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AIAA SciTech Forum

作者： Borwankar, Pranav Kapania, Rakesh K. Inoyama, Daisaku Stoumbos, Tom Virginia Polytech Inst & State Univ Kevin T Crofton Dept Aerosp & Ocean Engn Blacksburg VA USA Northrop Grumman Corp Space Syst Engn Tact Space Syst Div Dulles VA 20166 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

The digital transformation of engineering design processes is essential for the aerospace industry to remain competitive in the global market. multidisciplinary design optimization (MDO) frameworks play a crucial role in this transformation by integrating various engineering disciplines and enabling the optimization of complex systems. A multidisciplinary structural analysis and design optimization (MSADO) framework can account for interactions between structural responses. This paper presents an MSADO framework for spacecraft structures utilizing commercial software tools such as Simcenter 3D, Nastran, HEEDS and open-source Python libraries. The proposed framework integrates structural, thermal and acoustic analysis to optimize the spacecraft's overall performance while satisfying multiple design constraints. The framework is applied to the design of a typical spacecraft structure, aiming to optimize structural weight for required structural performance under various static and dynamic loading conditions when the spacecraft is inside the launch vehicle or operating in orbit. Lamination parameter optimization and mixed integer programming are incorporated into the framework to significantly improve optimization performance when composite parts are involved in the design.

关键词： multidisciplinary design analysis and optimization Structural analysis Launch Vehicles Nastran Spacecraft Structures MATLAB Aerospace Industry Digital Transformation Space Vehicle Structure Software Tool

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Comparison of Overwing and Underwing Nacelle Aeropropulsion optimization for Subsonic Transport Aircraft

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JOURNAL OF AIRCRAFT 2024年第2期61卷 638-653页

作者： Ahuja, Jai Lee, Chung Hyun Perron, Christian Mavris, Dimitri N. Georgia Inst Technol Sch Aerosp Engn Aerosp Syst Design Lab Atlanta GA 30332 USA

This research compares a forward-mounted overwing nacelle configuration to a conventional underwing nacelle for a single-aisle transport aircraft. We focus on characterizing the impact of the overwing placement on cruise fuel burn. To this end, we optimize both configurations under similar constraints and design processes. We use coupled computational fluid dynamics and propulsion cycle analysis with Gaussian process-based adaptive sampling in a multistage design process. The particular overwing design has a 4% higher fuel flow than the underwing design at cruise conditions. However, a postoptimization nacelle placement study illustrates that this fuel burn difference can drop to 2-3% if the overwing nacelle is moved farther forward in our design space without accounting for any resulting structural weight changes.

关键词： Numerical Propulsion System Simulation Cumulative Distribution Function Aerodynamic Interference Aerodynamic Performance multidisciplinary design analysis and optimization Computational Modeling Computational Fluid Dynamics Aircraft Overwing Nacelle

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Benefits and Challenges of Electric Propulsion for Commuter Aircraft

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JOURNAL OF AIRCRAFT 2024年第1期61卷 7-24页

作者： Kruger, Michael Uranga, Alejandra Univ Southern Calif Dept Aerosp & Mech Engn 3650 McClintock Way OHE 500P Los Angeles CA 90089 USA

This paper presents the Library for Unified Conceptual Aircraft Synthesis (LUCAS) sizing and optimization framework, which is largely based on Stanford's Stanford University Aerospace Vehicle Environment (SUAVE). LUCAS is applied to a commuter mission carrying 19 passengers. Results show that energy usage benefits depend on mission range and electrical component technology and that reserve requirements play a significant role in the feasibility of electrified aircraft. It is found that storing more energy in batteries rather than fuel reduces the mission energy requirement at the expense of aircraft weight growth. All-electric aircraft could provide onboard energy savings of upward of 30% for a 180 km mission, but this would only become feasible if battery specific energy reached the high value of 900 W & sdot;h/kg. Range could be increased to 550 km if part of the reserve mission requirements is relaxed. Under more realistic technology assumptions, a hybrid design storing energy in fuel and batteries could fly commuter missions with energy savings of 6%. A beneficial use case of hybrid configurations is a mode of operation where the aircraft uses only batteries during the main mission and fuel to store all the reserve energy. If reserves are not required for a particular flight, energy savings are still maximized, while the availability of fuel ensures certification requirements are met with fewer penalties.

关键词： Electric Propulsion Hybrid Electric Aircraft Propulsive Efficiency Freestream Velocity Aeropropulsive design optimization Aircraft design Advanced Air Transportation Technology multidisciplinary design analysis and optimization Aircraft design Process Aircraft Conceptual design

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Electrothermal Coupling Methodologies and Their Influence on the optimization of Aircraft Electric Motors

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AIAA JOURNAL 2024年第7期62卷 2659-2677页

作者： Babcock, Tucker McKeever, Bryan Hicken, Jason E. Rensselaer Polytech Inst Dept Mech Aerosp & Nucl Engn Troy NY 12180 USA

This work presents a fully coupled electrothermal motor analysis and optimization framework, where the motor's electromagnetic performance depends on its temperature distribution, and the temperature distribution simultaneously depends on its electromagnetic performance. Notably, we analytically compute derivatives through this nonlinear, multidisciplinary analysis using coupled adjoints, which enables the exploration of high-dimensional design spaces. We demonstrate the framework on a series of optimization problems that investigate the effect of feedback coupling and serve to highlight the framework's utility and flexibility. Furthermore, our results indicate that modeling the motor's electrothermal coupling is critical to accurate performance prediction. We show that designs optimized using a feedforward-coupled model are found to be either infeasible or nonoptimal under the fully coupled feedback analysis;both conditions are unacceptable for aircraft applications, in which performance is critical.

关键词： Synchronous Motors Convective Heat Transfer Coefficient Thermal Modeling and analysis multidisciplinary design analysis and optimization multidisciplinary design optimization Electromagnetic analysis

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Automatic Continuous Thrust Control for Supersonic Transport Takeoff Noise Reduction

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JOURNAL OF AIRCRAFT 2024年第1期61卷 291-306页

作者： Voet, Laurens J. A. Prashanth, Prakash Speth, Raymond L. Sabnis, Jayant S. Tan, Choon S. Barrett, Steven R. H. MIT Cambridge MA 02139 USA MIT Dept Aeronaut & Astronaut Cambridge MA 02139 USA

Advanced takeoff trajectories are proposed for supersonic transport noise reduction by capitalizing on excess engine thrust and improved aerodynamic efficiency at higher takeoff speeds. These novel trajectories use i) automatic continuous control of thrust, ii) increased takeoff speed, and iii) reduced cut-back altitude, compared to conventional pilot-initiated discrete thrust cut-back procedures currently used for subsonic transport. In this paper, we develop an optimal control framework to assess the attributes of effective takeoff trajectories for supersonic transport that yield minimum noise levels. We quantify the noise reduction potential of advanced takeoff trajectories for the eight-passenger, 55-metric-ton, Mach-1.4 NASA Supersonic Technology Concept Airplane. For the aircraft examined, these advanced takeoff trajectories enable a cumulative certification noise reduction of 10.6 EPNdB, which is insufficient to meet current subsonic transport noise limits.

关键词： Effective Perceived Noise Level Supersonic Commercial Air Transport Noise Abatement Departure Procedure Aircraft Noise Aircraft Engine Noise Noise Reduction Optimal Control multidisciplinary design analysis and optimization

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High-Dimensional Bayesian optimization Using Both Random and Supervised Embeddings

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AIAA JOURNAL 2024年第1期63卷 162-173页

作者： Priem, Remy Diouane, Youssef Bartoli, Nathalie Dubreuil, Sylvain Saves, Paul Tech Unit DGA Maitrise Informat Aeronaut Syst F-35170 Bruz France Polytech Montreal Math & Ind Engn Dept Montreal PQ H3T 1N8 Canada GERAD Math & Ind Engn Dept Montreal PQ H3T 1N8 Canada Univ Toulouse DTIS ONERA F-31000 Toulouse France Univ Toulouse Informat Proc & Syst Dept Federat ENAC ISAE SUPAERO ONERA F-31000 Toulouse France

Bayesian optimization (BO) is one of the most powerful strategies to solve computationally expensive-to-evaluate blackbox optimization problems. However, BO methods are conventionally used for optimization problems of small dimension because of the curse of dimensionality. In this paper, a high-dimensionnal optimization method incorporating linear embedding subspaces of small dimension is proposed to efficiently perform the optimization. An adaptive learning strategy for these linear embeddings is carried out in conjunction with the optimization. The resulting BO method, named efficient global optimization coupled with random and supervised embedding (EGORSE), combines in an adaptive way both random and supervised linear embeddings. EGORSE has been compared to state-of-the-art algorithms and tested on academic examples with a number of design variables ranging from 10 to 600. The obtained results show the high potential of EGORSE to solve high-dimensional blackbox optimization problems, in terms of both CPU time and the limited number of calls to the expensive blackbox simulation.

关键词： Bayesian optimization Cumulative Distribution Function multidisciplinary design analysis and optimization Computer Programming and Language Numerical analysis Robots optimization Algorithm Aircraft design Robot Kinematics Flight Recorder

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Enforcing Work Conservation in Modular Aeroelastic Coupling For multidisciplinary design optimization

Enforcing Work Conservation in Modular Aeroelastic Coupling ...

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AIAA SciTech Forum

作者： van Schie, Sebastiaan P. C. Warner, Michael A. P. Fletcher, Andrew H. Hwang, John T. Univ Calif San Diego Dept Mech & Aerosp Engn 9500 Gilman Dr La Jolla CA 92093 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

There is significant interest in solving multidisciplinary design analysis and optimization (MDAO) problems, in which models of various disciplines are used simultaneously. As mentioned in NASA's CFD Vision 2030 report this has often happened at the cost of significant software development efforts and one-off model coupling implementations. This work investigates a methodology for modular aeroelastic coupling for use in MDAO problems by using a Solver-Independent Field Representation (SIFR) as intermediate configuration between solid and fluid solvers. Each solver is integrated into SIFR through a standardized approach that allows for force consistency and aeroelastic work conservation. The aim of leveraging such an approach for aeroelasticity is to significantly reduce the development and implementation cost of coupled aeroelastic analysis for MDAO. In this work we implement a coupled aeroelastic approach through SIFR and use it to carry out static simulations of an aircraft wing. We derive various sets of algebraic constraints for work conservation that can inform model developers and analysts when defining coupled aeroelastic analyses. We apply the coupling methodology to a Vortex Lattice Method model and FEniCS-based Finite Element and carry out coupled simulations of an aircraft wing, in which it's shown that we can indeed obtain force consistency and work conservation with SIFR.

关键词： multidisciplinary design analysis and optimization Aircraft Wings Aeroelastic analysis Vortex Lattice Method Software Development Aerodynamic Force Lagrange Multipliers Linear Mapping Flight Sciences Aurora

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multidisciplinary Spacecraft and Trajectory Uncertainty Quantification for an Interplanetary Mission

Multidisciplinary Spacecraft and Trajectory Uncertainty Quan...

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AIAA SciTech Forum

作者： Naidu, Siddhesh Leifsson, Leifur Purdue Univ Sch Aeronaut & Astronaut W Lafayette IN 47907 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Low tolerance to failure in space systems makes uncertainty quantification vital to its design and optimization. In this work, a sequential multidisciplinary analysis framework is created to optimize and quantify the uncertainties associated with the spacecraft and its trajectory. The engine of the spacecraft is modelled using the rocket propulsion analysis (RPA) tool, and the trajectory is modelled using NASA's general mission analysis tool (GMAT). The selected mission is an interplanetary transfer trajectory from Earth to Mars using B-plane targeting. The analysis and optimization framework OpenMDAO is used to build a multidisciplinary model within which RPA and GMAT are integrated in to sequentially analyze the spacecraft engine and trajectory and then optimize it. The uncertainty associated with the launch date is propagated to the mission trajectory analysis and a Monte Carlo simulation is used to quantify the uncertainty in the spacecraft's time of flight, velocities, and fuel consumed. For a 20-day launch window, the variation in the velocity was computed to be 2-4 km/s and the variation in the fuel consumed was 300 kg. Uncertainty in the engine performance parameters resulted in fuel consumption variations of 0.25 kg during the TCM burn and 30 kg during the MOI burn.

关键词： Uncertainty Quantification Interplanetary Mission Planets General Mission analysis Tool OpenMDAO Fuel Consumption multidisciplinary design analysis and optimization Rocket Propulsion System Space Systems Monte Carlo Simulation

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System Integration Study for a Hybrid-Electric Commuter Aircraft Concept with a Solar Auxiliary Power System

System Integration Study for a Hybrid-Electric Commuter Airc...

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AIAA SciTech Forum

作者： Licheva, Gala Mohan, Vijesh Jeyaraj, Andrew K. Bamrah, Parush Mir, Mohammad Liscouet-Hanke, Susan Concordia Univ Gina Cody Sch Engn & Comp Sci Montreal PQ H3G IM8 Canada

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Commuter and regional aircraft are promising candidates as testbeds for technologies that aim to reduce emissions. Among these technologies, the electrification of the propulsion system and the subsystem architectures is a potential research avenue. However, to find promising candidate architectures, particularly in a retrofitting context, multiple design disciplines must be considered in combination with systems integration. This paper investigates the retrofitting of the Dornier 228 regional commuter aircraft with a combination of hybrid-electric propulsion, more-electric subsystems, and an auxiliary solar power system, using a conceptual multidisciplinary design analysis and optimization (MDAO) framework. It includes an auxiliary solar power system sizing and performance analysis tool, which allows the analysis of power generated by aircraft-mounted solar panels and the associated impact on aircraft weight and mission fuel burn. The sensitivity of such a system concept to solar panel technology, aircraft operation, and available solar radiation is explored in conjunction with system electrification and hybridization of the propulsion system. Systems integration and safety considerations are also studied. The authors first present a step-by-step evaluation of the effect of propulsion hybridization, system electrification, and the solar power system individually on the aircraft performance and emissions profile. The impact of the combination of these three technologies is assessed on the aircraft mission fuel burn and CO2 emissions. Finally, this paper provides insights into the viability of such a combined system for commuter aircraft missions, investigates how each system contributes to the overall fuel burn reduction at the aircraft level and explores the management of battery weight by using the electric component of the hybrid-electric power train in specific combinations of flight phases.

关键词： Commuter and Regional Aircraft Energy Density Electrical Systems Solar Power Systems Flight Phases Hybrid Electric Propulsion Propulsion System multidisciplinary design analysis and optimization Electric Power System Aircraft Operations

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Assessment of Techniques for Global Sensitivity Analyses in Conceptual Aircraft design

Assessment of Techniques for Global Sensitivity Analyses in ...

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AIAA Aviation Forum

作者： Alder, M. Froehler, B. Ahmed, T. Skopnik, A. German Aerosp Ctr eV DLR Inst Syst Architectures Aeronaut Digital Methods Syst Architecting Hamburg Germany German Aerosp Ctr eV DLR Inst Syst Architectures Aeronaut Aviat Syst Concepts & Evaluat Hamburg Germany Tech Univ Chemnitz Chemnitz Germany

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The design of novel air transportation systems typically targets market introduction several years in the future and is therefore generally characterized by various assumptions, for example on the evolution of materials, manufacturing technologies and subsystem performance. These assumptions are inherently subject to uncertainties that need to be considered to make robust design decisions already in early stages of the design process. To manage the complexity of the design problem and the vast design spaces considered, the execution of sensitivity studies aims at identifying the most influential uncertain factors. While observing these, the factors with low impact can be neglected in the considerations. Nowadays, the majority of sensitivity studies conducted in aircraft design are based on local techniques, i.e. input variables are successively varied around a fixed, single point in the design space. Although this method is straightforward and easy to understand, it only provides limited informative value. Global sensitivity analyses (GSA) have the potential to overcome this limitation by quantifying the sensitivity characteristics of the entire design space. However, its application is numerically expensive and it is not always obvious which of the various GSA techniques fits best to the individual use cases. Therefore, the objective of this work is to assess the applicability of four different state-of-the-art GSA techniques, being the methods of Sobol', FAST, Morris, and Polynomial Chaos Expansion, to application cases representing the numerical challenges faced within conceptual aircraft design. These challenges are the high-dimensionality of the design space due to its multidisciplinary nature, the nonlinearity of the model equations involved, and the computational intensity of the design process. Through a thorough investigation of the convergence properties and a comparison of the resulting sensitivity measures, recommendations for the best choice of GSA meth

关键词： multidisciplinary Aircraft design Air Transportation System Robust design Zero Lift Drag Coefficient Civil Transport Aircraft Surrogate Model Acquisition Costs Materials Science Surface Modeling multidisciplinary design analysis and optimization

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