Guo,HUANG Haiming,XU Xiaoliang,et al.Simulation on impact attenuation capability of bi-cylinder airbags[J].Chinese journal of computational mechanics,2014,31(2):212-216(in Chinese)).
[7]吴鸿超,梁增友,冯阳,等.薄壁金属管在中高速冲击下的缓冲特性研究[J].应用力学学报,2016,33(2):325-332.(WU Hongchao,LIANG Zengyou,FENG Yang,et al.Energy absorption characteristics of the expansion of thin-walled circular metal tubes by middle-speed and high-speed impact of a rigid cylinder[J].Chinese journal of applied mechanics,2016,33(2):325-332(in Chinese)).
[8]徐鹏,高猛.高g值冲击下泡沫铝填充壳结构抗冲击性能多目标优化[J].应用力学学报,2016,33(5):845-851.(XU Peng,GAOMeng.Multi-objective crashworthiness optimization for foam-filled thin-walled structures subjected to high g value impact[J].Chinese journal of applied mechanics,2016,33(5):845-851(in Chinese)).
[2]DOUGLAS A.Mars exploration rover airbag landing loads testing and analysis[C]//Proceedings of 5th AIAA/ASME/ASCE/AHS/ASCStructures,Structural Dynamics&Materials Conference.California,USA:AIAA,2004:1-11.
[3]BEN T,SUSANNAH G,AARON W.A summary of the development of a nominal land landing airbag impact attenuation system for the orion crew module[C]//Proceedings of 20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar.Washington,USA:AIAA,2009:1-11.
[4]李建阳,王红岩,芮强,等.自充气式气囊缓冲特性试验研究[J].振动与冲击,2014,33(4):119-123.(LI Jianyang,WANG Hongyan,RUI Qiang,et al.Tests for cushioning characteristics of a self-inflating airbag[J].Journal of vibration and shock,2014,33(4):119-123(in Chinese)).
[5]牛四波,王红岩,迟宝山,等.重装回收系统双气室气囊缓冲特性分析[J].振动与冲击,2012,31(10):74-78.(NIU Sibo,WANGHongyan,CHI Baoshan,et al.Cushioning characteristics of double-chamber airbag for heavy equipment recovery system[J].Journal of vibration and shock,2012,31(10):74-78(in Chinese)).
[6]黄国,黄海明,徐晓亮,等.双圆柱气囊缓冲性能分析[J].计算力学学报,2014,31(2):212-216.(HUANG Guo,HUANG Haiming,XU Xiaoliang,et al.Simulation on impact attenuation capability of bi-cylinder airbags[J].Chinese journal of computational mechanics,2014,31(2):212-216(in Chinese)).
[7]吴鸿超,梁增友,冯阳,等.薄壁金属管在中高速冲击下的缓冲特性研究[J].应用力学学报,2016,33(2):325-332.(WU Hongchao,LIANG Zengyou,FENG Yang,et al.Energy absorption characteristics of the expansion of thin-walled circular metal tubes by middle-speed and high-speed impact of a rigid cylinder[J].Chinese journal of applied mechanics,2016,33(2):325-332(in Chinese)).
[8]徐鹏,高猛.高g值冲击下泡沫铝填充壳结构抗冲击性能多目标优化[J].应用力学学报,2016,33(5):845-851.(XU Peng,GAOMeng.Multi-objective crashworthiness optimization for foam-filled thin-walled structures subjected to high g value impact[J].Chinese journal of applied mechanics,2016,33(5):845-851(in Chinese)).