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检索条件"主题词=Multidisciplinary Design and Optimization"

共 115 条记录，以下是51-60 订阅

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Towards a Framework for Parametric Models and Geometric Sensitivity Computations with SU2 and pyCAPS

Towards a Framework for Parametric Models and Geometric Sens...

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AIAA Aviation Forum

作者： Shen, Yiren Patel, Harsh C. Alonso, Juan J. Galbraith, Marshall C. Stanford Univ Dept Aeronaut & Astronaut Stanford CA 94305 USA MIT Dept Aeronaut & Astronaut Cambridge MA 02139 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Shape design optimization relies on obtaining objective and constraint functional sensitivities to geometric parameters in order to explore the design space effectively. To facilitate computer-aided design (CAD) applications in industry, this study presents a workflow for effectively handling geometric constraints and computing analytic sensitivities. The workflow is capable of computing parametric sensitivities by combines geometric sensitivities obtained using Engineering Sketch Pad with adjoint surface sensitivities from the SU2 adjoint solver through a dot product within the pyCAPS framework. The effectiveness and limitations of this workflow are evaluated through three test cases, including a preliminary demonstration of a shape optimization problem in wing design. The results indicate that the conceptual effectiveness of the proposed workflow, while noting the need for further improvement in the mesh generation routine.

关键词： Computer Aided design multidisciplinary design and optimization Shape optimization Computing Rectangular Wing Mesh Generation Proper Orthogonal Decomposition Application Programming Interface Aerodynamic Shape optimization Angle of Attack

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Vibroacoustic studies on structurally optimized Pareto designs of curved composite stiffened panel

Vibroacoustic studies on structurally optimized Pareto desig...

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AIAA SciTech Forum

作者： Joshi, Pankaj Mulani, Sameer B. Kapania, Rakesh K. ZAL Ctr Appl Aeronaut Res Acoust & Vibrat D-21129 Hamburg Germany Univ Alabama Dept Aerosp Engn & Mech Tuscaloosa AL 35487 USA Virginia Polytech Inst & State Univ Kevin T Crofton Dept Aerosp Engn Blacksburg VA 24061 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

The last several decades have seen a shift in material selection for the primary structure of an aircraft from predominantly aluminum to composite material. Two aircraft, Airbus A350 and Boeing 787, are the two living examples of such a shift in material technology. However, composite materials' low weight and high stiffness, together, could deteriorate the vibroacoustic performance as compared to a similar aluminum design. The present authors were the first to propose the use of aircraft panels with curvilinear stiffeners as a means to improve the vibroacoustic performance of panels. However, our earlier vibroacoustic studies were mainly focused on flat aluminum panels with curvilinear stiffeners. This manuscript focuses on performing design studies on composite curved panels with curvilinear stiffeners by using multi-objective design optimization to minimize mass and maximize buckling performance as two competing objectives. Seven selected Pareto optimal designs are next analyzed using finite element and infinite element based coupled fluid-structure interaction analysis for obtaining vibroacoustic response. Three excitation cases, namely point, diffuse acoustic field, and turbulent boundary layer, are considered for vibroacoustic analysis of structurally optimized seven Pareto designs. In the low to mid frequency region, the selected Pareto designs show significantly different sound radiation performances. It is shown that the differences in sound radiation characteristics of Pareto designs in low to mid frequency range gives the designer additional freedom to select a structurally optimized design with a better vibroacoustic performance.

关键词： Turbulent Boundary Layer multidisciplinary design and optimization Fluid Structure Interaction Laminated Composites Airbus Finite Element Analysis Sound Pressure Level Frequency Response Functions Aerospace Structure Structural optimization

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Integrating MBSE and MDO through an Extended Requirements-Functional-Logical-Physical (RFLP) Framework

Integrating MBSE and MDO through an Extended Requirements-Fu...

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AIAA Aviation Forum

作者： Swaminathan, Rajashekar Sarojini, Darshan Hwang, John T. Univ Calif San Diego Mech & Aerosp Engn Dept 9500 Gilman Dr La Jolla CA 92093 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The design of mechanical systems is a complex process that is often associated with significant time and budget overruns. Model-Based Systems Engineering (MBSE) has emerged as a way to mitigate these issues. However, MBSE alone lacks the ability to simulate, analyze and design mechanical systems. multidisciplinary design optimization (MDO) treats the parameters of the mechanical system as design variables and uses numerical optimization methods to find the parameters that optimize performance metrics while meeting constraints. However, it lacks the systematic traceability that MBSE offers. This paper proposes a methodology that builds on the Requirements Engineering, Functional design, Logical design, and Physical design (RFLP) approach to integrate MBSE and MDO and overcome each other's limitations. The recently proposed Process RFLP is used to aid in the development, enumeration, and selection of design activities involving simulation and MDO. Guidelines for the implementation of RFLP are formulated and presented. The approach is demonstrated through a test case involving the design of a single-aisle transport category aircraft. Compliance with aircraft requirements is verified, and a change in requirements case is presented. The long-term goal is to automate the methodology to enable MBSE to drive the formulation and execution of MDO.

关键词： Model Based System Engineering multidisciplinary design and optimization Budget Overrun Computer Programs Computational Modeling Computer Aided design Drag Rudders Top Level Aircraft Requirements Vertical Takeoff and Landing Mathematical Models

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High-fidelity Aerostructural optimization Benchmark for Aircraft Propellers in Hover

High-fidelity Aerostructural Optimization Benchmark for Airc...

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AIAA SciTech Forum

作者： Zoppelt, Seth A. Koyuncuoglu, Heyecan U. He, Ping Iowa State Univ Dept Aerosp Engn Ames IA 50011 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper proposes an aerostructural optimization benchmark for aircraft propellers working in a hover condition. This benchmark uses an untwisted and untapered blade with a NACA0012 sectional profile as the baseline design. The objective function is the propeller shaft power coefficient. The design variables include the propeller twist, shape, chord, span, and rotation speed. The constraints include the propeller thrust coefficient, mass, von Mises stress, and geometry (e.g., thickness and curvature). We propose three different optimization configurations with various combinations of design variables. The proposed propeller aerostructural optimization benchmark can be solved using various optimization algorithms and modeling fidelities. This paper showcases a high-fidelity gradient-based optimization approach. To be more specific, we use the finite-volume computational fluid dynamics and finite-element structural dynamics solvers to simulate the fluid and solid domains, respectively. We then use the discrete adjoint approach to compute the derivatives for gradient-based optimization with a large number of design variables. To consider fluid-structure interaction and coupled derivative computation, we utilize OpenMDAO/MPhys, an open-source framework that facilitates high-fidelity multidisciplinary design optimization. We compare the objective, constraints, and distributions of spanwise shape, twist, and thrust between the baseline and optimized designs. This study has the potential to build a common benchmark and promote collaboration in the propeller multidisciplinary design optimization community.

关键词： Aerostructural optimization Aircraft Propeller Computational Fluid Dynamics Propeller Performance OpenMDAO multidisciplinary design and optimization Power Coefficient Fluid Structure Interaction Airfoil Profiles Computational Structural Dynamics

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Linearized Frequency-Domain Gust Analysis and Adjoint-Based Sensitivities

Linearized Frequency-Domain Gust Analysis and Adjoint-Based ...

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AIAA SciTech Forum

作者： Jacobson, Kevin E. Thelen, Andrew S. Stanford, Bret K. NASA Langley Res Ctr Aeroelast Branch Hampton VA 23681 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Gust analysis is added to a linearized frequency-domain method in FUN3D, a NASA computational fluid dynamics solver. The method linearizes about a nonlinear static equilibrium condition and is therefore appropriate for problems with small perturbations such as transonic stochastic gust analysis. In addition to the gust analysis, adjoint-based sensitivities of stochastic gust constraints are implemented for multidisciplinary design optimization. The linearized frequency-domain gust model and adjoint-based sensitivities are described and verified. The method is applied to an optimization for mass minimization of the AGARD 445.6 wing subject to a stochastic gust constraint limiting the displacement of the wing tip.

关键词： Power Spectral Density FUN3D Computational Fluid Dynamics multidisciplinary design and optimization Common Research Model Wing Tip Freestream Mach Number Lift Coefficient OpenMDAO NACA 64A010

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Optimal design of eVTOLs for Urban Mobility using Analytical Target Cascading (ATC)

Optimal Design of eVTOLs for Urban Mobility using Analytical...

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AIAA SciTech Forum

作者： Chinthoju, Prajwal K. Lee, Yong Hoon Das, Ghanendra K. James, Kai A. Allison, James T. Univ Illinois Ind & Enterprise Syst Engn 104 S Mathews Ave406 TB Urbana IL 61801 USA Univ Memphis Dept Mech Engn 3815 Cent Ave322D ES Memphis TN 38152 USA Georgia Inst Technol Sch Aerosp Engn 275 Ferst Dr NW212 Weber Atlanta GA 30332 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Over the past few decades, multidisciplinary design optimization (MDO) techniques have shown great potential in generating optimal designs for complex system of systems. Monolithic MDO methods that formulate the design problem as a single optimization problem are effective, but present challenges in coordination. On the other hand, distributed MDO methods decompose the design problem into different optimization problems and hence offer more modularity and flexibility, especially when implemented by teams of optimization specialists. In this article, one such distributed MDO method, Analytical Target Cascading (ATC), is investigated as a candidate for the design of electric Vertical Take Off and Landing aircraft (eVTOL). design of eVTOLs for urban mobility has been a subject of immense interest over the past decade. eVTOLs offer many advantages over conventional modes of urban transport such as reduced environmental impact, utilization of vertical space for transportation, and competitive cost of transportation. Most current efforts for eVTOL design are in relatively early stages. Hence, distributed MDO methods that can effectively consider complex interactions between different subsystems and disciplines can help support eVTOL design efforts. In this study, ATC is implemented to optimize the total cost per flight for a simple mission, involving take-off to a set altitude, cruising at constant velocity for a range of 50-150 km, and landing, all while carrying a given payload. The key design parameters that are optimized as a part of this study are the mass of aircraft and individual subsystems, cruise velocity, wingspan, and radius of the propeller. Furthermore, a comparison of the resulting optimal solutions using ATC and monolithic MDO methods is presented. General observations are also articulated regarding potential computational advantages, such as parallelism and tailored solution algorithms, as well as organizational considerations, such as distributed iterati

关键词： multidisciplinary design and optimization Electric Vertical Take off and Landing Propeller Blades Solution Algorithm Maximum Takeoff Weight Lift Coefficient Electric Motors Helicopters Drag Coefficient Blade Element Momentum Theory

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Solid-State Electroaerodynamic Uncrewed Aircraft for Near-Silent Package Delivery

Solid-State Electroaerodynamic Uncrewed Aircraft for Near-Si...

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AIAA Aviation Forum

作者： Brown, Arthur Gomez-Vega, Nicolas Barrett, Steven R. H. MIT Dept Aeronaut & Astronaut Cambridge MA 02139 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

This paper presents the design of two uncrewed aircraft, powered by electroaerodynamic (EAD) multistaged ducted (MSD) thrusters, for a last-mile package delivery mission. Propeller-driven uncrewed aircraft for package delivery are in development;however, noise generated by their propellers can annoy local residents, leading to community opposition. Because EAD thrusters have no moving parts, they are almost silent in some applications. EAD-powered aircraft may therefore be able to complete package delivery missions without community opposition to noise. MSD thrusters, in which multiple EAD electrode stages are enclosed inside a duct, are more efficient and thrust-dense than their exposed counterparts. This is in part because the duct contributes to thrust, in a manner analogous to ducted fans. Two MSD-powered aircraft configurations are presented: a monoplane and a box wing. Both are capable of vertical takeoff and landing;their MSD thrusters tilt vertically to provide thrust in hover, then tilt horizontally for wingborne flight. While both aircraft concepts can fly a nominal out-and-back urban package delivery mission, their feasibility is contingent on improvements in four technological modeling parameters, relative to today's state-of-the-art: thruster ionization energy, stage loss coefficient, power-converter specific power, and battery specific power.

关键词： Aeroplane Fixed Wing Aircraft Aircraft Configurations Vertical Takeoff and Landing Propellers Ducted Fans Freestream Velocity multidisciplinary design and optimization Wing Planforms Radioactive Decay

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Coupled Vehicle and Trajectory design optimization for Boost-Glide Hypersonic Systems

Coupled Vehicle and Trajectory Design Optimization for Boost...

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AIAA SciTech Forum

作者： Gottlieb, Jonah R. Mines, John Mark Garmendia, Daniel C. Emhoff, Jerold W. Clemens, Daniel E. Johns Hopkins Univ Appl Phys Lab Air & Missile Def Sect Laurel MD 20723 USA Johns Hopkins Univ Appl Phys Lab Space Explorat Sect Laurel MD 20723 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

multidisciplinary design optimization approaches have been successfully applied to many flight vehicle design problems in academia and are now becoming more common in industry. Typically, the vehicle design is optimized given a constrained trajectory, or the trajectory is optimized given a fixed vehicle design;however, simultaneous vehicle/trajectory optimization is very challenging. Certain applications, even for conceptual design, demand higher fidelity in the vehicle model and/or trajectory solver, which is possible given sufficient computational resources. This paper describes missile conceptual design optimization methods and software tools under development for more than a decade at the Johns Hopkins University Applied Physics Laboratory. These methods are applied to the problem of simultaneous vehicle and trajectory design optimization to demonstrate how that coupling drives performance for a hypothetical boost-glide hypersonic vehicle.

关键词： Boost Glide multidisciplinary design and optimization Hypersonic Systems Optimal Control Problem Launch Vehicle design optimization Algorithm Suborbital Spaceplane Flight Vehicle design Software Tool Propellant

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Embedding the Sensitivities of a Structural Surrogate in a Coupled AerostructuralWing optimization

Embedding the Sensitivities of a Structural Surrogate in a C...

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AIAA Aviation Forum

作者： Fontana, Joshua E. Piperni, Pat Yang, Zhi Mavriplis, Dimitri J. Clarkson Univ Potsdam NY 13699 USA Univ Wyoming Laramie WY USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

It is well known that the most critical phases of aircraft design are the conceptual and preliminary design stages, as these have the largest impact on both the performance and economic viability of new aircraft. To this end, the work presented herein targets the preliminary design stage, in which it is imperative to have a time-efficient multidisciplinary design optimization (MDO) capability that can support evolving design requirements, whilst also facilitating interdepartmental collaboration. As the number of disciplines included in MDO processes continues to increase, it is envisioned that some of the disciplinary tools will take the form of surrogate models, while others remain physics-based, depending on the requirements and stage of the design process. To simulate this in the context of aerostructural optimization, the current work features a high-fidelity aerodynamic flow solver, while a surrogate is employed to model the wing structure. This approach includes the evaluation of the sensitivities of both the aerodynamic and structural disciplines, using a coupled-adjoint formulation to enable gradient-based optimization. An important aspect of the method is that the surrogate is trained only once, prior to the optimization, and held fixed throughout. The surrogate model in effect parameterizes the structural design process, and outputs the structural weight and equivalent stiffness of an optimized wing structure, given inputs of global geometry parameters and sizing loads. The sizing loads used to interrogate the surrogate are represented as parameterized load envelopes, which keeps the number of surrogate inputs small and allows the surrogate to be trained using a wide variety of representative load envelopes that cover the full range of the structural design space. The new method has been implemented in the Isight process integration framework, using the NSU3D Reynolds-Averaged Navier-Stokes code for the aerodynamic analysis and adjoint implementation, and

关键词： Aerostructural Wing optimization Aerodynamic Force Coefficients Reduced Order Modelling Aerostructural optimization multidisciplinary design and optimization NSU3D Reynolds Averaged Navier Stokes Euler Bernoulli Beams Bombardier Aviation Aircraft design

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An SQP algorithm based on a hybrid architecture for accelerating optimization of large-scale systems

An SQP algorithm based on a hybrid architecture for accelera...

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AIAA Aviation Forum

作者： Joshy, Anugrah Jo Dunn, Ryan Sperry, Mark Gandarillas, Victor Hwang, John T. Univ Calif San Diego Dept Mech & Aerosp Engn La Jolla CA 92093 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The optimization of large-scale and multidisciplinary engineering systems is now prevalent in many fields, exemplified in areas such as aircraft, satellite, and wind turbine design. The rise of advanced modeling frameworks has expanded the scope of large-scale optimization techniques across various research domains. However, novel applications have emerged that pose efficiency-related computational challenges to the existing methods employed in large-scale, gradient-based optimization. The authors previously proposed a new paradigm for accelerating the optimization of large-scale and complex-engineered systems, laying the groundwork for a new approach. The new paradigm is based on a hybrid optimization architecture called SURF which stands for strong unification of reduced-space and full-space. SURF has the potential to expedite optimization of models with state variables that are iteratively computed by solving nonlinear systems. This paper extends the existing paradigm by providing new theoretical results that unify the reduced-space and full-space algorithms in a practical optimization setting that considers line searches and quasi-Newton methods. We also present a practical, SQP-based SURF algorithm that can be applied to general, inequality-constrained problems. The new algorithm also includes an adaptive hybrid selection strategy for robust convergence and faster solutions. We test the new algorithm on a low-fidelity motor optimization problem and a wind farm layout optimization problem to validate the optimization results, and to demonstrate its computational benefits. In one of the problems, SURF was able to speed up the traditional optimization by approximately 25 percent. In the other problem, SURF was able to converge to a better optimal solution.

关键词： Broyden Fletcher Goldfarb Shanno Nonlinear Systems Wind Turbine design Satellites multidisciplinary design and optimization Computational Modeling Space Architecture Energy Production Gradient Free Method Synchronous Motors

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