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Home>Products>Journal and Reviews>I.RE.AS.E.>Latest issue International Review of Aerospace Engineering - December 2009 - Papers
International Review of Aerospace Engineering - Papers
Abstract - This paper presents the experimental results on the flow characteristics of a 15º slanted entry Convergent-Divergent (CD) nozzle with a design Mach number of 2.94 exposed to M = 1.6, 1.8 and 2.0 streams. The 15º slanted entry nozzle results are compared with the results of identical geometry straight entry nozzle. The objective is to check whether a slanted entry nozzle, kept in a supersonic flow, with a detached shock present at its mouth, can choke and deliver supersonic flow. The results show that the nozzle can choke and deliver supersonic flow. The present study also explores the flow separation inside a slanted entry supersonic nozzle when it is exposed to a supersonic stream. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Slanted Entry Nozzle, Flow Separation, Schilling Relation, Shock and Flow Deflection Angle.
Abstract - Continuous Descent Approach (CDA) procedures for aircraft coming to an airport have proved their potential for reducing noise impact on the airport environment. During a CDA procedure, the aircraft keeps a specific altitude until it reaches top of descent (TOD), where it adopts a configuration that allows for continuous descent, i.e. with no “step-down” effects, without changing its status during approach, changing the speed and path profiles according to aircraft performance. A major problem faced when these procedures are applied in real scenarios is how compatible they are with conventional or staggered procedures. This article uses the aircraft total energy model (TEM) for a mathematical approach of aircraft descent, which allows for establishing their vertical, speed and thrusting profiles for a CDA-flying aircraft with fuel consumption and aerodynamic drag information provided by the Base of Aircraft Data (BADA).The purpose here is to have a simple, open tool to analyse the descent profiles of different aircraft into airports. This would enable us to predict the path followed by an aircraft from its dynamic state at descent launch, considering idle thrust and constant vertical. On the basis of the mathematical model and the computer-based development of the vertical and speed profiles followed by aircrafts, this article defines procedures that can be applied in a congested airport –like Madrid Barajas – so that its impact on real operation can be analysed as it is made compatible with conventional procedures. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Air Transport, Environmental Impact, Modeling.
Abstract - This paper deals with the vibration analysis of a 1.3 mm aluminium aircraft panel which is fitted to the aircraft frame of a Coast Guard helicopter for the purpose of housing new retrofits. The total mass of the retrofits is approximated at 5 kg and thus its vibration behaviour during flight will be of major concern. Ground vibration test was conducted whereby the natural frequencies of the panel board loaded with the retrofits are identified and checked against the operational frequencies of the aircraft. If they coincide, resonance may occur. It was found that several critical vibration modes that lie in the vicinity of the operating frequencies of the aircraft existed. Further in-flight vibration test was performed to ensure the vibration levels are not excessive. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Vibration Analysis, Resonance, Instrument Panel, Natural Frequencies.
Abstract - This paper presents the equations that govern the dynamic behavior of two aircraft that are flying in formation while one of them is being refueled by the other in mid-flight. During aerial refueling, large quantity of fuel is transferred from one vehicle to the other in a relatively short time. The resulting change in mass and the related change in aircraft inertia properties can affect the dynamics of the aircraft system during fuel transfer. This work exploits results obtained by the control volume method of equation derivation for variable mass systems to develop a compact set of equations of motion that can be used for an analytical study of in-flight refueling. The equations derived include the effects of variations in receiver mass and inertia on the dynamics of the aircraft system. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Aerial Refueling, Aircraft Dynamics, Variable Mass Systems.
Abstract - Blade failures are observed ever since Frank Whittle faced problems with his W2 jet engine development during the II World War. They continue to happen even now with advances in engine designs. Stress based and Strain based life estimation help in design stage; however a failure always has a tell-tale story of Fracture with Crack Initiation and Propagation that embeds all the clues of how the failure occurred. A study of this fracture surface helps in understanding the underlying phenomena in the machine causing the failure. Here a case study is described in understanding a blade fracture through a process driven tool “TurboManager” developed with several modules as a turbine life estimation work bench for the rotating machine components. It is shown how such a tool helps in blade failure investigation. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Quality Costs, Disruption Management, Airline Operations, Agents, Multi-Agents.
Abstract - Nesting is a process where shapes are orientated and located on a parent substrate. Effective nesting packs the parts optimally and maximizes the remnant on the substrate. The paper describes how Simulated Annealing was made to operate effectively as the optimisation process on aerospace components. Key issues affecting the use of Simulated Annealing are described. The methods described were integrated into a software package and applied to the Aerospace Industry. The method operated in real time and produce quality nesting solutions. Copyright © 2009 Praise Worthy Prize S.r.l. - All rights reserved
Keywords: Optimisation, Simulated Annealing, Aerospace Components.
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