2026-09-19T02:02:06Zhttps://dspace.mit.edu/server/oai/request

oai:dspace.mit.edu:1721.1/166532022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023

Karen E. Willcox. Barter, Garrett E. (Garrett Ehud), 1979- Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics 2005-05-17T14:48:32Z 2005-05-17T14:48:32Z 2004 2004 http://hdl.handle.net/1721.1/16653 56524351 Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004. Includes bibliographical references (p. 83-86). This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections. Design and regulatory initiatives for aircraft noise and emissions should appreciate the integrated nature of the aircraft system. The computational ability exists to consider environmental and traditional performance objectives of aircraft concurrently. This context of multi-disciplinary system design is named the Environmental Design Space (EDS) and is studied in this thesis with an integrated aircraft-engine conceptual design framework. With this tool, the objectives of this thesis were to assess the fidelity and level of uncertainty of the design framework, to characterize the tradeoffs between aircraft noise, emissions and aircraft performance and to evaluate the system-level impacts of a future noise reduction technology. Assessment of the EDS framework was accomplished with a probabilistic model assessment methodology. The assessment involved the selection of stochastic inputs and generation of output distributions through Monte Carlo simulations. A sensitivity analysis of the key drivers of uncertainty and the user-defined input distributions is also provided. This methodology was applied to one of the framework modules, the NASA Engine Performance Program (NEPP), and found that the modeling error was subsumed within the modeling uncertainty. A sensitivity study indicated that the component efficiencies had the largest impact on the output distribution. When the level of NEPFP uncertainty was propagated to the system level, the resulting coefficient of variance for fuel burn was 4.1%. The tradeoffs between the competing EDS objectives were characterized through Pareto fronts generated by multi-objective genetic algorithms. (cont.) The quantification of these trades for a given aircraft, 8 dB in cumulative EPNL vs. 8kg of LTO-NO[sub]x for example, give designers and regulators supporting information for their decisions. A future noise reduction technology, fan trailing edge blowing, was also evaluated at the system level. A probabilistic analysis of the technology design in the EDS framework revealed poor tolerance of engine cycle variability. A robust design procedure was employed, and showed that while the technology offered a flyover noise reduction of 11.9 dB, it incurred a fuel burn and LTO-NO[sub]x penalty of 2.8% and 11.0%, respectively. by Garrett E. Barter. S.M. 86 p. 1920926 bytes 1919167 bytes application/pdf application/pdf eng Massachusetts Institute of Technology M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 Aeronautics and Astronautics. Exploration and assessment of the environmental design space for commercial aircraft and future technologies Thesis application/pdf false Publication unknown unknown <Publication xmlns="https://www.openaire.eu/cerif-profile/1.1/" id="7af637e1-cd0b-4f06-ae5d-2d099ff975f9"> <Type xmlns="https://www.openaire.eu/cerif-profile/vocab/COAR_Publication_Types">http://purl.org/coar/resource_type/c_1843</Type> <Language>eng</Language> <Title>Exploration and assessment of the environmental design space for commercial aircraft and future technologies</Title> <PublishedIn> <Publication> </Publication> </PublishedIn> <PublicationDate>2004</PublicationDate> <Authors> <Author> <DisplayName>Barter, Garrett E. (Garrett Ehud), 1979-</DisplayName> <Affiliation> <OrgUnit> </OrgUnit> </Affiliation> </Author> </Authors> <Editors> </Editors> <Publishers> <Publisher> <DisplayName>Massachusetts Institute of Technology</DisplayName> <OrgUnit /> </Publisher> </Publishers> <License>http://dspace.mit.edu/handle/1721.1/7582</License> <Keyword>Aeronautics and Astronautics.</Keyword> <Abstract>Design and regulatory initiatives for aircraft noise and emissions should appreciate the integrated nature of the aircraft system. The computational ability exists to consider environmental and traditional performance objectives of aircraft concurrently. This context of multi-disciplinary system design is named the Environmental Design Space (EDS) and is studied in this thesis with an integrated aircraft-engine conceptual design framework. With this tool, the objectives of this thesis were to assess the fidelity and level of uncertainty of the design framework, to characterize the tradeoffs between aircraft noise, emissions and aircraft performance and to evaluate the system-level impacts of a future noise reduction technology. Assessment of the EDS framework was accomplished with a probabilistic model assessment methodology. The assessment involved the selection of stochastic inputs and generation of output distributions through Monte Carlo simulations. A sensitivity analysis of the key drivers of uncertainty and the user-defined input distributions is also provided. This methodology was applied to one of the framework modules, the NASA Engine Performance Program (NEPP), and found that the modeling error was subsumed within the modeling uncertainty. A sensitivity study indicated that the component efficiencies had the largest impact on the output distribution. When the level of NEPFP uncertainty was propagated to the system level, the resulting coefficient of variance for fuel burn was 4.1%. The tradeoffs between the competing EDS objectives were characterized through Pareto fronts generated by multi-objective genetic algorithms.</Abstract> <Abstract>(cont.) The quantification of these trades for a given aircraft, 8 dB in cumulative EPNL vs. 8kg of LTO-NO[sub]x for example, give designers and regulators supporting information for their decisions. A future noise reduction technology, fan trailing edge blowing, was also evaluated at the system level. A probabilistic analysis of the technology design in the EDS framework revealed poor tolerance of engine cycle variability. A robust design procedure was employed, and showed that while the technology offered a flyover noise reduction of 11.9 dB, it incurred a fuel burn and LTO-NO[sub]x penalty of 2.8% and 11.0%, respectively.</Abstract> <Access xmlns="http://purl.org/coar/access_right" > </Access> </Publication>