scholarly journals Application of an Efficient Gradient-Based Optimization Strategy for Aircraft Wing Structures

Aerospace ◽  
2018 ◽  
Vol 5 (1) ◽  
pp. 3 ◽  
Author(s):  
Odeh Dababneh ◽  
Timoleon Kipouros ◽  
James Whidborne
Keyword(s):  
Optimization Strategy ◽  
Aircraft Wing ◽  
Wing Structures ◽  
Gradient Based

scholarly journals A finite element parametric modeling technique of aircraft wing structures

2013 ◽  
Vol 26 (5) ◽  
pp. 1202-1210 ◽  
Author(s):  
Jiapeng Tang ◽  
Ping Xi ◽  
Baoyuan Zhang ◽  
Bifu Hu
Keyword(s):  
Finite Element ◽  
Parametric Modeling ◽  
Modeling Technique ◽  
Aircraft Wing ◽  
Wing Structures

An Adjoint Based Approach for Optimal Design of Morphing SMP

2013 ◽  
Author(s):  
Shuang Wang ◽  
John C. Brigham
Keyword(s):  
Shape Change ◽  
Mechanical Energy ◽  
Optimization Methods ◽  
Design Parameters ◽  
Optimization Strategy ◽  
Thermally Activated ◽  
Gradient Based ◽  
Nonlinear Optimization Methods ◽  
Numerical Representations ◽  
Objective Functional

This work presents a strategy to identify the optimal localized activation and actuation for a morphing thermally activated SMP structure or structural component to obtain a targeted shape change or set of shape features, subject to design objectives such as minimal total required energy and time. This strategy combines numerical representations of the SMP structure’s thermo-mechanical behavior subject to activation and actuation with gradient-based nonlinear optimization methods to solve the morphing inverse problem that includes minimizing cost functions which address thermal and mechanical energy, morphing time, and damage. In particular, the optimization strategy utilizes the adjoint method to efficiently compute the gradient of the objective functional(s) with respect to the design parameters for this coupled thermo-mechanical problem.

Structural sizing for the weight estimation of a very light aircraft wing

2018 ◽  
Vol 232 (14) ◽  
pp. 2681-2687
Author(s):  
Abdelkader Benaouali ◽  
Robert Rogólski ◽  
Stanisław Kachel
Keyword(s):  
Finite Element ◽  
Design Process ◽  
Geometric Modeling ◽  
Optimization Techniques ◽  
Product Development Process ◽  
Optimization Strategy ◽  
Aircraft Wing ◽  
Lattice Method ◽  
Vortex Lattice Method

The design process is no longer a trial-and-error procedure due to the introduction of computer-aided tools and optimization techniques. The product development process is therefore accelerated, allowing to produce more in a relatively lesser time. Moreover, the best possible design, with regard to the performance, can hence be obtained. When applied to the design of an aircraft wing, the optimization objective is usually to minimize the structural weight under failure-based constraints. This paper presents an optimization strategy that allows the determination of the wing surface structural thicknesses corresponding to the minimal weight while keeping the structure safe in terms of strength and buckling. This strategy is applied for the wing sizing process of a new two-seater very light aircraft, currently under development. The design process goes through geometric modeling, aerodynamic calculations using vortex lattice method, and finite element modeling. Structural optimization is performed within MATLAB, and is based on the automatic execution of the finite element solver MSC.NASTRAN.

scholarly journals Three-Phase PWM Voltage-Source-Inverter Weight Optimization for Aircraft Application Using Deterministic Algorithm

Electronics ◽  
2020 ◽  
Vol 9 (9) ◽  
pp. 1393
Author(s):  
Adrien Voldoire ◽  
Jean-Luc Schanen ◽  
Jean-Paul Ferrieux ◽  
Alexis Derbey ◽  
Cyrille Gautier
Keyword(s):  
Pulse Width Modulation ◽  
Deterministic Algorithm ◽  
Voltage Source ◽  
Weight Optimization ◽  
Optimization Strategy ◽  
Pwm Inverter ◽  
Thermal Constraints ◽  
Three Phase ◽  
Gradient Based ◽  
Aircraft Application

In this paper, a design by optimization process is used to size a 10-kW three-phase pulse width modulation (PWM) inverter for aeronautic application. The objective function is the converter weight, which has to be minimized. Sizing constraints are the efficiency, alternating current (AC) and direct current (DC) harmonics, and thermal constraints on all devices. A deterministic algorithm is chosen since it allows obtaining quick results and dealing with a large number of variables. All equations are analytical, in order to comply with this gradient-based optimization strategy, which imposes the derivability of the models. Several optimization results using different AC inductor solutions (iron powder and ferrite) are compared. The optimized converters were built and tested experimentally to verify their performances. Semiconductor and inductor losses were measured accurately using calorimetric test benches. The optimality of the solutions was carefully verified by changing parameters.

scholarly journals Ground Structures-Based Topology Optimization of a Morphing Wing Using a Metaheuristic Algorithm

Metals ◽  
2021 ◽  
Vol 11 (8) ◽  
pp. 1311
Author(s):  
Seksan Winyangkul ◽  
Kittinan Wansaseub ◽  
Suwin Sleesongsom ◽  
Natee Panagant ◽  
Sumit Kumar ◽  
...  
Keyword(s):  
Topology Optimization ◽  
Optimization Problems ◽  
Future Research ◽  
Structural Constraints ◽  
Metaheuristic Algorithm ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
Multi Objective ◽  
Wing Structures ◽  
Wing Structure

This paper presents multi-objective topology and sizing optimization of a morphing wing structure. The purpose of this paper is to design a new aircraft wing structure with a tapered shape for ribs, spars, and skins including a torsion beam for external actuating torques, which is anticipated to modify the aeroelastic characteristic of the aircraft wing using multi-objective optimization. Two multi-objective topology optimization problems are proposed employing ground element structures with high- and low-grid resolutions. The design problem is to minimize mass, maximize difference of lift effectiveness, and maximize the buckling factor of an aircraft wing subject to aeroelastic and structural constraints including lift effectiveness, critical speed, and buckling factors. The design variables include aircraft wing structure dimensions and thickness distribution. The proposed optimization problems are solved by an efficient multi-objective metaheuristic algorithm while the results are compared and discussed. The Pareto optimal fronts obtained for all tests were compared based on a hypervolume metric. The objective function values for Case I and Case II at 10 selected optimal solutions exhibit a range of structural mass as 115.3216–411.6250 kg, 125.0137–440.5869 kg, lift effectiveness as 1.0514–1.1451, 1.0834–1.1639 and bucking factor as 38.895–1133.1864 Hz, 158.1264–1844.4355 Hz, respectively. The best results reveal unconventional aircraft wing structures that can be manufactured using additive manufacturing. This research is expected to serve as a foundation for future research into multi-objective topology optimization of morphing wing structures based on the ground element framework.

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