See links to institutions for detailed program information.
BEng Mechanical Engineering, 1986:
Royal Military College, Kingston, OntarioFinal Year Courses:
Fluid Dynamics
Heat Transfer
Stress Analysis
Dynamic Systems
Thermodynamics
Aeronautical and Space Propulsion
Aerodynamics
Aircraft Performance and Control
MSc Aerospace Vehicle Design, 1992:
Cranfield Institute of Technology, EnglandSample Courses:
Aerospace Human Factors
Maintainability
Fault Tree/Failure Modes and Effects Analysis
Project Design of Aircraft Systems and Structural Components
Aircraft Loading Actions Analysis
Aeroelasticity
Aerodynamic loading
Maneuver and Landing Loads
Aircraft Sizing, Structural Layout and Design
Control Surface Design
Aircraft Control Systems and Active Control Technology
Project Management and Finance
Aircraft Stability and Control
Stuctural Stability: Statically Indeterminate Structures; Buckling Analysis; Panel Buckling
Finite Element Design
Research Thesis: Parametric Relationships in the Development of Composite Material Design Data
Performed in conjunction with the Royal Aircraft Establishment Farnborough, United Kingdom, this study comprised:
- the development of potential parametric relationships between various composite materials properties (eg. tensile strength, interlaminar shear strength) based a literature survey of the theoretical bases of failure, and regression analysis of empirical data
- verification of these relationships through coupon testing and subsequent statistical analysis
The study concluded that strong parametric relationships exist between the means of various material properties for a given structural composite, but that differences in the coefficients of variation of these properties rendered the use of these as a design tool problematic. In the course of the study, an interactive design formula was developed that predicts the ultimate bearing strength of any laminate based solely on its layup sequence and longitudinal compressive strength
.Design Thesis: Rudder Design for the T-91 Advanced Training Aircraft
This design project involved the sizing preliminary and detailed design and stress analysis of a rudder for the replacement to the RAF Hawk trainer aircraft. Aerodynamic and inertial loading was derived from specification requirements and test data, and a finite element model of the rudder structure defined. Various competing design concepts were considered, including composite honeycomb structures with graphite/epoxy and E-glass/epoxy skins, and a conventional copper-aluminum alloy rib/skin structure. These were stressed and roughly sized, then compared on the basis of cost, mass, ease of manufacture and maintainability. The E-glass epoxy structure was then subjected to finite element analysis, detailed stressing and fatigue evaluation. Engineering drawings were prepared including production details.
MBA (part-time, commenced 1996, completion 2001):
York University, Toronto, Ontario Ongoing Projects (Top) 
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