Airplane engine selection by optimization on surface fit approximations

Healy, M. J. R.; Kowalik, Janusz S.; Ramsay, James W.

doi:10.2514/3.44477

Cited by 29 publications

(16 citation statements)

References 3 publications

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“…x R Chi and Bloebaum [61] x x R Englund et al [62] x x 2nd x Gadallah and ElMaraghy [63] x x 2nd x x x S/N Giunta et al [64] x x 2nd x Giunta et al [65] x x x x 2nd x Healy et al [66] x x 2nd x x Hong et al [67] x x 2nd x x S/N Koch et al [68] x x 2nd x Korngold and Gabriele [69] x 2nd x Li et al [70] x 2nd x x S/N Mavris et al [71] x x 2nd R Mavris et al [72] x x 2nd R Roux et al [57] x…”

Section: Doe Rsm and Taguchi's Robust Designmentioning

confidence: 99%

“…Several authors have reported statistical measures (e.g. F-statistics and root mean square error) to verify model adequacy; see Healy et al [66], Unal et al [77,78], Koch et al [68], Venter et al [56] and Welch et al [37]. However, these measures have no statistical meaning, since they assume the observations include a random error term with a mean of zero and a non-zero standard deviation.…”

Section: A Closer Look At Experimental Design For Deterministic Compumentioning

confidence: 99%

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Metamodels for Computer-based Engineering Design: Survey and recommendations

Simpson

Poplinski

Koch³

et al. 2001

EWC

1,593

919

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Section: Doe Rsm and Taguchi's Robust Designmentioning

confidence: 99%

Section: A Closer Look At Experimental Design For Deterministic Compumentioning

confidence: 99%

Metamodels for Computer-based Engineering Design: Survey and recommendations

Simpson

Poplinski

Koch³

et al. 2001

EWC

1,593

919

View full text Add to dashboard Cite

“…... To try to circumvent this problem a Latin square technique was used." (61) The 'Latin square technique' resembles a least-squares fitting procedure and is described by Healey et al (68) .…”

Section: Class III Synthesis Approach (Computer Automation)mentioning

confidence: 99%

Evolution of generic flight vehicle design synthesis

Chudoba¹,

Heinze

2010

Aeronaut. j.

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the next generation of aerospace life-cycle synthesis systems, a software and management process capable to immediately calculate cost and time implications while simultaneously linking design, manufacturing, testing, and operation. A historical review of how design has been accomplished until today is presented. The design approaches are categorised and the characteristics of today's stateof-the-art design synthesis systems are discussed. A specification for the new class of intelligent generic design synthesis systems is presented capable of satisfying the demands imposed by the new breed of high-performance aircraft, space access vehicles, space missions, and others. Finally, the development status of the next generation aerospace vehicle design synthesis (AVDS-PrADO) simulation-based acquisition environment is presented. NOMENCLATURE AVDaerospace vehicle design AVDS aerospace vehicle design synthesis BWB blended-wing body C certification CAD computer-aided design CAM computer-aided manufacturing CD conceptual design CFD computational fluid dynamics ABSTRACTWhen defining a new product like an aircraft, space access vehicle or space mission, the Advanced Projects Group evaluates the available design space and compares it with the design space required to accomplish the specified mission. As with any product development process, the general life-cycle characteristics are established first during the conceptual design (CD) phase, clearly before a design proposal can be released to the follow-on design phases such as preliminary design (PD), detail design (DD), flight test (FT), and finally operation and disposal. As a rule of thumb, it can be assumed that around 80% of the flight vehicle configuration and mission tandem are determined during the CD phase alone, which is the key phase where the initial brainstorming has to take place. Clearly, it is the responsibility of the CD team to simulate the entire life-cycle of the project from 'cradle to grave' where the focus is on correctness rather accuracy in order to identify the design space and offer an overall proof of design convergence. Currently, the important primary aerospace vehicle and mission design decisions at CD level are still made using extremely simple analysis and heuristics. A reason for this scenario is the difficulty in synthesising the range of individual design disciplines for both, classical and novel aerospace vehicle conceptual designs, in more than an ad hoc fashion.Although the CD segment is seen as the most important step in the product development phase due to its pre-defining function, it is the least well understood part of the entire product evolution process due to its level of abstraction. This paper presents the roadmap towards 'Managerial implication of computerised aircraft design synthesis' -revisitedThe potential of computerised synthesis on product development is well recognised in the multi-disciplinary analysis (MDA) and multidisciplinary optimisation (MDO) engineering domains. However, it appears that the implications of to...

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“…Suction is provided by six ram-air turboshaft The preceding definition of the LFC systems and configuration provided the baseline airplane for a wing geometry/cruise speed optimization study. The technique used 3 consists of the five sequential steps shown in Fig. 4.…”

Section: Lfc Wing Optimizationmentioning

confidence: 99%

Application of Laminar Flow Control to Large Military Transports

Jobe

Kulfant

Vacha

1979

Journal of Aircraft

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A study of performance increase that could result from applying advanced aerodynamic concepts to large, long-range military transport aircraft showed that laminar flow control (LFC) offered the largest potential. A more in-depth design study then investigated the impact of LFC on the performance, weight, fuel consumption, and economics of a military transport designed to carry 350,000 Ib 10,000 nmi. Tlte design study identifies the optimum wing planform and cruise speed, the relative performance increases from different amounts of LFC, and sensitivities to the major LFC uncertainty items; i.e., increased systems weight, complexity, and maintenance, which can only be quantified by design, development, and flight test.

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Airplane engine selection by optimization on surface fit approximations

Cited by 29 publications

References 3 publications

Metamodels for Computer-based Engineering Design: Survey and recommendations

Metamodels for Computer-based Engineering Design: Survey and recommendations

Evolution of generic flight vehicle design synthesis

Application of Laminar Flow Control to Large Military Transports

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