[ 10 ] 曹增强 .电磁铆接技术研究 [D].西安 :西北工业大学机电学院 ,2000. Cao Zengqiang. Research on electromagnetic riveting[D]. Xi’an: Schoolof Mechatronics,Northwestern Polytechni2
cal University ,2000. (in Chinese)
[ 11 ] Hartmann J , Assadi M. Low voltage electromagnetic lockbolt installation[C] ∥SAE Aerofast’92. 1992.
[12 ] 中国航空科学技术研究院 .飞机结构抗疲劳断裂强化工艺手册 [M].北京 :航空工业出版社 ,1993 :110. Chinese Aeronautical Science and Techndogy Establish2 ment. Handbook of fatigue life enhancement technique of aircraft structures[M]. Beijing: Aviation Industry Press, 1993 :110. (in Chinese)
[ 13 ] Letheris B P. Method of welding metal using stress waves: USA,3,9617,39[P].1976.
[ 14 ] Smith S. Lockbolt qualification testing for wing panel as2 semblies[ C] ∥SAE Aerofast’2000. 2000.
[ 15 ] Я рковецA И.飞机结构长寿命螺栓连接技术 [M].北京 :航空工业出版社 , 1991 :1002101.
ЯрковецA И. Long life bolted joining and riveting tech2
nologyinaircraft structures[M]. Beijing:AviationIndus2
try Press , 1991 :1002101. (in Chinese)
[ 16 ] 曹增强 .大直径铆钉的应力波铆接 [J ].航空制造技术 , 1996 (2) :27228. Cao Zengqiang. Stress wave riveting of large diameter riv2 ets[J].Aeronautical Manufacturing Technology,1996 (2) : 27228. (in Chinese)
作者简介 :曹增强 (1966 -) 男 ,博士 ,教授 ,博士生导师。主要研究方向 :飞机装配与先进连接技术 ,复合材料结构制造。 Tel : 029288494454 E2mail : czq66326 @nwpu. edu. cn
(责任编辑 :蔡斐 )
国外期刊《Journal of Aerospace Engineering ,
Proceedings of the IMechE Part G》
PROCEEDINGS OF THE IMechE PART G ISSN 095424100 http :/ / www. pepublishing. com
CONTENTS A test rig for investigations of gas turbine combustor cooling concepts under realistic operating conditions
T Behrendt and Ch Hassa 169
Efficient prediction of damage resistance and tolerance of composite aerospace structures 179 J Baaran , L K.rger , and A Wetzel
Obtaining multi2loop pursuit2control pilot models from computer simulation 189 R A Hess
Energy dissipation in spacecraft structures incorporating bolted joints with viscoelastic layers 201 R Wang , A D Crocombe , G Richardson , and C I Underwood
Observer2based digital tracker for manoeuvring target described by the continuous2time non2linear dyna mic system
JSHTsai,CTWang,SMGuo,LSShieh,andCRLiu 213
Aeroelastic response of a swept wing with cubic structural non2linearities 229 M Razi and B Ghadiri
A review of pressure2sensitive paint for high2speed and unsteady aerodynamics 249 J W Gregory , K Asai , M Kameda , T Liu , and J P Sullivan
Uncertainty2based model2order reduction of flexible systems preserving robust closed2loop performance
N Aouf and B Boulet 291
Table for contents of Acta Aeronautica et Astronautica Sinia , Volume 29 , Number 1 , January 2008
Published for the Institution of Mechanical Engineers
by Professional Engineering Publishing Limited , London , U K
文章编号 :100026893 (2008) 0320645206
迭代动力缩聚法的收敛性分析
汪晓虹 1,曹立娟 2,刘慧 1,陈怀海 2
(1.南京航空航天大学理学院 ,江苏南京 210016)
(2.南京航空航天大学航空宇航学院 ,江苏南京 210016)
Convergence Analysis of Iterative Dynamic Condensation Methods
Wang Xiaohong1 , Cao Lijuan2 , Liu Hui1 , Chen Huaihai2
(1. College of Science , Nanjing University of Aeronautics and Astronautics , Nanjing 210016 , China)
(2. College of Aerospace Engineering , Nanjing University of Aeronautics and Astronautics , Nanjing 210016 , China)
摘 要 :利用 L yap unov矩阵方程和 Riccati矩阵方程解的理论 ,对迭代动力缩聚法的收敛性进行了分析证明 ,并给出了迭代收敛的充分条件。揭示了动力缩聚法与经典的子空间迭代法的内在关系 ,阐明了各自的优缺点。迭代动力缩聚法实质上是子空间迭代法的变形 ,它需要人为选择主辅自由度
,而子空间迭代法需要人为选定初始迭代向量。从理论上讲 ,只有主辅自由度选择满足收敛的充分条件要求
,才能保证迭代结果收敛到理论上的精确解。给出了一个数值算例 ,对几种算法进行了对比 ,并验证了本文的论点。关键词 :动力缩聚 ;迭代法 ;矩阵方程 ;有限元法 ;建模中图分类号 : V214. 1 文献标识码 :A
Abstract : Based on the theory of solution to the Lyapunov and Riccati matrix equations , in this paper an in2
introduced. The relationship between the iterative dynamic condensation methods and the classical subspace iterative method is uncovered. In fact , the iterative dynamic condensation methods are a transformed kind of the subspace iterative method. One must select the master and slave degrees of freedom in the iterative dynamic condensation algorithms or the initial iterative vectors in the subspace itera2 tivealgrithm. Theoretically,iftheselectionofthemasterandslavedegreesoffreedommeetthedemandofthe sufficient conditions ,the iterative dynamic condensation algorithms will obtain an accurate result. A numerical example is presented in the end of the paper. The results by the various algorithms are compared ,and the idea of the paper is verified. Key words : dynamic condensation; iterative method; matrix equation; finite element method; modeling
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：航空学报08大飞机专刊(41)
