Aircraft engine emissions from civil aviation cause several adverse effects to the atmospheric environment. These emissions are among the known major contributors to changes in atmospheric chemistry and global climate change. One way in which the international community has responded to the problem has been the adoption of several international treaties, generally dealing with subjects such as protection of the ozone layer, long-range transboundary air pollution, and global climate change. / The other way in which the problem has been dealt with is the adoption of an industry-specific international regulatory regime for controlling aircraft engine emissions from civil aviation. In this regard, the international community has, through the law making functions of the International Civil Aviation Organization (ICAO), adopted the mechanism of Standards and Recommended Practices (SARPs) to establish a regulatory framework aimed at reducing environmentally harmful engine emissions. These SARPs, though international in nature, are to be implemented at the national level by the member states of ICAO. / This thesis provides a review of current understanding of the effects of aircraft engine emissions on the atmospheric environment and an analysis of the international responses to the problem. In particular, it focuses on the industry-specific regime adopted by ICAO and considers whether it is an effective tool for achieving a balance between the safe and orderly development of civil aviation and the human environment.

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This thesis compares the results of two of the more popular flexible aircraft modeling formulations, the mean-axes method and the fixed-axes method, for application in real-time motion simulators. First, the time-domain equations of motion for an elastic body using the fixed-axes are derived. Subsequently, the mean-axes equations are derived by making a few assumptions from the fixed-axis equations. The two formulations are then implemented for a scaled-up beam model of a Cessna Citation aircraft, with the deformations represented by the modal expansion of the whole aircraft from their respective constrained and free-free finite element solutions. Time-domain results, consisting of the acceleration, velocity, and attitude of a point on the aircraft body, are obtained in both models at two beam-stiffness configurations using a quasi-steady aerodynamic model for a single maneuver at one flight condition. The two methods produced similar results with the fixed-axes formulation producing slightly more accurate results.

This thesis compares the results of two of the more popular flexible aircraft modeling formulations, the mean-axes method and the fixed-axes method, for application in real-time motion simulators. First, the time-domain equations of motion for an elastic body using the fixed-axes are derived. Subsequently, the mean-axes equations are derived by making a few assumptions from the fixed-axis equations. The two formulations are then implemented for a scaled-up beam model of a Cessna Citation aircraft, with the deformations represented by the modal expansion of the whole aircraft from their respective constrained and free-free finite element solutions. Time-domain results, consisting of the acceleration, velocity, and attitude of a point on the aircraft body, are obtained in both models at two beam-stiffness configurations using a quasi-steady aerodynamic model for a single maneuver at one flight condition. The two methods produced similar results with the fixed-axes formulation producing slightly more accurate results.