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  • 1
    Electronic Resource
    Electronic Resource
    Global-Local Hierarchical Analysis Techniques for Damaged Aircraft Fuselage Considering Bulging Deformation of Crack (2006)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 324-325 (Nov. 2006), p. 871-874 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: In order to calculate the fracture parameters (Stress intensity factor) in a complicated 3-dimention aircraft model with damage in the aircraft panel, a new two steps global-localhierarchical analysis strategy is used. This paper primarily describes the development andapplication of advanced computational analysis techniques to determine stress intensity factors forthe damaged panels based on the two steps hierarchical analysis strategy from global to 3-D localmodel, the bulging deformation of crack can be considered in the local model. A fracture parametercalculation programme based on automated global-local procedure to simulate cracked aircraftpanel tests is developed for the hierarchical strategy. This programme may create models of twostages, transfer boundary conditions, calculate and obtain fracture parameter automatically. Finally,this paper presents some of the experimental data and the calculated fracture parameters arecompared with the experimental results
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/52/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.324-325.871.pdf
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  • 2
    Electronic Resource
    Electronic Resource
    Fracture Analysis for Damaged Aircraft Fuselage Using Substructure Method (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Advanced materials research Vol. 33-37 (Mar. 2008), p. 29-34 
    Details
    ISSN: 1662-8985
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: This paper primarily describes the development and application of substructurecomputational analysis techniques to determine stress intensity factors for the damaged panelssubjected to fatigue internal pressure. A program based on substructure analysis technique has beendeveloped for the fracture analysis of curved aircraft panels containing cracks. This program maycreate whole model which consists of substructure superelements and obtain fracture parameter of thecrack by expanding results in superelement automatically. For instance, a typical test curved panelmodel consists of 7 frames and 8 stringers is calculated. This numerical approach has been validatedthrough comparison between the calculation SIF results and available experimental data of a typicaltest panel with a longitudinal crack. The technique that has been established here is also applied to theother analysis of a test series of cracked panel with 7 frames and 10 stringers. SIFs of four cracks in itwith different crack lengths are obtained efficiently
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/40/transtech_doi~10.4028%252Fwww.scientific.net%252FAMR.33-37.29.pdf
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    Paper (German National Licenses)
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  • 3
    Electronic Resource
    Electronic Resource
    Numerical Solution of Elas-Plastic Impact Load of Tube Column (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Advanced materials research Vol. 33-37 (Mar. 2008), p. 363-368 
    Details
    ISSN: 1662-8985
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: The explicit numerical method is used to trace the impact procedure of the tube columnsimpacted by a rigid body. The bar and rectangle tube models are both used to simulate the tubecolumn. The elastic and elas-plastic impact load with different mass ratio and impact speed areobtained. The calculation results show that: for elastic models, the bigger the mass ratio and thehigher the rigid body speed, the bigger the peak value of elastic impact load; at the same time, themore obvious the reduction effect of local buckling of rectangle tube on the peak value of impact loadand the longer the contact time of tube model; so the peak value of impact load of the rectangle tube isnot proportional to the rigid body speed. The stress wave in the tube causes a little difference betweenthe load curves of tube model and bar model. For elas-plastic models, the higher the rigid body speedand the smaller the mass ratio, the bigger the peak value of impact load and the longer the contacttime. The higher the rigid body speed, the bigger the difference between elastic and elas-plasticimpact load peak value due to the expanding of plasticity. Because of the effect of local buckling, thepeak value of elas-plastic impact load of rectangle tube is always lower than that of bar
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/40/transtech_doi~10.4028%252Fwww.scientific.net%252FAMR.33-37.363.pdf
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  • 4
    Electronic Resource
    Electronic Resource
    Analysis of the Load-Carrying Capability of the Casing Plug Joint of Steel Tube Structures Considering the Contact Effect (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Advanced materials research Vol. 33-37 (Mar. 2008), p. 321-326 
    Details
    ISSN: 1662-8985
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Nonlinear finite element model analysis of the casing plug joints of steel tubular has beenrealized by ANSYS software. The law of load-carrying capability and stiffness of joint are separatelygained by changing the ratio of length and diameter (R/L) and the ratio of the casing length and themain tube length (l/L). The influence of the casing thickness on the load-carrying capability andstiffness are also discussed. The results indicated that the load-carrying capability and stiffness of thejoints both increase with the ratio(R/L) increment and the ratio of the casing length and main tubelength (l/L). When the main tube thickness is equal to casing thickness, the load-carrying capacity ofjoints achieves the most
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/40/transtech_doi~10.4028%252Fwww.scientific.net%252FAMR.33-37.321.pdf
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  • 5
    Electronic Resource
    Electronic Resource
    Fracture Analysis for Stiffened Aircraft Fuselage Using Substructure Method (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 385-387 (July 2008), p. 837-840 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: This paper primarily describes the development and application of substructurecomputational analysis techniques in two-step hirarchical strategy to determine stress intensityfactors for the stiffened damaged panels subjected to fatigue internal pressure. A program based onsubstructure analysis technique and global-local hierarchical strategy has been developed for thefracture analysis of curved aircraft panels containing cracks. This program may createsuperelements in global and local models, and obtain fracture parameter of the crack in local modelby expanding results in superelements automatically. The technique is applied to the analysis of acracked panel with 7 frames and 10 stringers. SIFs of four cracks in it with different crack lengthsare obtained efficiently
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/57/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.385-387.837.pdf
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  • 6
    Electronic Resource
    Electronic Resource
    Fracture Analysis for Damaged Aircraft Fuselage Subjected to Blast (2007)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 348-349 (Sept. 2007), p. 705-708 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: This paper primarily presents the development and application of automationcomputational analysis techniques to determine the dynamic stress intensity factor for the damagedaircraft fuselage subjected to triangle blast load. A program based on automated procedure tosimulate cracked fuselage is developed. It may create 3-dimention panel model usingparameterization. The stress around the crack tips will be captured and the dynamic stress intensityfactor can be obtained at every moment of the blast automatically. A typical curved panel modelwhich consists of 7 frames and 8 stringers is calculated. The calculation results shown that the formof the dynamic SIF curve is similar to that of the triangle load curve while the peak point ofdynamic SIF curve occurs a little later than that of the load curve due to the inertia effect. Thelonger the crack is, the more obvious the effect is. The peak SIF value of the crack under blast loadis bigger than that under the static load for certain crack length. The longer the crack is, the biggerthe difference between the dynamic peak SIF value and static SIF is. At the same time, the loadtime has effect on the dynamic SIF curve and its peak value. These results show good agreementswith theoretical principles
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/55/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.348-349.705.pdf
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  • 7
    Electronic Resource
    Electronic Resource
    Elastic-Plastic Torque Analysis of Notched Cross-Section Bars Using the Finite Difference Method (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 385-387 (July 2008), p. 869-872 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: A new strategy of finite differences method is proposed for analysis of notchedcross-section bars under elastic-plastic torsion. Relation curves of the elastic-plastic torqueresponding with different positions, angles and lengths of the notches in one section are obtained bynumerical tests. It can be seen that these relation curves exhibit obvious nonlinearity. Meanwhile,the stress intensity factors can also be easily calculated by utilizing the results of above finitedifferences method. It provides an effective way for solving such elastic-plastic fracture mechanicsproblem
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/57/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.385-387.869.pdf
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    Paper (German National Licenses)
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  • 8
    Electronic Resource
    Electronic Resource
    The Analytical Trial Function Method (ATFM) for Finite Element Analysis of Plane Crack/Notch Problems (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 385-387 (July 2008), p. 617-620 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: A new technique, Analytical Trial Function Method (ATFM), is proposed to formulatenew finite element models for analysis of plane crack/notch problems. A new analytical finiteelement, named ATFM-CN, is successfully constructed. Furthermore, in order to determine theeigenvalues of the crack/notch problems, which utilized in above analytical trial functions, a modifiedsub-region accelerated Müller method is also suggested. Numerical examples show the presentapproach exhibits excellent performance in the analysis of stress-singularity problems
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/57/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.385-387.617.pdf
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