Browsing by Author "Eshelby, M. E."
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Item Open Access The application of computational techniques to the design of thermal ice protection systems(1990-03) Leah, C. W.; Eshelby, M. E.A bibliography citing 1350 references related to all aspects of aircraft icing is presented. An ice adhesion database has been compiled, and a survey of ice adhesion test rig designs is presented. An ice shear adhesion test rig is designed, manufactured and operated. The results are added to and compared with those in the database. The adhesion of ice accreted on metal and non-metallic composite aircraft propeller blades in flight is assessed. A one-dimensional thermodynamic study of ice accreted on a non-metallic composite propeller blade with ’built-in1 electrothermal de-icing system is effected and compared with a solid metal blade. A two-dimensional aerofoil icing prediction program is modified and executed in series with additionally created software to predict icing on aircraft engine air intake duct lips in flight. Hence a new de-icing system design method is developed to replace and improve upon an existing one. Validation of the new design method is initiated and a programme for its completion is presented. Icing predictions produced using the new method correlate well with expected values derived by several methods. The new design method is incorporated in the sponsoring companies business with an appropriate computer hardware/software system and employed, in parallel with the ’old’ approach (till validation completion), on commercial projects. Market response indicates a definite preference for the new design method. The ’non-technical’ and other related practical topics of implementing the new de-icing system design method, including specification and installation of computer hardware and software are discussed. Marketing, financial and other commercially oriented subjects are addressed in justifying the research and the implications of introducing the new design method into the commercial business of the sponsoring organisation are considered. This research programme forms a part of a large, long term icing research commitment. Continued research subjects and investigative routes including the integration of ice adhesion mechanical characteristics into the de-icing system design method are discussed together with their relationship to this and the overall icing research plan.Item Open Access Design and development of an algorithm for a take-off performance monitor(Cranfield University, 2001-02) Zammit-Mangion, David; Eshelby, M. E.A take-off performance monitor is an instrument that is intended to monitor the progress of the take-off manoeuvre in real-time in order to ensure that the aircraft will meet the various distance constraints of the airfield. Several designs have to date been proposed but none have been successful commercially. This work has involved the development of a novel design concept based on the consideration of the time history of the run to obtain an accurate prediction of the distance required to VI. Scheduled post-VI distances are then allowed for in the estimate of the actual distances required to complete the manoeuvre. A performance standard complementing SAE aerospace standard AS-8044 has also been established to ensure system reliability during operation. The algorithms developed were validated using the College of Aeronautics' Jetstream-100 flying laboratory and take-off data of B747 and B737 aircraft. A fixed-base simulator was also used to evaluate the algorithm in adverse operating conditions. The algorithm was demonstrated to meet the named performance standards and is shown to have the potential of being utilised in a successful commercial performance monitor. A novel display design concept is also proposed, providing a basis on which an attractive display can be further developed.Item Open Access A non-linear analysis of the longitudinal static stability of light, multi-engined aircraft(Cranfield University, 1979-01) Eshelby, M. E.The longitudinal handling qualities of light aircraft have traditionally been assessed in terms of the slope of the static stability trim curves. This method of assessment is simple in terms of analysis as well as being a relatively easy task for the pilot to perform. The theory is however based on a simple linearised model of . the aircraft'and omits, amongst other things, the effects of power. A comparison between the estimated and measured trim curves of a typical light aircraft shows that the linearised theory severely overestimates its static stability. A design based on the linear assumptions would be unlikely to comply with airworthiness requirements. In Part II the main omissions from the linearised model are considered individually and their effect on the trim curves found. In Part I the individual contributions from Part II are used to complete the full, non-linear, trim equations and these are solved in terms of elevator angle and incidence to trim, n and ä. The solution shows that the non-linear analysis provides a good simulation of the flight measured trim curve data thus verifying the methods of estimation developed in Part II. The trim curves are considered in terms of incidence and lift coefficient and show that assumption of a linear lift-incidence relationship may cause some misleading interpretations of the trim curves drawn in terms of lift coefficient.