期刊文献+

含局部非线性的月球探测器软着陆动力学模型降阶分析 被引量:7

Model Reduction Analysis of Soft Landing Dynamics for Lunar Lander with Local Nonlinearities
原文传递
导出
摘要 为准确预估探测器着陆冲击过程的动力学响应,采用非线性有限元方法建立了探测器软着陆动力学模型,能够较全面地反映出各种非线性因素。针对非线性有限元求解耗时长的弱点,考虑到探测器的局部非线性特性,利用广义动力缩聚(GDR)方法建立了月球探测器中心体的降阶模型。提出了一种基于脉冲响应函数的模态截断准则,在广义动力缩聚方法的基础上筛选少数几阶模态影响系数(MIC)较高的模态表征中心体的加速度响应,能够进一步降低模型的阶数。将降阶的中心体模型与含非线性的缓冲机构连接后进行的软着陆动力学分析能够准确而快速地预估探测器测点的加速度响应,与非降阶模型对比,计算时间缩短了75.5%,加速度响应的相对峰值误差控制在5%以内。数值仿真表明,广义动力缩聚方法能够有效地解决传统非线性有限元方法求解效率低的问题,本文所提模态截断准则的优点是适于求解模态密集问题并且与系统的输入输出无关。 In order to accurately predict the dynamic response of a lunar lander during its landing process,a dynamics model for the lunar lander is built using the nonlinear finite element method.This method considers comprehensively various nonlinear factors but is time consuming.Aiming at solving this disadvantage,the generalized dynamic reduction (GDR) method is adopted to build an order reduced model for the center body of the lunar lander which takes into consideration the lander's local nonlinearities and a new modal truncation criterion is proposed based on the impulse response function.By means of this criterion,the acceleration of the center body can be characterized by selecting just a few normal modes with high model influence coefficient (MIC) based on GDR method,this further reduces the order of the center body.In a case study on soft landing dynamics,the order reduced center body is jointed with the nonlinear landing gear.Compared with the original nonreduced FE model,up to 75.5% computational time is saved using the modal truncation criterion while the relative peak error of acceleration is kept below 5%.From the results it can be concluded that the GDR method works excellently for enhancing the simulation efficiency of lunar landing and the proposed criterion has the advantage of solving modal-denseness systems with independence of input and output.
出处 《航空学报》 EI CAS CSCD 北大核心 2014年第5期1319-1328,共10页 Acta Aeronautica et Astronautica Sinica
基金 北京理工大学基础研究基金(20120142009)~~
关键词 月面软着陆 非线性有限元法 局部非线性 模型降阶 模态截断准则 lunar soft landing nonlinear FEM local nonlinearity model reduction modal truncation criterion
  • 相关文献

参考文献20

  • 1Lavender R E.Equations for two-dimensional analysis of touchdown dynamics of spacecraft with hinged legs including elastic,damping,and crushing effects,N 66 23668[R].Huntsville:George C.Marshall Space Flight Center,1963.
  • 2Nohmi M,Miyahara A.Modeling for lunar lander by mechanical dynamics software,AIAA-2005-6416[R].Reston:AIAA,2005.
  • 3Otto O R,Laurenson R M,Melliere R A,et al.Analyses and limited evaluation of payload and legged landing system structures for the survivable soft landing of instrument payloads,NASA CR-111919[R].Washington D.C.:NASA,1971.
  • 4陈金宝,聂宏,张明,汪岸柳.Overloading of Landing Based on the Deformation of the Lunar Lander[J].Chinese Journal of Aeronautics,2008,21(1):43-47. 被引量:16
  • 5万峻麟,聂宏,陈金宝,李立春,汪岸柳.月球着陆器有效载荷着陆冲击响应分析[J].宇航学报,2010,31(11):2456-2464. 被引量:12
  • 6赵俊锋.月球探测器软着陆动力学分析及力学环境研究[D].北京:北京理工大学,2011.
  • 7梁东平,柴洪友,曾福明.月球着陆器着陆腿非线性有限元建模与仿真[J].北京航空航天大学学报,2013,39(1):11-15. 被引量:13
  • 8Kim K O,Anderson W J.Generalized dynamic reduction in finite element dynamic optimization[J].AIAA Journal,1984,22(11):1616-1617.
  • 9Laurenson R,Melliere R,Mcgehee J.Analysis of legged landers for the survivable soft landing of instrument payloads[J].Journal of Spacecraft and Rockets,1972,10(3):208-214.
  • 10William F R.Apollo experience report-lunar module landing gear subsystem,NASA TN D-6850[R].Washington D.C.:NASA,1972.

二级参考文献36

共引文献39

同被引文献152

引证文献7

二级引证文献19

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部