1 / 18

Application in Finite Element Analysis MAE 5060 Term Semester Project: Finite Element Analysis

Application in Finite Element Analysis MAE 5060 Term Semester Project: Finite Element Analysis Of the FIT Sat III Rocket Carlos Figueredo Lionel Fevre. Presentation Of The Original Model:. Pay Load Section. Stringers. Motor Section. Wing Assembly. Motor = 10 000N.

rebecca-chen
Download Presentation

Application in Finite Element Analysis MAE 5060 Term Semester Project: Finite Element Analysis

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Application in Finite Element Analysis MAE 5060 Term Semester Project: Finite Element Analysis Of the FIT Sat III Rocket Carlos Figueredo Lionel Fevre

  2. Presentation Of The Original Model: Pay Load Section Stringers Motor Section Wing Assembly Motor = 10 000N

  3. Problem: Structure too weak. Motor plate: Max Stress =213 MPa 2 Stringers at Payload section and Motor section

  4. New Design:

  5. New Design in Details: • Top Housing cut in two • 4 stringers at Payload Section • 8 Stringers above the Motor-Plate • 8 vertical flanges on the Motor-Plate • Wing-Assembly Ring raised up around Motor-Plate • 4 Stringers at Motor Section • Addition of hole patterns (fasteners)

  6. Finite Element Analysis: • Payload Section • Housing Static / Buckling / Modal Analyses • Stringers Static / Buckling / Modal Analyses • Motor Section • Motor PlateStatic / Modal Analyses • Short stringersStatic / Buckling / Modal Analyses • Long Stringers Static / Modal Analyses • Motor Assembly (1/8th)Static / Modal Analyses • Idealization of Complete assemblyModal / Static Analyses

  7. Motor Section • Motor PlateStaticAnalyses VM max: MAX. 13.748 MPa Max Displacement: MAX. 3.86462E-05 [mm]

  8. Motor Section • Motor PlateModalAnalyses The values for the 6 modes frequencies were: Mode #. Freq.(Rad/sec) Freq.(Hertz) Period(Seconds) 1 16130 2567.1 0.00038954 2 16911 2691.4 0.00037155 3 18344 2919.5 0.00034252 4 24651 3923.4 0.00025488 5 26683 4246.7 0.00023548 6 30391 4836.9 0.00020674 Motor load applied for 5 sec:

  9. Fully constrained weld 2500N force • Motor Section • Short StringersStaticAnalyses Max VM = 47 MPa VM = 31 MPa

  10. Motor Section • Short StringersBucklingAnalyses BLF = 0.1028156E+01 Max Displacement

  11. Motor Section • Short StringersModalAnalyses Mode Frequency (Hz) 1 118.3 2 243.1 3 382.2 Natural Frequencies :

  12. Motor Section • Motor AssemblyModal Fix: Z Displacement Mode Frequency (Hz) 1 602.9 2 904.7 3 1043 4 1295 5 1636 6 2289 Symmetric Restraint

  13. Motor Section • Motor AssemblyStatic MAX. 5.856+07 Pa

  14. Complete Rocket Analysis - Modal CPU: 4.5359Kg Plane: 6.8038Kg Wing Assemble: 16.3293Kg Mode Frequency Convergence ---- ------------ ----------- 1 0.000000e+00 0.0% 2 0.000000e+00 0.0% 3 6.484042e-08 0.0% 4 7.989401e-04 4.6% 5 9.185365e-04 5.8% 6 9.255145e-04 6.0% Constrain: Free R Disp. & Th Rotation

  15. Complete Rocket Analysis - Static CPU - Load: 702.52N VM MAX. 0.57542E+07 [Pa] Plane - Load: 1053.77N Symmetric Constrains Constrain: Free R Disp. & Th Rotation Wing Assemble: 2529.03N

  16. QUESTIONS ?

More Related