Multidisciplinary Design and Optimization for Fluid-Structure Interactions

2002 ◽  
Author(s):  
Franco Mastroddi ◽  
Claudia Bonelli ◽  
Luigi Morino ◽  
Giovanni Bernardini
Keyword(s):  
Incompressible Flow ◽  
Multidisciplinary Optimization ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Fluid Structure Interactions ◽  
Design And Optimization ◽  
Induced Drag ◽  
Introductory Overview ◽  
Modeling Techniques ◽  
Numerical Formulation

The paper presents an introductory overview of modeling techniques used by the authors for MDO–PD (MultiDisciplinary Optimization – Preliminary Design). The algorithms used by the authors in their MDO–PD code for modeling aerodynamics and aeroelasticity are reviewed. For the aerodynamic analysis, a boundary–element potential–flow method is used (for simplicity, only the incompressible–flow formulation is presented). The methodology is geared specifically towards MDO–PD for civilian aircraft. The numerical formulation is applied to a specific, highly–innovative aircraft configuration proposed by Frediani, which has, as a distinguishing feature, a low induced drag. A comparison with an MDO-PD of a standard wing configuration has been included.

scholarly journals An Integrated Design and Optimization Approach for Radial Inflow Turbines—Part I: Automated Preliminary Design

2018 ◽  
Vol 8 (11) ◽  
pp. 2038 ◽  
Author(s):  
Qing-Hua Deng ◽  
Shuai Shao ◽  
Lei Fu ◽  
Hai-Feng Luan ◽  
Zhen-Ping Feng
Keyword(s):  
Three Dimensional ◽  
Integrated Design ◽  
Multidisciplinary Optimization ◽  
Flow Coefficient ◽  
Design Stage ◽  
Optimization Approach ◽  
Preliminary Design ◽  
Design And Optimization ◽  
Preliminary Design Stage ◽  
Radial Inflow Turbine

An integrated design and optimization approach was developed for radial inflow turbines, which consists of two modules, an automated preliminary design module, and a flexible three-dimensional multidisciplinary optimization module. In this paper, the first module about the automated preliminary design approach was presented in detail and validated by the experimental data. The approach employs a genetic algorithm to explore the design space defined by the loading coefficient, flow coefficient, and rotational speed. The aim is to obtain the best design scheme with high aerodynamic performance under specified constraints and to reduce the dependency on human experiences when designing a radial inflow turbine. The validation results show that the present approach is able to get the optimal design and alleviate the dependence on the designer’s expertise under specified constraints at the preliminary design stage. Furthermore, the optimization results indicate that using the present optimization approach the total-to-static efficiency of the optimized T-100 radial inflow turbine can be increased by 1.0% under design condition and the rotor weight can be decreased by 0.35 kg (26.7%) as compared with that of the original case.

Research on Multidisciplinary Design Optimization of Aeroengine Turbine Flow Path in the Preliminary Design Phase

2014 ◽  
Author(s):  
Xiuli Shen ◽  
Dan Long
Keyword(s):  
Design Process ◽  
Multidisciplinary Design Optimization ◽  
Flow Path ◽  
Multidisciplinary Optimization ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Design Cycle ◽  
Aero Engine ◽  
Turbine Rotors ◽  
Turbine Flow Path

The design of an aero-engine is traditionally divided into three levels: conceptual design, preliminary design and detailed design. This three-step design process is inherently iterative, which can slow the design process and overall productivity. Additionally, as an integrated systems engineering analysis, aero-engine design involves multiple-disciplines. The complex coupled-relationship among multiple-disciplines and multiple-components gives rise to severe conflict with performance requirements when designing, especially when it comes to high-performance aero-engine. Traditionally, designers need to empirically balance all kinds of requirements, which lead to a longer design cycle. So it is necessary to apply Multidisciplinary Design Optimization (MDO) to organize and manage the process of design system which sufficiently utilizes the effect of interaction of multidisciplines for the optimal solution. The MDO of a turbine flow path is one of the key multidisciplinary optimization technologies in aeroengine overall design. The problem studied and presented in this paper consists in optimizing a turbine modeled by a multidisciplinary system of two coupled disciplines: turbine aerodynamics and structural strength, with temperature limited by the materials. In the present work, three modules are established to conduct the MDO research of turbine flow path: flow path design, turbine strength calculation and MDO. The aeroengine turbine flow path, including high and low pressure turbine flow path, is designed in the first module, with its efficiency estimated. In the second module, turbine rotors consisting of blades, discs and the low spool shaft are parametric modeled so as to analyze the structural aspects of turbine rotors, such as weight and stresses. MDO is conducted using multi-island genetic algorithm optimization (MIGA) optimization algorithm provided in iSIGHT software. Fully Integrated Optimization (FIO) strategy is studied to deal with the multidisciplinary analysis. The complex coupling relations between aerodynamic performance and turbine strength are analyzed to establish turbine multidisciplinary optimization system. The optimal values of loading coefficient, rotational speed, bore diameter of rotor discs defined by the shaft size, and other independent design variables are obtained in order to achieve minimum weight of turbine rotors while simultaneously meeting the strength and aerodynamics efficiency requirements. This method presented in this paper can greatly shorten turbine design cycle, improve aeroengine design ability, and is prospective to be widely applied to engineering field.

scholarly journals An Integrated Design and Optimization Approach for Radial Inflow Turbines—Part II: Multidisciplinary Optimization Design

2018 ◽  
Vol 8 (11) ◽  
pp. 2030 ◽  
Author(s):  
Qinghua Deng ◽  
Shuai Shao ◽  
Lei Fu ◽  
Haifeng Luan ◽  
Zhenping Feng
Keyword(s):  
Optimization Design ◽  
Three Dimensional ◽  
Integrated Design ◽  
Multidisciplinary Optimization ◽  
Design Stage ◽  
Optimization Approach ◽  
Preliminary Design ◽  
Design And Optimization ◽  
Static Efficiency ◽  
Preliminary Design Stage

This paper proposes an integrated design and optimization approach for radial inflow turbines consisting of an automated preliminary design module and a flexible three-dimensional multidisciplinary optimization module. The latter was constructed by an evolution algorithm, a genetic algorithm-assisted self-learning artificial neural network and a dynamic sampling database. The 3-D multidisciplinary optimization approach was validated by the original T-100 turbine and the T-100re turbine obtained from the automated preliminary design approach, for maximizing the total-to-static efficiency and minimizing the rotor weight while keeping the mass flow rate constant and stress limitation satisfied. The validation results indicate that the total-to-static efficiency is 89.6%, increased by 1.3%, and the rotor weight is reduced by 0.14 kg (14.6%) based on the T-100re turbine, while the efficiency is 88.2%, increased by 2.2% and the weight is reduced by 0.49 kg (37.4%) based on the original T-100 turbine. Moreover, the T-100re turbine shows better performance at the preliminary design stage and conserves this advantage to the end, though both the aerodynamic performance of the T-100 and the T-100re turbine are improved after 3-D optimization. At the same time, it is implied that the preliminary design plays an essential role in the radial inflow turbine design process, and it is hard for only 3-D optimization to get a further performance improvement.

Multidisciplinary design and optimization of expendable launch vehicle for microsatellite missions

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Qasim Zeeshan ◽  
Amer Farhan Rafique ◽  
Ali Kamran ◽  
Muhammad Ishaq Khan ◽  
Abdul Waheed
Keyword(s):  
Research Effort ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Design And Development ◽  
Content Type ◽  
Design And Optimization ◽  
Design Variables ◽  
Development Costs

Purpose The capability to predict and evaluate various configurations’ performance during the conceptual design phase using multidisciplinary design analysis and optimization can significantly increase the preliminary design process’s efficiency and reduce design and development costs. This research paper aims to perform multidisciplinary design and optimization for an expendable microsatellite launch vehicle (MSLV) comprising three solid-propellant stages, capable of delivering micro-payloads in the low earth orbit. The methodology’s primary purpose is to increase the conceptual and preliminary design process’s efficiency by reducing both the design and development costs. Design/methodology/approach Multidiscipline feasible architecture is applied for the multidisciplinary design and optimization of an expendable MSLV at the conceptual level to accommodate interdisciplinary interactions during the optimization process. The multidisciplinary design and optimization framework developed and implemented in this research effort encompasses coupled analysis disciplines of vehicle geometry, mass calculations, aerodynamics, propulsion and trajectory. Nineteen design variables were selected to optimize expendable MSLV to launch a 100 kg satellite at an altitude of 600 km in the low earth orbit. Modern heuristic optimization methods such as genetic algorithm (GA), particle swarm optimization (PSO) and SA are applied and compared to obtain the optimal configurations. The initial population is created by passing the upper and lower bounds of design variables to the optimizer. The optimizer then searches for the best possible combination of design variables to obtain the objective function while satisfying the constraints. Findings All of the applied heuristic methods were able to optimize the design problem. Optimized design variables from these methods lie within the lower and upper bounds. This research successfully achieves the desired altitude and final injection velocity while satisfying all the constraints. In this research effort, multiple runs of heuristic algorithms reduce the fundamental stochastic error. Research limitations/implications The use of multiple heuristics optimization methods such as GA, PSO and SA in the conceptual design phase owing to the exclusivity of their search approach provides a unique opportunity for exploration of the feasible design space and helps in obtaining alternative configurations capable of meeting the mission objectives, which is not possible when using any of the single optimization algorithm. Practical implications The optimized configurations can be further used as baseline configurations in the microsatellite launch missions’ conceptual and preliminary design phases. Originality/value Satellite launch vehicle design and optimization is a complex multidisciplinary problem, and it is dealt with effectively in the multidisciplinary design and optimization domain. It integrates several interlinked disciplines and gives the optimum result that satisfies these disciplines’ requirements. This research effort provides the multidisciplinary design and optimization-based simulation framework to predict and evaluate various expendable satellite launch vehicle configurations’ performance. This framework significantly increases the conceptual and preliminary design process’s efficiency by reducing design and development costs.

Integrated Multidisciplinary Design and Optimization Methodologies in Electronics Packaging: State-of-the-Art Review

2006 ◽  
Author(s):  
Tohru Suwa ◽  
Hamid Hadim
Keyword(s):  
State Of The Art ◽  
Design Procedure ◽  
Computation Time ◽  
Automated Design ◽  
Electronics Packaging ◽  
Optimization Techniques ◽  
Multidisciplinary Optimization ◽  
Multidisciplinary Design ◽  
Design Environment ◽  
Design And Optimization

Electronic packaging design is a process that requires optimized solutions based on multidisciplinary design tradeoffs, which usually have complicated relations among multiple design variables. Required numerical analyses such as thermal and thermo-mechanical have hampered this multidisciplinary optimization process because of their time intensive modeling and computation time. This paper presents a state-of-the-art overview of recent multidisciplinary design and optimization methodologies in electronics packaging. The reported methodologies are divided into tow groups: (1) integrated multidisciplinary CAD environment, and (2) automated design and optimization techniques. A semi-automated design environment, which includes graphical user interface, modeling, and simulation, enhances the design procedure in the first group. Fully automated design optimization methodologies are used for various design applications in the second group. In recent years, methodologies using (1) detailed numerical analysis models directly connected to optimization algorithms, (2) design of experiments (DoE), and (3) artificial neural networks (ANNs) have been proposed as new trends in this field. Advantages as well as disadvantages of these methods are discussed.

Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

2020 ◽  
pp. 095441002092665
Author(s):  
Jacek Mieloszyk
Keyword(s):  
Dynamic Stability ◽  
Optimization Methods ◽  
Multidisciplinary Optimization ◽  
Preliminary Design ◽  
Flight Performance ◽  
Design And Optimization ◽  
Optimization Framework ◽  
Aircraft Flight ◽  
Vertical Takeoff And Landing ◽  
Vertical Takeoff

Classical approach to conceptual and preliminary design in aerospace sciences reaches limits. To go further and achieve better, competitive results’ use of optimization methods becomes mandatory. The trend is clearly visible in professional software for simulations equipped with optimization tools, which was not standard just decade ago. Many examples of multidisciplinary optimization were shown, especially with coupled aerodynamics and structure analyses, but only few of them consider dynamic stability effects in the conceptual and preliminary design. The article shows successful example of multidisciplinary design and optimization of Vertical Takeoff and Landing aircraft, which includes coupling of aerodynamics, mass analyses and innovative approach of constraints from flight dynamic stability. Presented optimization framework revealed potential for more efficient conceptual and preliminary design with the result of known dynamic stability characteristics of the aircraft. Obtaining the dynamic stability characteristics is not common on the early stages of the design yet crucial for the aircraft flight performance.

scholarly journals Preliminary Sailplane Design Using MDO And Multi-Fidelity Analysis

2021 ◽  
Author(s):  
Chris V. Pilcher
Keyword(s):  
Multidisciplinary Design Optimization ◽  
High Performance ◽  
Vortex Lattice ◽  
Optimization Techniques ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Adaptive Meshing ◽  
Analysis Methods ◽  
And Performance ◽  
Modern Optimization

A multidisciplinary design optimization (MDO) strategy for the preliminary design of a sailplane has been developed. The proposed approach applies MDO techniques and multi-fidelity analysis methods which have seen successful use in many aerospace design applications. A customized genetic algorithm (GA) was developed to control the sailplane optimization that included aerodynamics/stability, structures/weights and balance and, performance/airworthiness disciplinary analysis modules. An adaptive meshing routine was developed to allow for accurate modeling of the aero structural couplinginvolved in wing design, which included a finite element method (FEM) structural solver along with a vortex lattice aerodynamics solver. Empirical equations were used to evaluate basic sailplane performance and airworthiness requirements. This research yielded an optimum design that correlated well with an existing high performance sailplane. The results of this thesis suggest that preliminary sailplane design is a well suited application for modern optimization techniques when coupled with, multi-fidelity analysis methods.

Integrated Thermomechanical Design and Optimization of BGA Packages Using Genetic Algorithm

Volume 4 ◽  
2004 ◽  
Author(s):  
Hamid A. Hadim ◽  
Tohru Suwa
Keyword(s):  
Genetic Algorithm ◽  
Thermal Strain ◽  
System Level ◽  
Multidisciplinary Design ◽  
Design Stage ◽  
Computational Time ◽  
Design Parameters ◽  
Package Design ◽  
Early Design Stage ◽  
Design And Optimization

A new multidisciplinary design and optimization methodology in electronics packaging is presented. A genetic algorithm combined with multi-disciplinary design and multi-physics analysis tools are used to optimize key design parameters. This methodology is developed to improve the electronic package design process by performing multidisciplinary design and optimization at an early design stage. To demonstrate its capability, the methodology is applied to a Ball Grid Array (BGA) package design. Multidisciplinary criteria including thermal, thermal strain, electromagnetic leakage, and cost are optimized simultaneously. A simplified routability analysis criterion is treated as a constraint. The genetic algorithm is used for systematic design optimization while reducing the total computational time. The present methodology can be applied to any electronics product design at any packaging level from the chip level to the system level.

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