Optimization Assisted Structural Design of a New Military Transport Aircraft

Schuhmacher, G.; Stettner, M.; Zotemantel, R.; O’Leary, Owen L.; Wagner, Markus

doi:10.2514/6.2004-4641

Cited by 20 publications

(8 citation statements)

References 3 publications

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“…A current example of strain-energy-based topology optimization in industrial practice is given by [6], which presents an investigation of the rear fuselage structure of the Airbus A400M transport aircraft. A topology optimization is used to find a solution with minimum compliance for multiple load cases, with the objective of minimizing the structural mass.…”

Section: Nomenclaturementioning

confidence: 99%

“…The topology-optimization approaches of [6,7] optimize topologies for minimum compliance, but not necessarily for a Pareto-optimal design under consideration of additional design constraints and limitations. This shows that the application of multicriteria optimizations, considering all relevant criteria in a single optimization step, is rare for aircraft structures, especially when it comes to real-world problems with an appropriate level of detail.…”

Section: Nomenclaturementioning

confidence: 99%

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Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Hansen¹,

Häusler²,

Horst³

2008

Journal of Aircraft

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In industrial practice, innovative structural aircraft design is, on the one hand, driven by several design criteria like static stress, damage tolerance, and stability, and, on the other hand, by new manufacturing methods and materials, which promise beneficial effects on manufacturing costs and weight. Published optimization approaches are mostly based on pure static stress criteria, albeit the important influence of stability and damage tolerance is neglected. This assumption is perilous but significantly simplifies the investigation. The investigation of unconventional designs under consideration of the preceding criteria is challenging because no analytical or handbook solutions are available. This paper introduces an optimization approach based on an evolution strategy, which incorporates multiple criteria by using nonlinear finite-element analyses for stability and a set of linear analyses for damage-tolerance evaluation. To demonstrate the approach, one design investigation is presented for the window area of a generic aircraft fuselage. The definition of dimensions and the choice of an ideal topology define the optimization problem. The chosen fuselage structure uses an integral design with an innovative combination of window and circumferential frame and is investigated with regard to three load cases that represent relevant in-flight conditions derived from global finite-element analyses. NomenclatureA, B, k, C f , n f , K c = Forman coefficients a = crack length a m , b m , m = shape coefficients of the mass mapping function a u , b u = shape coefficients of the deflection mapping function a SIF , b SIF = shape coefficients of the fatigue-response mapping function C feas , D feas = coefficients of the failure mapping function, feasible state C limit , D limit = coefficients of the failure mapping function, limit state d i = design response i E = Young's modulus G I = energy release rate, mode I G II = energy release rate, mode II g = gravitational acceleration K = stress intensity factor K th = stress intensity factor, threshold value N = load cycle n = load factor p = pressure R = stress ratio t = thickness u = longitudinal displacements at the crack surface v = normal displacements at the crack surface w i = weight factor i X i = longitudinal force at the crack tip Y i = normal force at the crack tip d = exponent of the deflection mapping function SIF = exponent of the fatigue-response mapping function = life span = offspring per generation = population size = Poisson's ratio = density

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Section: Nomenclaturementioning

confidence: 99%

Section: Nomenclaturementioning

confidence: 99%

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Hansen¹,

Häusler²,

Horst³

2008

Journal of Aircraft

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“…Structural optimization methods evolved in the aerospace industry in the late 1950s, when the need to design lightweight structures was critical [32,33,34]. Since then, the aerospace manufacturing industry has shown increasing interest in the application of optimization methods for the optimum design of minimum-weight aircraft structural components [35,36,37]. The survey paper by Venkayya [38] For composite skin panels, spar webs and ribs, the Tsai-Wu criterion [42,43,44] is used to predict the strength of the composite laminate in terms of the failure index ( ).…”

Section: Structural Design Optimization Of the Crm Wingboxmentioning

confidence: 99%

Influence of high fidelity structural models on the predicted mass of aircraft wing using design optimization

Dababneh

Kipouros

2018

Aerospace Science and Technology

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This paper explores the necessary and appropriate level of detail that is required to describe the structural geometry of aircraft wings accurately enough to predict the mass of the main load-carrying wing structure to an acceptable level of accuracy. Four different models of increasing structural fidelity are used to describe the wingbox structure of a realistic real-world aircraft wing. The wingbox of the NASA Common Research Model served as a test model for exploring and analyzing the trade-off between the granularity level of the wingbox geometry description under consideration and the computational resources necessary to achieve the required degree of accuracy. The mass of metallic and composite wingbox configurations was calculated via finite element analysis and design optimization techniques. The results provided an insight into the competence of certain wingbox models in predicting the mass of the metallic and composite primary wing structures to an acceptable level of accuracy, and in demonstrating the relative merits of the wingbox structural complexity and the computational time and input efforts for achieving the required level of accuracy.

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“…Due to the importance of weight reduction in aviation field [1] structural optimization methods started in aerospace industry in by the end of 1950. Aerospace manufacturing industry increases applications of optimization methods for the optimum design to minimize aircraft structural components weight [2].A few of these studies are referenced in this section to provide some background information in the field. In 1960s, Brandt and Wasiutynski [3] reviewed the state of art in the field of optimal design of structures.…”

Section: Introductionmentioning

confidence: 99%

Weight optimization of fixed landing gear for medium range UAV

Hammad¹,

Gadelrab²,

El-Shaer

2019

Engineering Research Journal

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Weight reduction of Unmanned Aerial Vehicle (UAV) components and systems is one of the most essential factors for aviation. Takeoff gross weight can be divided into crew weight, payload, fuel, and empty weight. The empty weight is divided into the structure, engine/s, landing gear, avionics and fixed equipment. Engine/s, landing gear, avionics and fixed equipment are selective items. Weight optimization can be made for structure and landing gear to minimize aircraft total weight. The main objective of the present study is to optimize weight and reach safe landing for a medium range UAV landing gear. The reduced weight can be used to increase payload and/or fuel to increase range or endurance of the UAV. In the present study, ANSYS shape (Topology) optimization tool is used to get a proposed shape for the UAV landing gear. Then parametric size optimization of the shape proposed was done. Design of experiment (DOE) technique is used in order to get the minimum weight for the landing gear at a specified stress limit. Aluminum alloy 7075-T61 and bi-directional carbon fiber which are the most common used materials in UAVs landing gear were used, It was found that using topology weight optimization technique reduces Aluminum Alloy landing gear weight by (30.4 %) changing the material to be bi-directional carbon fiber without optimization reduce landing gear weight with additional value (27.9 %). Optimizing bi-directional carbon fiber landing gear reduces the weight with additional value (4 %) to be the total weight ratio by (62.3 %). The optimization technique for weight optimization is a guide to optimize any other type of landing / part to minimize the total weight for the Unmanned Aerial Vehicle.

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Optimization Assisted Structural Design of a New Military Transport Aircraft

Cited by 20 publications

References 3 publications

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Evolutionary Multicriteria Design Optimization of Integrally Stiffened Airframe Structures

Influence of high fidelity structural models on the predicted mass of aircraft wing using design optimization

Weight optimization of fixed landing gear for medium range UAV

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