Extension of AWSOM to Strut-Braced Wings

Bombardier is interested in investigation a novel aircraft configuration known as the strut-braced wing configuration, which is has the potential for improved fuel efficiency relative to current tube and wing aircraft. However, Bombardier’s preliminary multipdisciplinary design optimization tools need to be extended in order to be applicable to this configuration. The intern will extend the capabilities of Bombardier’s tools to enable sizing of strut-braced wing.

Virtual testing of composites in aerospace

Canada’s aerospace industry relies on expensive and time-consuming testing campaigns to introduce new composites or obtain baseline material properties. Design allowables (e.g., strength used in design phases) are obtained from empirical knock-down factors that account for temperature, environment, etc. This approach is over-conservative and disconnected from physical grounds; it also leads to situations where different teams in the same company (e.g., Bombardier) use different factors for the same part. Having accurate predictive models could reduce testing and decrease knock-down factors.

AVIO 1603: Cosmic radiation In-flight Measurement and real-time analysis for Electronic Systems and passenger protection (CIMES)

Due to increasing miniaturization, future systems will be made of components that are more energy efficient and at the same time more sensitive to external radiation. To ensure that future systems remain protected against cosmic radiation and single events, aircraft and flight systems manufacturers must collect in-flight data for cosmic radiations and develop a global strategy for real-time processing of this data to provide pilots, crew and aircraft operations, with appropriate information to help them make the right decisions in case of unusually high cosmic radiation exposure.

Buckling Analysis of Hybrid Composite-Metallic Stiffened Structures

In order to reduce the structural weight and operating cost of the aircraft, hybrid structures composed of composite skins and metallic sub-structures are commonly used as components of the wing and fuselage. The skin temperature change of the aircraft during takeoff and landing causes different amounts of deformation in composite and metallic materials due to their difference in thermal expansion properties. This induces internal loads in such hybrid structures, which need to be considered together with the flight loads when evaluating the structure’s stability.

Analysis of the implementation of a Model-Based Systems Engineering approach for the conceptual design of advanced aircraft high-lift system architectures

Today, the development of complex products such as aircraft systems is still mainly based on a paper-based requirements and development process which leads to delays, cost overrun and sometimes failure to respond to customer needs. A structured, model-based design approach is considered promising to bring innovation and optimization in systems architectures. The project aims to demonstrate the value of a model-based systems engineering approach opposed to a traditional bottom-up approach for the example of advanced aircraft high-lift system architectures.