A5076975727- Fatigue and fracture mechanics
- Probabilistic and Robust Engineering Design
- Additive Manufacturing Materials and Processes
- Material Properties and Failure Mechanisms
- High Entropy Alloys Studies
- Welding Techniques and Residual Stresses
- Computational Fluid Dynamics and Aerodynamics
- High-Velocity Impact and Material Behavior
- Aluminum Alloy Microstructure Properties
- High Temperature Alloys and Creep
- Mechanical Failure Analysis and Simulation
- Non-Destructive Testing Techniques
- Advanced Sensor Technologies Research
- Titanium Alloys Microstructure and Properties
- Additive Manufacturing and 3D Printing Technologies
- Mechanical Behavior of Composites
- Advanced Welding Techniques Analysis
- Engineering Diagnostics and Reliability
- Rocket and propulsion systems research
- Natural Fiber Reinforced Composites
- Structural Health Monitoring Techniques
- Metal Alloys Wear and Properties
- Heat Transfer and Numerical Methods
- Turbomachinery Performance and Optimization
- Advanced Aircraft Design and Technologies
Qinetiq (United Kingdom)
2024
Defence Science and Technology Group
2002-2022
Defence Materials Technology Centre (Australia)
2020
RMIT University
2014-2015
Victorian Bar
1989
Lockheed Martin (United States)
1970
NOAA Physical Sciences Laboratory
1970
Abstract Fatigue crack growth tests were conducted on compact, C(T), specimens made of 7249‐T76511 aluminium alloy. These to generate rate data from threshold near fracture over a wide range load ratios (R). Four methods used data: (1) ASTM E‐647 reduction (LR), (2) compression pre‐cracking constant‐amplitude (CPCA), (3) LR, and (4) constant mouth opening displacement LR method. A closure analysis was develop an effective stress‐intensity factor against relation using constraint (α = 1.85)....
ABSTRACT The phenomenon of flat-to-slant crack growth has been studied by many in the fracture mechanics community. At low stress-intensity factors, a fatigue-crack surface is flat (tensile mode) and crack-front region under plane-strain conditions (high constraint). As grows with higher 45° shear lip occurs through thickness sheet or plate. This behavior mode, which constraint plane-stress conditions. In 1966, Schijve found that transition from on 2024-T3 Alclad aluminum alloy over wide...
ABSTRACT Fatigue crack growth rate properties are typically determined by experimental methods in accordance with ASTM Standard E647. These traditional use standard notched specimens that precracked under cyclic tensile loads before the main test. The data produced using this approach have been demonstrated elsewhere to be potentially adversely affected test method, particularly threshold region where load reduction (LR) also required. Coarse‐grained materials exhibit rough and tortuous...
Through Thickness Residual Stress and Microstructural Mapping of AA7085-T7452 Die Forging P.S. Baburamani, K.F. Walker, P.K. Sharp , J. Niclis, A. Shekhter Abstract. Significant weight savings reductions in manufacturing costs have motivated the drive towards use unitised structures such as large die forgings modern aircraft. However, detrimental bulk tensile residual stresses, […]
Crack closure is an important factor affecting fatigue crack growth in high strength alloy materials. Plasticity known to be the main driver of closure, but some materials and at stages other mechanisms such as fracture surface roughness debris accumulation are also important. Analytical models based on plasticity induced concept have been very successful correlating rates lives for a range under constant amplitude spectrum loading. However, extreme values plastic constraint factors,...