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A Coupled-Adjoint Framework for High-Fidelity Aero-Structural-Trim Optimization in Aircraft Design /

Record Type:	Electronic resources : Monograph/item
Title/Author:	A Coupled-Adjoint Framework for High-Fidelity Aero-Structural-Trim Optimization in Aircraft Design // Harsh C Patel.
Author:	Patel, Harsh C.,
Description:	1 electronic resource (210 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 86-04, Section: A.
Contained By:	Dissertations Abstracts International86-04A.
Subject:	Aircraft. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31520269
ISBN:	9798342113199

A Coupled-Adjoint Framework for High-Fidelity Aero-Structural-Trim Optimization in Aircraft Design /
Patel, Harsh C.,

A Coupled-Adjoint Framework for High-Fidelity Aero-Structural-Trim Optimization in Aircraft Design /Harsh C Patel. - 1 electronic resource (210 pages)

Source: Dissertations Abstracts International, Volume: 86-04, Section: A.

Aircraft design involves solving complex optimization problems that encompass various engineering disciplines, such as aerodynamics, structures, controls, and propulsion. The interdependence among these disciplines has made multidisciplinary design optimization (MDO) methods particularly valuable in the field of conceptual aircraft design.Recent advancements in computational methods, high-performance computing, and efficient gradient-based optimization algorithms have significantly impacted the development of aircraft through MDO. By formulating the design challenge as a mathematical optimization problem and integrating multiple disciplines as well as their interactions within a unified, parameterized model of the system, it is possible to efficiently explore the design space. This MDO approach allows for the systematic resolution of engineering trade-offs and the exploitation of beneficial interactions involving thousands of design variables, leading to faster generation of improved aircraft designs.The integration of high-fidelity computational fluid dynamics (CFD) and finite element analysis (FEA) in MDO has proven to be remarkably successful for aeroelastic wing design. However, certain critical aspects, such as aircraft dynamics, stability, and control requirements, have been largely ignored. In real-world applications, the primary emphasis in aeroelastic wing design shifts from solely maximizing wing performance to carefully tailoring the wing's aeroelastic response. This shift is essential to ensure stable flight dynamics and effective control, which are crucial considerations in the conceptual design of aircraft.To address the challenges and limitations of current high-fidelity MDO methods, this thesis presents a comprehensive framework for aircraft design that integrates aeroelasticity and aircraft dynamics. The framework enables simultaneous optimization of aerodynamic properties based on aeroelastic stiffness and optimization of aeroelastic stiffness based on stability and control characteristics. This ensures that the resulting wing design not only exhibits excellent aerodynamic and structural performance but also meets stability and control requirements throughout its operational envelope.To begin, we formulate the fully-coupled aero-structural-trim (AST) optimization problem by incorporating the aircraft stability and control characteristics into the analysis. Our primary focus lies in efficiently computing aeroelastic sensitivities for a large number of aerodynamic shape and structural size design variables, which is achieved by employing the discrete adjoint method.Second, we integrate a high-fidelity aerodynamics solver (SU2) with a commercial software for structural modeling and aircraft dynamics (NASTRAN) within a large-scale multidisciplinary design, analysis, and optimization framework (OpenMDAO). The OpenMDAO framework orchestrates the execution of coupled analyses, sensitivity analyses essential for gradient-based optimization, and design updates.Third, we apply the AST optimization framework to address the conceptual design of a flexible, tailless fighter aircraft called the efficient supersonic air vehicle (ESAV). The finite element and aerodynamic models utilized during the optimization process are representative of a realistic aircraft and align with industry standards and practices.Finally, we assess the effectiveness of high-fidelity AST optimization framework in terms of providing valuable design insights and discovering novel solutions. We evaluate their impact on crucial aspects such as aircraft performance, computational efficiency, and the accuracy of analysis models. This evaluation allows us to determine the practical utility and effectiveness of these sensitivities in the context of conceptual aircraft design.

English

ISBN: 9798342113199Subjects--Topical Terms:

832698
Aircraft.

A Coupled-Adjoint Framework for High-Fidelity Aero-Structural-Trim Optimization in Aircraft Design /
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520 $a Aircraft design involves solving complex optimization problems that encompass various engineering disciplines, such as aerodynamics, structures, controls, and propulsion. The interdependence among these disciplines has made multidisciplinary design optimization (MDO) methods particularly valuable in the field of conceptual aircraft design.Recent advancements in computational methods, high-performance computing, and efficient gradient-based optimization algorithms have significantly impacted the development of aircraft through MDO. By formulating the design challenge as a mathematical optimization problem and integrating multiple disciplines as well as their interactions within a unified, parameterized model of the system, it is possible to efficiently explore the design space. This MDO approach allows for the systematic resolution of engineering trade-offs and the exploitation of beneficial interactions involving thousands of design variables, leading to faster generation of improved aircraft designs.The integration of high-fidelity computational fluid dynamics (CFD) and finite element analysis (FEA) in MDO has proven to be remarkably successful for aeroelastic wing design. However, certain critical aspects, such as aircraft dynamics, stability, and control requirements, have been largely ignored. In real-world applications, the primary emphasis in aeroelastic wing design shifts from solely maximizing wing performance to carefully tailoring the wing's aeroelastic response. This shift is essential to ensure stable flight dynamics and effective control, which are crucial considerations in the conceptual design of aircraft.To address the challenges and limitations of current high-fidelity MDO methods, this thesis presents a comprehensive framework for aircraft design that integrates aeroelasticity and aircraft dynamics. The framework enables simultaneous optimization of aerodynamic properties based on aeroelastic stiffness and optimization of aeroelastic stiffness based on stability and control characteristics. This ensures that the resulting wing design not only exhibits excellent aerodynamic and structural performance but also meets stability and control requirements throughout its operational envelope.To begin, we formulate the fully-coupled aero-structural-trim (AST) optimization problem by incorporating the aircraft stability and control characteristics into the analysis. Our primary focus lies in efficiently computing aeroelastic sensitivities for a large number of aerodynamic shape and structural size design variables, which is achieved by employing the discrete adjoint method.Second, we integrate a high-fidelity aerodynamics solver (SU2) with a commercial software for structural modeling and aircraft dynamics (NASTRAN) within a large-scale multidisciplinary design, analysis, and optimization framework (OpenMDAO). The OpenMDAO framework orchestrates the execution of coupled analyses, sensitivity analyses essential for gradient-based optimization, and design updates.Third, we apply the AST optimization framework to address the conceptual design of a flexible, tailless fighter aircraft called the efficient supersonic air vehicle (ESAV). The finite element and aerodynamic models utilized during the optimization process are representative of a realistic aircraft and align with industry standards and practices.Finally, we assess the effectiveness of high-fidelity AST optimization framework in terms of providing valuable design insights and discovering novel solutions. We evaluate their impact on crucial aspects such as aircraft performance, computational efficiency, and the accuracy of analysis models. This evaluation allows us to determine the practical utility and effectiveness of these sensitivities in the context of conceptual aircraft design.
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