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Author: Paul T. Millhouse
Publisher:
ISBN: 9781423563648
Category : Airplanes, Military
Languages : en
Pages : 153
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Book Description
Automated techniques for selecting jet engines that minimize overall fuel consumption for a given aircraft mission have recently been developed. However, the current techniques lack the efficiency required by Wright Laboratories. Two noted dependencies between turbine engine fan pressure ratio, bypass ratio, high pressure compressor pressure ratio and overall engine mass flow allows for a reduction in the number of independent design variables searched in the optimization process. Additionally, through the use of spatial statistics (specifically kriging estimation), it is possible to significantly reduce the number of time consuming response function evaluations required to obtain an optimal combination of engine parameters. A micro Genetic Algorithm (microGA) is employed to perform the non linear optimization process with these two computation saving techniques. Optimal engine solutions were obtained. in 25 percent of the time required by previous automated search algorithms.
Author: Paul T. Millhouse
Publisher:
ISBN: 9781423563648
Category : Airplanes, Military
Languages : en
Pages : 153
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Book Description
Automated techniques for selecting jet engines that minimize overall fuel consumption for a given aircraft mission have recently been developed. However, the current techniques lack the efficiency required by Wright Laboratories. Two noted dependencies between turbine engine fan pressure ratio, bypass ratio, high pressure compressor pressure ratio and overall engine mass flow allows for a reduction in the number of independent design variables searched in the optimization process. Additionally, through the use of spatial statistics (specifically kriging estimation), it is possible to significantly reduce the number of time consuming response function evaluations required to obtain an optimal combination of engine parameters. A micro Genetic Algorithm (microGA) is employed to perform the non linear optimization process with these two computation saving techniques. Optimal engine solutions were obtained. in 25 percent of the time required by previous automated search algorithms.
Author: Brian Matthew Yutko
Publisher:
ISBN:
Category :
Languages : en
Pages : 179
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Book Description
Existing commercial aircraft are designed for high mission flexibility, which results in decreased fuel efficiency throughout the operational life of an aircraft. The objective of this research is to quantify the impact of this practice and other non-optimal emergent behaviors of the current global air transportation system. The analysis focuses on improvements that can be made using existing technology. Previous attempts at performing this type of analysis, especially the joint optimization of aircraft design and operations, have been hindered by problem complexity and computational time. In order to overcome these issues and perform the analysis on a global scale, a machine-learning algorithm is used to create a computationally efficient artificial neural network relating aircraft design and off-design mission performance to operational fuel burn and flight time. The data used to train the aircraft performance neural network is generated from an extensive sample of new vehicles optimized for minimum fuel burn on an extremely broad combination of Design Reference Missions (design-payload, -range, and cruise Mach). The resulting comprehensive model of aircraft performance is capable of solving large-scale air transportation network optimization problems. A set of scenarios is analyzed to both establish the limits of the major contributors to system fuel consumption and determine potential realistic benefits from introducing new aircraft with varying design reference missions. Results indicate that approximately 33% of current system fuel consumption is due to the slow retirement and replacement of aircraft in the operational fleet. Additionally, a significant pool of potential fuel burn savings can be realized by designing aircraft closer to their intended operating regime. Multiple large-scale optimization scenarios are presented, including the optimal choice of new aircraft designs for fixed cruise Mach numbers and the globally optimum aircraft choices given any cruise Mach. It is found that reducing design cruise speed can yield system fuel benefits on the order of 7%. Fuel stops are shown as a potentially promising method to operate long-haul missions closer to the maximum fuel efficiency range of an aircraft, and also as a way to mitigate the impact of designing high-efficiency, short-range aircraft that can no longer fly long haul missions directly.
Author: Takahisa Kobayashi
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
In this paper, a model-based diagnostic method, which utilizes Neural Networks and Genetic Algorithms, is investigated. Neural networks are applied to estimate the engine internal health, and Genetic Algorithms are applied for sensor bias detection and estimation. This hybrid approach takes advantage of the nonlinear estimation capability provided by neural networks while improving the robustness to measurement uncertainty through the application of Genetic Algorithms. The hybrid diagnostic technique also has the ability to rank multiple potential solutions for a given set of anomalous sensor measurements in order to reduce false alarms and missed detections. The performance of the hybrid diagnostic technique is evaluated through some case studies derived from a turbofan engine simulation. The results show this approach is promising for reliable diagnostics of aircraft engines.
Author: Augustine R. Dovi
Publisher:
ISBN:
Category : Mathematical optimization
Languages : en
Pages : 36
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Book Description
Author: Jack D. Mattingly
Publisher: AIAA
ISBN: 9781600860164
Category : Aircraft gas-turbines
Languages : en
Pages : 732
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Book Description
Annotation A design textbook attempting to bridge the gap between traditional academic textbooks, which emphasize individual concepts and principles; and design handbooks, which provide collections of known solutions. The airbreathing gas turbine engine is the example used to teach principles and methods. The first edition appeared in 1987. The disk contains supplemental material. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author: Nicholas J. Kuprowicz
Publisher:
ISBN: 9781423552666
Category :
Languages : en
Pages : 82
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Book Description
The integrated multi-objective multi-disciplinary jet engine design optimization program is an analysis tool to aid engineers in the conceptual engine design process. The program allows performance evaluation of a specified engine or a specified aircraft/engine combination at given operating conditions or over a given mission. In addition, the program allows the selection of values for specified engine parameters that yield the best composite performance at one or more operating conditions or over a given mission. Finally, the program utilizes multi-objective optimization techniques to simultaneously address conflicting objectives such as maximizing performance and minimizing fuel use, size, and cost. This report is primarily a software use's guide to provide instruction on using the Integrated Multi-Objective Multi-Disciplinary Jet Engine Design Optimization Program. The genetic algorithm routines used in the program are based on an existing public domain package. The aircraft design program is based on a AIAA sponsored code. The engine performance program is a proprietary DoD limited code.
Author: James D. Heidmann
Publisher: BiblioGov
ISBN: 9781289042967
Category :
Languages : en
Pages : 26
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Book Description
The NASA Environmentally Responsible Aviation (ERA) Project and Fundamental Aeronautics Projects are supporting compressor and turbine research with the goal of reducing aircraft engine fuel burn and greenhouse gas emissions. The primary goals of this work are to increase aircraft propulsion system fuel efficiency for a given mission by increasing the overall pressure ratio (OPR) of the engine while maintaining or improving aerodynamic efficiency of these components. An additional area of work involves reducing the amount of cooling air required to cool the turbine blades while increasing the turbine inlet temperature. This is complicated by the fact that the cooling air is becoming hotter due to the increases in OPR. Various methods are being investigated to achieve these goals, ranging from improved compressor three-dimensional blade designs to improved turbine cooling hole shapes and methods. Finally, a complementary effort in improving the accuracy, range, and speed of computational fluid mechanics (CFD) methods is proceeding to better capture the physical mechanisms underlying all these problems, for the purpose of improving understanding and future designs.
Author: MartÃn Espanã
Publisher:
ISBN:
Category : Flight simulators
Languages : en
Pages : 50
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Book Description
Author: D. Schaechter
Publisher: Elsevier
ISBN: 148329692X
Category : Technology & Engineering
Languages : en
Pages : 447
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Book Description
An important, successful area for control systems development is that of state-of-the-art aeronautical and space related technologies. Leading researchers and practitioners within this field have been given the opportunity to exchange ideas and discuss results at the IFAC symposia on automatic control in aerospace. The key research papers presented at the latest in the series have been put together in this publication to provide a detailed assessment of present and future developments of these control system technologies.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722056407
Category :
Languages : en
Pages : 34
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Book Description
A new technique which converts a constrained optimization problem to an unconstrained one where conflicting figures of merit may be simultaneously considered was combined with a complex mission analysis system. The method is compared with existing single and multiobjective optimization methods. A primary benefit from this new method for multiobjective optimization is the elimination of separate optimizations for each objective, which is required by some optimization methods. A typical wide body transport aircraft is used for the comparative studies. Dovi, Augustine R. and Wrenn, Gregory A. Unspecified Center NAS1-19000; RTOP 505-63-01...
