High Fidelity MDO Process Development and Application to Fighter Strike Conceptual Design

Davies, Clifton; Stelmack, Marc A.; Zink, Scott; Garza, Antonio De La

doi:10.2514/6.2012-5490

Cited by 18 publications

(8 citation statements)

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“…1) 6 . The configuration selected for this paper has a total length from nose to tail of 64 ft., wingspan of 63 ft. with aspect ratio 4, and an estimated take-off gross weight of 69,000 lb.…”

Section: Notional Vehiclementioning

confidence: 98%

“…The total pitch stiffness is the difference between the augmented and the clean vehicle pitch stiffness, so to command an angle of attack for a pitch up maneuver, the pitch moment coefficient must be (6) with the commanded angle of attack determined by 1 (7) Similarly, to overcome a vertical gust (idealized as an increase to angle of attack):…”

Section: B Controllability Analysismentioning

confidence: 99%

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Aerodynamic Modeling Techniques for Efficient Supersonic Air Vehicle Multidisciplinary Design Optimization

Meckstroth

Alyanak

Lindsley

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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A comparative analysis of aerodynamic modeling techniques for potential use in the multidisciplinary design optimization (MDO) of next generation Efficient Supersonic Air Vehicles (ESAVs) is presented. These vehicles will likely be tailless, with unique challenges in lateral control requiring the use of multiple unconventional control effectors. However, with no previous examples and no empirical knowledge in which to base these designs, the analysis of these effectors must be validated. In addition, for inclusion in the overall design optimization routine, the analysis must balance a tradeoff between fidelity of the solution and computation time. This paper explores this tradeoff, comparing multiple analysis techniques, ranging from linear panel methods to Reynolds averaged Navier-Stokes solutions. The paper applies these tools to a representative ESAV with different forebody shapes. Additionally the impact of body tabs deployed on these different forebody configurations is investigated. Finally the required control authority to meet level one flying qualities is quantified and compared to that available for each configuration. Nomenclature= pitch moment coefficient at zero degrees angle of attack = pitch moment coefficient derivative with respect to angle of attack = angle of attack required for trimmed flight = pitch moment coefficient required for trimmed flight = frequency of short period mode = damping ratio of short period mode = augmented pitch stiffness required to meet short period flying qualities requirements , , = moments of inertia = dynamic pressure , , = reference wing span, chord, area = body axis dimensional vertical force derivative with respect to angle of attack = freestream total velocity = commanded angle of attack = pitch moment coefficient required to command an angle of attack 2 = commanded g-loading = aircraft weight = lift curve slope = gust velocity = angle of attack change due to vertical gust = pitch moment coefficient required to reject vertical gust = roll moment coefficient required to meet rolling flying qualities requirements = roll angle = dimensional roll moment derivative with respect to roll rate = yaw moment coefficient required for roll initiation = yaw moment coefficient derivative with respect to roll rate = roll moment coefficient derivative with respect to roll rate = pitch moment coefficient required for roll coordination = roll rate = augmented yaw moment derivative with respect to sideslip required for dutch roll = frequency of Dutch roll mode = damping ratio of Dutch roll mode = dimensional yaw moment derivative with respect to sideslip = sideslip angle change due to lateral gust = yaw moment coefficient required to reject lateral gust = yaw moment coefficient derivative with respect to sideslip = sideslip angle due to crosswind = yaw moment coefficient required to overcome crosswind = roll moment coefficient derivative with respect to sideslip = roll moment coefficient required to overcome crosswind

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Section: Notional Vehiclementioning

confidence: 98%

Section: B Controllability Analysismentioning

confidence: 99%

Aerodynamic Modeling Techniques for Efficient Supersonic Air Vehicle Multidisciplinary Design Optimization

Meckstroth

Alyanak

Lindsley

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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“…To this date, the structural analyses are solely focused on the wing [27,36], and their main advantage within a MDO framework is that they can be used either to directly calculate the strength [27,44] or to provide additional data for further static as well as dynamic aeroelastic computations [48,49]. Finally, the propulsion specifications can be expressed in high-fidelity applications through a dedicated simulation model that considers the entire [12,17,26,[50][51][52][53] or an isolated part [38,54,55] of the engine's operation, but for faster optimizations, it is also efficient to use statistical approximations [43,45] or "rubberized" engines by means of scaling factors [16,32,56].…”

Section: Disciplinary Modelsmentioning

confidence: 99%

“…On the downside, such complex integration can pose a number of challenges for the MDO process, and in fact, it can be seen that there is no obvious figure of merit that can be used as an objective, while at the same time, it is often necessary to perform numerous, and possibly unaffordable, analyses in order to cover the entire flight envelope [28]. To this end, the coupling between aerodynamics, structures, and flight mechanics has shown very promising results for the overall design quality [29,33,36,76,77], and the most notable methods of integration include the decomposition of the mission into different segments [28], the alleviation of loads through aeroservoelastic optimization [51,75], the exploration of innovative control configurations [43,78], and the assessment of handling qualities through the incorporation of military standards [28,67,78].…”

Section: Alternative Modelsmentioning

confidence: 99%

“…To this end, there are several techniques which aim to make the aeroelastic analysis more efficient, and it has been shown that significantly faster results can be obtained if the estimation of the aerodynamic loads is replaced with a metamodel [46,51,90] or if several load cases are distributed in parallel computers [35]. In addition to this, it can be seen that it is possible to use interpolation splines based on a radial basis function (RBF) in order to effectively transfer the aerodynamic loads and consequently reduce the mesh connectivity incompatibilities between CFD and CSM when complex configurations must be considered [32, 35, 36, 45, 48, 62-64, 68, 91].…”

Section: Analysis Capabilitiesmentioning

confidence: 99%

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Multidisciplinary Design Optimization of Aerial Vehicles: A Review of Recent Advancements

Παπαγεωργίου

Tarkian

Amadori

et al. 2018

International Journal of Aerospace Engineering

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The aim of this paper is to present the most common practices in multidisciplinary design optimization (MDO) of aerial vehicles over the past decade. The literature sample is identified through established internet search engines, and a stringent review methodology is implemented in order to ensure the selection of the most relevant sources. In this work, the primary emphasis is on the assessment of the state-of-the-art framework development strategies, while at a secondary level, the objective is to identify the possible improvement directions by evaluating the research trends and gaps. As an additional contribution, statistical studies are also provided, and it is shown how MDO of aerial vehicles has evolved in terms of problem formulation, disciplinary modeling, analysis capabilities, tool implementation, and general applicability. Given this foundation as well as the results of the review, this work concludes by presenting a roadmap for guiding academia and industry in respect to the application of MDO on aerial vehicles. Overall, the roadmap together with the literature review is not only expected to serve as a guide for newcomers into the MDO field but also as an elementary basis which will allow researchers to conduct additional studies in this important and constantly evolving area of design.

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Future aircraft concepts and design methods

McDonald¹,

German

Takahashi

et al. 2021

Aeronaut. j.

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With an annual growth in travel demand of about 5% globally, managing the environmental impact is a challenge. In 2019, the International Civil Aviation Organisation (ICAO) issued emission reduction targets, including well-to-wake greenhouse gas (GHG) emissions reduced at least 50% from 2005 levels by 2050. This discusses several technologies from an aircraft design perspective that can contribute to achieving these targets. One thing is certain: aircraft will look different in the future. The Transonic Truss-Braced Wing and Flying V configurations are promising significant efficiency improvements over conventional configurations. Electric propulsion, in various architectures, is becoming a feasible option for general aviation and commuter aircraft. It will be a growing field of aviation with zero-emissions flight and opportunities for special missions. Lastly, this paper discusses methods and design processes that include all relevant disciplines to ensure that the aircraft is optimised as a complete system. While empirical methods are essential for initial design, Multidisciplinary Design Optimisation (MDO) incorporates models and simulations integrated in an optimisation environment to capture critical trade-offs. Concurrent design places domain experts in one site to facilitate collaboration, interaction, and joint decision-making, and to ensure all disciplines are equally considered. It is supported by a Collaborative Design Facility (CDF), an information technology facility with connected hardware and software tools for design analysis.

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High Fidelity MDO Process Development and Application to Fighter Strike Conceptual Design

Cited by 18 publications

References 0 publications

Aerodynamic Modeling Techniques for Efficient Supersonic Air Vehicle Multidisciplinary Design Optimization

Aerodynamic Modeling Techniques for Efficient Supersonic Air Vehicle Multidisciplinary Design Optimization

Multidisciplinary Design Optimization of Aerial Vehicles: A Review of Recent Advancements

Future aircraft concepts and design methods

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