[ 10 ]　曹增強 .電磁鉚接技術研究 [D].西安 :西北工業大學機電學院 ,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 ]　中國航空科學技術研究院 .飛機結構抗疲勞斷裂強化工藝手冊 [M].北京 :航空工業出版社 ,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.飛機結構長壽命螺栓連接技術 [M].北京 :航空工業出版社 , 1991 :1002101.

ЯрковецA И. Long life bolted joining and riveting tech2
nologyinaircraft structures[M]. Beijing:AviationIndus2
try Press , 1991 :1002101. (in Chinese)
[ 16 ]　曹增強 .大直徑鉚釘的應力波鉚接 [J ].航空制造技術 , 1996 (2) :27228. Cao Zengqiang. Stress wave riveting of large diameter riv2 ets[J].Aeronautical Manufacturing Technology,1996 (2) : 27228. (in Chinese)
作者簡介 :曹增強 (1966 -)　男 ,博士 ,教授 ,博士生導師。主要研究方向 :飛機裝配與先進連接技術 ,復合材料結構制造。 Tel : 029288494454 E2mail : czq66326 @nwpu. edu. cn
(責任編輯 :蔡斐 )

國外期刊《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

　　文章編號 :100026893 (2008) 0320645206

迭代動力縮聚法的收斂性分析

汪曉虹 1,曹立娟 2,劉慧 1,陳懷海 2
(1.南京航空航天大學理學院 ,江蘇南京　 210016)

(2.南京航空航天大學航空宇航學院 ,江蘇南京　 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矩陣方程和 Riccati矩陣方程解的理論 ,對迭代動力縮聚法的收斂性進行了分析證明 ,并給出了迭代收斂的充分條件。揭示了動力縮聚法與經典的子空間迭代法的內在關系 ,闡明了各自的優缺點。迭代動力縮聚法實質上是子空間迭代法的變形 ,它需要人為選擇主輔自由度
,而子空間迭代法需要人為選定初始迭代向量。從理論上講 ,只有主輔自由度選擇滿足收斂的充分條件要求
,才能保證迭代結果收斂到理論上的精確解。給出了一個數值算例 ,對幾種算法進行了對比 ,并驗證了本文的論點。關鍵詞 :動力縮聚 ;迭代法 ;矩陣方程 ;有限元法 ;建模中圖分類號 : V214. 1　　　文獻標識碼 :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
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：航空學報08大飛機專刊(41)