- About
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The Global ETD Search service is a free service for researchers
to find electronic theses and dissertations. This service is
provided by the
Networked Digital Library of Theses and Dissertations.
Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
Search results
Showing 31 to 40 of 719 (0.016 seconds)| 31 |
Development of a validated computational procedure for the analysis of diesel engine inlet manifold flows with exhaust gas recirculation : predicaments, perceptions and policy-responsesPage, Vivian J. January 2002 (has links)
No description available.
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Stability effects of heat and mass transfer on thin liquid filmsAnderson, Harry January 2002 (has links)
No description available.
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Recognition of the immediate driving environmentWilson, Malcolm Baxter January 2002 (has links)
No description available.
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Evaluation of the GTA and plasma welding process applied to Ti-6Al-4V for aerospace applicationsMcGillicuddy, K. January 2002 (has links)
No description available.
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The development of usability scales for flight management systemsLane, Karen P. January 2002 (has links)
No description available.
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Investigation into the hovering flight dynamics and control of a flapping wing micro air vehicleLoh, K. January 2003 (has links)
The hovering flight of a micro air vehicle was investigated. Various flight control concepts, inspired by observation of insect and bird flight, were investigated in some detail. The concepts make use of flap frequency or phase between the flap and pitch attitudes of the wing to control the force magnitude. Tilt of the stroke plane or fuselage was used to vector the force. A flight control system was designed for each concept investigated. The investigation has revealed that the preferred control concept is one in which force vectoring is achieved by the fuselage tilt through a shift in the centre of gravity location while the force magnitude is controlled by the phase between pitch and flap attitudes. This has the advantage of reducing the vehicle weight while at the same time relaxing the demand of extremely high frequency actuators. The equations of motion based on a multi-body representation of a flapping wing micro air vehicle were derived and these form the basis for the SIMULINK flight simulation program used to carry out the above investigation. The aerodynamic model used for the simulation was obtained from force measurements with a flapping mechanism that allows the model wing to oscillate with two degrees of freedom (flap and pitch). During these measurements, the phase angle between the flap and pitch angles of the model wing was varied to determine the effects on the force magnitude and direction.
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Enhancing lift on a three element high lift aerofoil system by installing air jet vortex generatorsLewington, Neil January 2001 (has links)
No description available.
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The application of material requirements planning (MRP) system to aircraft parts inventoryGhobbar, Adel Abulgassem January 2001 (has links)
No description available.
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| 39 |
The non-linear modelling of squeeze film damped rotor-dynamic systems : an efficient integrated approachBonello, Philip January 2002 (has links)
No description available.
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| 40 |
Development of sensor technology to facilitate in-situ measurement of damage in composite materials for spacecraft applicationsMowlem, Matthew Charles January 2002 (has links)
No description available.
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