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.
This project focuses on the concept design and ACS/Geolocation simulation of an Earth-observation microsatellite in Low Earth Orbit. MSCI has a long history of building microsatellites, but not for an Earth observation mission. In this research, we will evaluate the current MSCI multi-mission bus design capability, given its current hardware, for use in the QEYSSat microsatellite mission proposal. QEYSSat is a proposed mission to create a quantum link between ground and space using polarized photons and to transmit encryption keys to ground based users using this link.
Aero-engines are lightweight structures which are assembled of several thin walled cylindrical components (casings). Casings are joined by bolted flanges, and must withstand high forces. To accurately predict the response of casings assembly, the non-linear behavior of the casing joints must be considered. Currently, aero-engine manufacturers (i.e PWC) are facing serious limitations in matching the experimental results with FE models prediction tools of the aero-engine.
Structural and vibration analysis is performed on a proposed design change on electronic assembly to ensure that it meets customer requirements and is a more cost-effective design. Such design change should be cost efficient. The important aspect, in addition to the design, is interacting with different engineers at different positions in the company. Working with mechanical engineers and suppliers in achieving such targets and ensuring the work done is viable and on track.
The aeronautic and aerospace industries are exploring new approached to reduce the mass of cables, bulky electronic systems. This rationally leads onto aircraft weight reduction as well as the amount of CO2 and greenhouse gas emitted by aircrafts. To reduce the mass of cables, merging/embedding different electronic systems in a single chip is an alternative. In this approach, massive electronic modules are miniaturized in a so-called SoC. Different SoCs can be embedded in a single package called SiP.
Electronic assemblies are used to control various systems in an aircraft. Under normal operating conditions, these assemblies undergo vibration, and therefore have an expected life span. Different designs are analyzed to reduce production cost, and these designs have to ensure that the electronic components contained within the hardware can tolerate the same operating conditions without failure. With time continuous research projects are being conducted to produce products with the same quality and lower costs, and this is one of them.
This research project studies a specific component in the commercial aircraft engine called the squeezed film damper, or SFD. The SFD is applied to reduce the vibration of the engine rotor, which in turn reduces the noise and brings comfort to the passengers. The expected delivery from this project includes an advanced SFD model which will be used by P&WC for the simulation of engine vibration. The developed model can also be studied as the guideline for an upgraded level of SFD design.
This project aims to develop a novel information-technology platform to improve the effectiveness of emergency response in disaster areas, ultimately saving lives. In case of any emergency response, the local communication infrastructure cannot be generally relied upon: therefore, we propose a distributed, self-organizing information system based on off-the-shelf mobile devices, supported by self-organizing, self-deploying UAVs.
With the rise in fuel prices, operators are constantly pushing aircraft manufacturers to find new ways to reduce their aircrafts operating costs. One of the objectives of this project is to create a Bombardier toolkit for the C Series. This will allow the operators to input parameters such as the miss-rigging present on their control surfaces, missing components, damage that occurred to the aircraft during flight or on the ground. Using Bombardiers proprietary information, the fuel burn occurring due to these issues can be computed.
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 structures stability.