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

共 115 条记录，以下是61-70 订阅

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Gradient-based sizing optimization of power-beaming-enabled aircraft

Gradient-based sizing optimization of power-beaming-enabled ...

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AIAA Aviation Forum

作者： Orndorff, Nicholas C. Wang, Bingran Ruh, Marius L. Fletche, Andrew H. Hwang, John T. Univ Calif San Diego Dept Mech & Aerosp Engn La Jolla CA 92092 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Power beaming is a potentially disruptive technology for aircraft that would lead to unprecedented increases in some aspects of mission performance. Existing aircraft design methods often rely on empirical data and energy-based formulas for size and performance estimations. These methods are not applicable to power-beaming-enabled aircraft, which have reduced needs for onboard energy storage. In this paper, we investigate the dominant variables that have the strongest influence on the size and design of a laser-powered, unmanned, high-altitude aircraft. This is accomplished by constructing several physics-based models within a large-scale design optimization framework. Using this framework, we perform a baseline optimization that minimizes total mass, demonstrating that our method can produce a feasible and optimal airplane design. By varying several parameters within the optimization problem we also determine the sensitivity of the airplane design to altitude, payload, endurance, and distance from the laser source. Among other things, we find that total mass increases exponentially with onboard battery power, and that total mass increases very little with distance until 600 km after which the mass begins to increase exponentially.

关键词： High Altitude Aircraft multidisciplinary design and optimization Aircraft design Energy Storage Kutta Joukowski Theorem Convective Heat Transfer Coefficient Aircraft Configurations Wing Box Structure Structural Analysis Finite Element Method

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Rapid Aerostructural optimization of Wing-Propeller Systems

Rapid Aerostructural Optimization of Wing-Propeller Systems

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AIAA SciTech Forum

作者： Exalto, Joaquin Pacini, Bernardo Kaneko, Shugo Martins, Joaquim R. R. A. Hoogreef, Maurice F. M. Univ Michigan Ann Arbor MI 48109 USA Univ Michigan Dept Mech Engn Ann Arbor MI 48109 USA Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Delft Univ Technol Delft Netherlands Delft Univ Technol Fac Aerosp Engn Kluyverweg 1 NL-2629 HS Delft Netherlands

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Propeller-wing configurations are expected to return to the aviation industry due to their high propulsive efficiency and applicability in urban and regional air mobility. A knowledge gap exists around wing-propeller optimization because of the complexity of the propeller-wing system and the absence of a computationally efficient way to assess the coupled system. This paper addresses this gap by providing and validating a computationally efficient, mid-fidelity framework. The paper presents optimization results and recommendations for future iterations of the framework. The TU Delft PROWIM propeller is optimized with the framework, comparing sequential isolated optimization, trim optimization, and fully coupled optimization. The studies gives a conservative estimate of the efficiency gains that can be achieved by using coupled optimization, as compared to isolated optimization. Lastly, recommendations are given for future studies, such as including a battery weight model and including swirl velocities. It is expected that such model additions will affect the optimization results, and further emphasize the importance of coupled aerostructural optimization.

关键词： Aerostructural optimization Propeller Performance Aviation Regional Air Mobility Propulsive Efficiency Wing Configurations Aerodynamic optimization Angle of Attack Aerostructural Wing optimization multidisciplinary design and optimization

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Free-Flight Flutter Constraint in Gradient-BasedWing Structural optimization

Free-Flight Flutter Constraint in Gradient-BasedWing Structu...

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AIAA SciTech Forum

作者： Rosatelli, Patrizio Cesnik, Carlos E. S. Lupp, Christopher A. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Air Force Res Lab Wright Patterson AFB OH 45433 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Aircraft with high aspect ratio wings are more likely to present geometric nonlinear effects and couplings with the flight dynamics that impact flutter calculation. This paper describes a method to account for that as part of a multidisciplinary design optimization (MDO) framework. Due to computational cost and robustness considerations, the flutter constraint is calculated based on a condensed model of the structure. This is obtained based on an equivalent beam representation of the high-aspect-ratio wing, so to make the stability considerations computationally tractable in an optimization. A surrogate problem is created to represent other constraints for the problem and to enable the demonstration of the new flutter constraint. OpenMDAO is the optimization framework used for handling the various features of the optimization, facilitating both the coupling of the necessary disciplines and the computation of derivatives for the gradient-based approach. The derivatives related to the flutter constraint are computed using AD in reverse mode. To numerically exemplify the approach, the optimization of a blended-wing body aircraft is performed and the importance of nonlinear aeroelastic considerations in the outcome of the optimization is assessed.

关键词： Structural optimization High Aspect Ratio multidisciplinary design and optimization Blended Wing Body Configurations OpenMDAO Flight Dynamics Wing Box Aerodynamic Coefficients Aeroelastic Instability Aerodynamic Performance

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multidisciplinary design and Mission Analysis of an Electric Amphibious Flying Vehicle

Multidisciplinary Design and Mission Analysis of an Electric...

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AIAA Aviation Forum

作者： Shihua, James M. Lyu, Yuan Liem, Rhea P. Hong Kong Univ Sci & Technol HKUST Dept Mech & Aerosp Engn Hong Kong Peoples R China

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Developing an electric amphibious flying vehicle faces multidisciplinary design challenges in addition to those of a conventional aircraft. For instance, hydrodynamics, electric propulsion system, and power battery are a few examples of distinct disciplines concerning this unique type of vehicles. In this paper, we propose a mission analysis framework for such a vehicle which comprehends various high-fidelity disciplinary models that combine computational and experimental results. The framework takes into consideration that real operations of the said vehicle typically require more agility and versatility than their conventional counterparts. The framework is aimed to realistically model the operation requirements that are physically consistent with the flight dynamics of all mission segments. By solving a set of residual equations constructed based on the states of different segments, we can ensure the consistency and continuity in the flight mission representation and analysis. The mission analysis is constructed such that explicit definitions of certain mission parameters are not required since they are already implicitly modeled in the procedure. The proposed framework is demonstrated by performing a pre-flight mission analysis for an electric amphibious flying vehicle of our design. Our preliminary results show that the predicted mission profile is physically feasible and yields vehicle states that are consistent with the prescribed operation requirements. The framework lays a fundamental for a mission-based optimization for the above-mentioned vehicle in the future.

关键词： Hybrid Electric Propulsion Hydrodynamics Flight Path Angle Amphibious Aircraft Calibrated Airspeed Numerical Integration multidisciplinary design and optimization Lift Coefficient Reynolds Averaged Navier Stokes Hybrid Electric Aircraft

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design-Sensitive Conceptual Aircraft Weight Estimation Utilizing a Modular Multi-Method Framework

Design-Sensitive Conceptual Aircraft Weight Estimation Utili...

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AIAA SciTech Forum

作者： Stamm, Ian W. Woods, Daniel C. Air Force Res Lab Booz Allen Hamilton Wright Patterson AFB OH 45433 USA Air Force Res Lab Struct Technol Branch Wright Patterson AFB OH 45433 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

In the context of aircraft design, a reasonable accounting for mass properties is crucial throughout the design process, including in the conceptual stage where early weight predictions are used to assess mission performance and inform subsequent engineering decisions. Though empirical methods have traditionally been employed for vehicle weight estimation, such approaches rely on historical data and show less utility for novel configurations, particularly as new material systems, advanced fabrication methods, and large-scale design optimization processes are introduced for modern aircraft design. In contrast, estimating mass properties with detailed computer models and finite element-based analyses can capture design aspects with greater fidelity and sensitivity (particularly for primary structure), but cannot directly inform estimates for the sizable weight contributions not modeled;such methods also generally require design details not available in conceptual design. In this work, we thus propose a framework that integrates an array of existing empirical methods with physics-informed analytical and numerical methods to deliver a more tailored, design-sensitive weight estimation approach. Within this framework, a common set of conceptual design parameters is specified to generate a basic geometric representation and then passed to constituent weight estimation methods, or modules, with primary or secondary loadbearing structure handled through analytical or finite element-based sizing methods. With tailored use of empirical, analytical, and "bottom-up" estimates introduced elsewhere, the weight results across modules and fidelity levels are placed on a common footing and modified through a least- squares regression scheme to generate the final vehicle weight breakdowns at the level of sections or systems and, where appropriate, components. By drawing on traditional or empirical methods in combination with newer, physics-based approaches, this framework is intended

关键词： Transport Aircraft Aircraft design Aircraft Configurations multidisciplinary design and optimization Finite Element Analysis Structural Element McDonnell Douglas Aerodynamic Loads Maximum Takeoff Weight Graphical User Interface

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Geometrically Nonlinear High-fidelity Aerostructural optimization Including Geometric design Variables

Geometrically Nonlinear High-fidelity Aerostructural Optimiz...

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AIAA Aviation Forum

作者： Gray, Alasdair C. Kennedy, Graeme J. Martins, Joaquim R. R. A. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Over the past decade, advances in MDO have enabled the optimization of aircraft wings using high-fidelity simulations of their coupled aerodynamic and structural behavior. Using RANS CFD and detailed structural finite element wingbox models, the aerodynamic shape and internal structural sizing of a wing can be optimized concurrently to tailor the aeroelastic behavior of the wing and optimally trade-off drag and structural mass. This capability makes MDO a key enabling technology for the next generation of efficient high-aspect-ratio transport aircraft. However, as their aspect-ratios increase, these wings increasingly exhibit geometrically nonlinear behavior that cannot be correctly modeled by typical linear structural analysis methods. This paper builds on our previous work, demonstrating the first simultaneous optimization of a wing's aerodynamic shape and structural sizing using high-fidelity geometrically nonlinear models. Our methods are implemented in the open-source finite element library, TACS, and include a geometrically nonlinear shell element formulation, an efficient nonlinear solver, and a constitutive model for stiffened shells. We then demonstrate the ability to couple these nonlinear structural analysis tools to a high-fidelity RANS CFD solver using a geometrically nonlinear load and displacement transfer scheme. Finally we use this capability to perform a series of fuel-burn minimizations of a single-aisle commercial transport aircraft wing featuring 578 design variables and 1287 constraints. Our results suggest that geometrically nonlinear effects noticeably change the optimum trade-off between drag and structural mass at aspect-ratios typical of modern transport aircraft, even if the attained fuel-burn is similar.

关键词： Aerostructural optimization High Aspect Ratio Aerospace Structure Reynolds Averaged Navier Stokes Structural Finite Elements Computational Fluid Dynamics Geometrically Nonlinear Analysis Commercial Aircraft multidisciplinary design and optimization Lift to Drag Ratio

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The "fish-mouth" actuator: design issues and test results

The "fish-mouth" actuator: Design issues and test results

引用

13th International Conferenc on Adaptive Structures and Technologies

作者： Campanile, LF Keimer, R Breitbach, EJ German Aerosp Ctr DLR D-38108 Braunschweig Germany

ISBN: (纸本)0849319277

The so-called "fish-mouth actuator", developed at DLR in the framework of the Adaptive Wing project (ADIF), is a compact hybrid actuator based on the interaction of a shape memory material and a composite flexible mechanism. The actuator offers a high effective strain (ratio between actuator's stroke and mounting dimension in the activation direction) and is therefore particularly interesting for the shape control of thin surfaces. In the ADIF project, the actuator development was focused on the realization of a wind-tunnel model for an adaptive wing with transonic bump. The actuator is designed and tested for a maximum stroke of 2 mm and a maximum force of 200N. Its thickness (in activation direction) amounts to about 8 mm. If used with a feedback control system, it can reach a displacement precision of less than 1 mum. More than 400 single actuators were built and tested;84 of them were integrated in the final system. In this paper, several design issues are discussed that are typical for such fully coupled hybrid systems. The design analysis and procedure used for the actuator development is described and a choice of experimental results is shown and discussed. The reported design philosophy and the related discussion include many concepts and solutions of general relevance which can be adopted for the development of similar hybrid actuators in the future.

关键词： compliant mechanisms shape memory alloys multidisciplinary design and optimization shape control

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AI-Driven multidisciplinary Conceptual design of Unmanned Aerial Vehicles

AI-Driven Multidisciplinary Conceptual Design of Unmanned Ae...

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AIAA SciTech Forum

作者： Karali, Hasan Inalhan, Gokhan Tsourdos, Antonios Cranfield Univ Sch Aerosp Transport & Mfg Cranfield MK43 0AL England Cranfield Univ Cranfield MK43 0AL England

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents a multidisciplinary conceptual design framework for unmanned aerial vehicles based on artificial intelligence-driven analysis models. This approach leverages AI-driven analysis models that include aerodynamics, structural mass, and radar cross-section predictions to bring quantitative data to the initial design stage, enabling the selection of the most appropriate configuration from various optimized concept designs. Due to the design optimization cycle, the initial dimensions of key components such as the wing, tail, and fuselage are provided more accurately for later design activities. Simultaneously, the generated structure enables more suitable design point selection through the feedback loop within the design iteration. Therefore, in addition to reducing design costs, this approach also offers a substantial time advantage in the overall design process.

关键词： Unmanned Combat Aerial Vehicle Aerodynamic Shape optimization Monostatic Radar multidisciplinary design and optimization Aircraft Configurations Artificial Intelligence Feedback Loop Multilayer Perceptron Aerodynamic Performance Structural Element

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A Novel Approach to Trimming Geometrically Nonlinearly Deformed Aircraft for Gradient-Based optimization Problems

A Novel Approach to Trimming Geometrically Nonlinearly Defor...

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AIAA SciTech Forum

作者： Lupp, Christopher A. Rosatelli, Patrizio Cesnik, Carlos E. S. Air Force Res Lab Air Vehicles Directorate Wright Patterson AFB OH 45433 USA Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Accounting for aeroelastic effects has become increasingly important in multidisciplinary analysis and optimization as designers employ high-aspect-ratio wings to obtain more fuel-efficient aircraft. Ensuring trim is paramount for many aeroelastic analyses such as free-flight flutter or transient studies. While aeroelastic trim has been studied in the past, solutions compatible with gradient-based optimization, particularly for nonlinearly deformed structures, have been elusive. This paper introduces a new approach to obtaining aeroelastic trim while providing efficient gradients needed by gradient-based optimization. Numerical studies benchmarking the new approach are presented using a notional blended wing body configuration and a geometrically nonlinear beam formulation. However, the proposed approach is fidelityagnostic and can be applied to higher-fidelity coupled aeroelastic problems.

关键词： Flight Vehicle Blended Wing Body Configurations High Aspect Ratio Influence Coefficients multidisciplinary design and optimization Aircraft Configurations Control Surfaces Nonlinear Aeroelasticity Newton Raphson Method Aerodynamics

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Uncertainty Quantification-Based Switching Control Method for Vision-Based Object Tracking in Unmanned Aerial Vehicles

Uncertainty Quantification-Based Switching Control Method fo...

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AIAA SciTech Forum

作者： Castano, Antonio Fernandez Pattont, Caleb Yoon, Hyung-Jin Voulgaris, Petros Univ Nevada Mech Engn Dept 1664 N Virginia St Reno NV 89557 USA Tennessee Technol Univ Mech Engn Dept 1 William L Jones Dr Cookeville TN 38505 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Ensuring safe aerial robotics has become paramount with the increasing utilization of UAVs (Unmanned Aerial Vehicles) in dense urban environments. Machine Learning-based object detection methods that process camera sensor images have become essential in planning and navigating UAVs through these environments. However, like any machine learning tool, the object detection model is prone to aleatoric and epistemic uncertainties. This paper introduces a perception-control framework incorporating a switching controller to improve robustness against uncertain measurements processed by an object detector. The proposed mechanism enables switching between different controllers based on the level of uncertainty quantified. This approach aims to enhance the reliability and safety of UAV operations in challenging environments. We tested this framework using a simulated environment where a UAV tracks an object using the YOLOv5 object detector. Our results demonstrate that the proposed control framework can mitigate the uncertainties of the machine learning perception by decreasing the system gain from the sensor noise to the output of the vehicle dynamics.

关键词： Unmanned Aerial Vehicle Uncertainty Quantification Sensors Reinforcement Learning Aerial Robotics Convolutional Neural Network Extended Kalman Filter Linear Time Invariant multidisciplinary design and optimization Quad Rotor

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