Stress analysis by finite element method and experimental verification of some deformoble bodies
Şekli değiştirilebilir cisimlerin sonlu eleman yöntemi ile gerilim analizi ve deneysel doğrulaması
- Tez No: 29046
- Danışmanlar: PROF. DR. A. ERMAN TEKKAYA
- Tez Türü: Yüksek Lisans
- Konular: Makine Mühendisliği, Mechanical Engineering
- Anahtar Kelimeler: Gerilme analizi, Sonlu elemanlar yöntemi, Contact Stress Analysis by Finite Element Method, Testing and Analysis of Composite Materials, Filament Wound Tubes, Finite Element Stress Analysis of Threaded Joints, Analysis of Polyamide Nozzle Cap Deformation. Science Code 625.03.02 IV, Stress analysis, Finite element method
- Yıl: 1993
- Dil: İngilizce
- Üniversite: Orta Doğu Teknik Üniversitesi
- Enstitü: Fen Bilimleri Enstitüsü
- Ana Bilim Dalı: Makine Mühendisliği Ana Bilim Dalı
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: Belirtilmemiş.
Özet
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Özet (Çeviri)
ABSTRACT STRESS ANALYSIS BY FINITE ELEMENT METHOD AND EXPERIMENTAL VERIFICATION OF SOME DEFORMABLE BODIES ERYÜREK, Halil M.S. in Mechanical Engineering Supervisor: Prof. Dr. A.Erman TEKKAYA September, 1993, 166 pages. In this thesis, the finite element stress analysis of specific deformable bodies is performed. It is shown that a numerical analysis should be accomplished by various experimental studies whenever possible. Computational analysis cover different fields: Plane wing flap actuator having complex geometry has been analyzed by linear analysis procedure although, the problem was nonlinear boundary condition problem. In this example, contact problem between the pin and main body has been eliminated by having a soft sleeve with no clearance. It has been observed that the boundary conditions used around the holes did not affect the nominal stress distribution in the body of the flap actuator. Steel rocket motor case-head threaded joint has been analyzed by contact algorithm. The threaded joints on the steel motor case and head have been modeled by having one element for each thread. The original design has been modified by removing the last two threads on the case and the thickness of the case mat threaded region has been increased. Nonlinear boundary conditions and elastic-perfectly-plastic material property has been considered on the stress analysis of polyamide nozzle cap. For different friction coefficients the punch force variation against the strain have been compared with experimental values. Composite rocket motor case has been analyzed as linear elastic with orthotropic property. Maximum stress criterion and maximum strain criterion results for six different winding patterns have been compared and the pattern ( ± 458, 90,5) has been selected. The experimental study covers typically data characterization of polyamide material, determination of failure criteria for composite material Kevlar 49/epoxy and verification of results of polyamide nozzle cap analyses and composite specimen computation. For the closed-end pressure test (biaxial stress state) of composite material, a apparatus has been modified for our case and produced. Comparison of experimental and numerical results were satisfactory. The maximum stress and maximum strain criteria for uniaxial and biaxial stress state have been found best failure criteria to determine burst failure of Kevlar 49/epoxy composite tubular structures.
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