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  1. Mat_Aero

    Question - Identification of critical modal freq.

    Thank you for responses, FEA way - well, as I understand it, the participation factor only tells you how each mode contributes to the overall response of the system, therefore which modes can be critical for overall response, but not which modes are critical for particular component. The modes...
  2. Mat_Aero

    Question - identification of critical modes

    Hello everyone, I have a question regarding modal / harmonic analysis. Is there any general rule or recommendation to determine which modal shapes can be critical for structure from stress point of view? I know that partially this information can be determined from modal effective...
  3. Mat_Aero

    Question - Identification of critical modal freq.

    Hello everyone, I have a question regarding modal / harmonic analysis. Is there any general rule or recommendation to determine which modal shapes can be critical for structure from stress point of view? I know that partially this information can be determined from modal effective...
  4. Mat_Aero

    Modal Analysis - modal matrices export

    Thank you for reply.I've already requested DISP=ALL. You're right, the generalized mass,stiffness,eigenvalues are printed in the eigenvalue summary table, thats no problem. But lets consider simple 2DOF spring-mass system. The system has obviously 2 DOF, so Mhh is 2x2, Phi(modal matrix) should...
  5. Mat_Aero

    Modal Analysis - modal matrices export

    Hello. I have question regarding the NX Nastran modal analysis. I am working on project which takes Nastran results from modal analysis for further post processing/computation. However, the values which I am interested in are modal mass matrix(Mhh), modal matrix(Phi) and matrix of...
  6. Mat_Aero

    Femap 6060.Laminate Max. Failure Index calculation

    FI means Failure Index. I've contacted the Nastran support as well and waiting for their answer. I forgot to attach the printscreen from f06 file. f06 printscreen: https://files.engineering.com/getfile.aspx?folder=fc5061ae-fee9-42c9-a39c-66ce9bfade46&file=f06_printscreen.PNG
  7. Mat_Aero

    Femap 6060.Laminate Max. Failure Index calculation

    Hello everyone, I have a question regarding the 6060. Laminate Max. failure Index computation in Femap. I’ve created basic 2D model of rectangular CFRP plate(M55J prepreg) with layup [(0/+-25/0)2/0]s. I’ve applied tensile load on one end and fixed constraint on the other and performed the...
  8. Mat_Aero

    Adhesively bonded joint analysis

    I am using the linear elastic properties. I managed to find stress-strain curve for the adhesive I assuming to use, and the curve has linear behavior for large portion of stress values and then remains practically flat. I’ve taken the adhesive properties from manufacturer’s datasheet. I haven’t...
  9. Mat_Aero

    Adhesively bonded joint analysis

    Hello. I have question regarding modeling and analysis of the bonded joint for thermoelastic load case. The bonded joint consists of CFRP tube from T700 prepreg and Titanium tube which are bonded together by epoxy adhesive, see attached figure. The CFRP tube is modeled with shell elements while...

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