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Multidisciplinary Design optimization of Low-Boom Supersonic Aircraft with Mission Constraints

AIAA JOURNAL 2021年第1期59卷 165-179页

作者： Li, Wu Geiselhart, Karl NASA Langley Res Ctr Aeronaut Syst Anal Branch Hampton VA 23681 USA

Conceptual design of low-boom supersonic aircraft is heavily dictated by aircraft volume and lift distributions. These unique design characteristics make it a challenge to enforce mission requirements (such as static margins and trim requirements) during design optimization. This low-boom design challenge is resolved by using reversed equivalent area targets for low-fidelity low-boom inverse design and a block coordinate optimization (BCO) method for multidisciplinary design optimization (MDO). The corresponding low-boom MDO problem includes aircraft mission constraints on ranges, cruise speeds, trim for low-boom cruise, static margins for takeoff/cruise/landing, takeoff/landing field lengths, approach velocity, and tail rotation angles for trim at takeoff/landing, as well as fuselage volume constraints for passengers and main gear storage. The BCO method is developed to optimally resolve the conflicts between the low-boom inverse design objective and other design constraints. This method is successfully applied to design a low-boom supersonic configuration that carries 40 passengers, flies a low-boom mission with cruise Mach of 1.6 and range of 2500 nm, and cruises overwater at Mach 1.8 with range of 3600 nm. The generated configuration satisfies all specified mission constraints and has the potential to match a reversed equivalent area target with ground noise level below 70 PLdB.

关键词： Supersonic Aircraft MDO Aircraft Configurations Aerodynamic Performance Aerodynamic Center Takeoff and Landing CFD Analysis flight optimization system Finite Element Analysis Sonic Booms

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Multi-Objective optimization of a Turbofan for an Advanced, Single-Aisle Transport

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JOURNAL OF AIRCRAFT 2011年第5期48卷 1795-1805页

作者： Berton, Jeffrey J. Guynn, Mark D. NASA Glenn Res Ctr Multidisciplinary Design Anal & Optimizat Branch Cleveland OH 44135 USA NASA Langley Res Ctr Aeronaut Syst Anal Branch Hampton VA 23681 USA

Considerable interest surrounds the design of the next generation of single-aisle commercial transports in the Boeing 737 and Airbus A320 class. Aircraft designers will depend on advanced, next-generation turbofan engines to power these airplanes. The focus of this study is to apply single- and multi-objective optimization algorithms to the conceptual design of ultrahigh bypass turbofan engines for this class of aircraft, using NASA's Subsonic Fixed Wing Project metrics as multidisciplinary objectives for optimization. The independent design variables investigated include three continuous variables: sea level static thrust, wing reference area, and aerodynamic design point fan pressure ratio, and four discrete variables: overall pressure ratio, fan drive system architecture (i.e., direct- or gear-driven), bypass nozzle architecture (i.e., fixed- or variable geometry), and the high- and low-pressure compressor work split. Ramp weight, fuel burn, noise, and emissions are the parameters treated as dependent objective functions. These optimized solutions provide insight to the ultrahigh bypass engine design process and provide information to NASA program management to help guide its technology development efforts.

关键词： Airbreathing Engine Twin Aisle Aircraft Landing Gear Overall Pressure Ratio flight optimization system Combustors Low Pressure Turbine Propulsive Efficiency Aerodynamic Design Fuel Consumption

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Designing for a Green Future: A Unified Aircraft Design Methodology

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JOURNAL OF AIRCRAFT 2010年第5期47卷 1789-1797页

作者： Kernstine, Kemp Boling, Bryan Bortner, Latessa Hendricks, Eric Mavris, Dimitri Georgia Inst Technol Dept Aerosp Engn Atlanta GA 30332 USA

Aristotle once said "the whole is more than the sum of its parts." It is in Aristotle's words that a basis for a greener aviation industry can be found. By looking at the whole, the aerospace community can make the entire air transportation system sustainable for generations to come. The effect of aviation on the environment is a multifaceted problem with far reaching consequences if addressed improperly. For this reason, the proposed methodology provides a strategic planning capability for environmental technologies. This unified methodology is a top-down-bottom-up approach starting and ending with the air transportation system, and is intended to align technology selection with an organization's long term environmental concerns. The objective is to systematically identify technologies worth investment based on their environmental impact throughout the future air transportation system. This unified methodology for green design provides the fundamental framework to make purposeful technology selections and investment decisions to meet the environmental needs of the future.

关键词： Aircraft Design Air Transportation system Alternative Fuels Aircraft Configurations Aircraft Manufacturing Air Traffic Management flight optimization system Thrust to Weight Ratio Energy Independence Earth

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Reduced-Order Modeling of a High-Fidelity Propulsion system Simulation

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AIAA JOURNAL 2011年第8期49卷 1665-1682页

作者： Lee, Kyunghoon Nam, Taewoo Perullo, Christopher Mavris, Dimitri N. Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Aerosp Syst Design Lab Atlanta GA 30332 USA

Ever stringent aircraft design requirements on simultaneous reduction in fuel consumption, emissions, and noise necessitate innovative, integrated airframe designs that require concurrent engine designs. To fulfill these design challenges, aerospace engineers have relied on a physics-based engine modeling environment, such as the numerical propulsion system simulation. To expedite the use of numerical propulsion system simulation in aircraft design, this research proposes a methodology for the reduced-order modeling of numerical propulsion system simulation by incorporating the following two techniques: probabilistic principal component analysis for basis extraction and neural networks for weighting coefficient prediction. To efficiently achieve an empirical orthogonal basis, this research capitalizes on an expectation-maximization algorithm for probabilistic principal component analysis to handle numerical propulsion system simulation engine decks that typically lack some data due to failed offdesign performance analyses;they result from the numerical instabilities present in the Newton-Raphson method used within numerical propulsion system simulation to find a converged solution at a given flight condition. In addition, to effectively explore a weighting coefficient space, this research uses neural networks to deal with six numerical propulsion system simulation engine modeling parameters. As a proof of concept, the proposed numerical propulsion system simulation reduced-order modeling method is applied to a numerical propulsion system simulation turbofan engine model usually employed for conventional civil transport aircraft. Comprehensive prediction quality investigations reveal that engine performance metrics estimated by the reduced-order numerical propulsion system simulation model show considerably good agreement with those directly obtained by numerical propulsion system simulation. Furthermore, the reduced numerical propulsion system simulation engine mode

关键词： Propulsion system Feedforward Neural Network flight optimization system Aircraft Design Aerospace Engineering Airframes Fuel Consumption Transport Aircraft Turbofan Engines Newton Raphson Method

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Reasonable design space approach to response surface approximation

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JOURNAL OF AIRCRAFT 1999年第1期36卷 308-315页

作者： Balabanov, VO Giunta, AA Golovidov, O Grossman, B Mason, WH Watson, LT Haftka, RT Virginia Polytech Inst & State Univ Multidisciplinary Anal & Design Ctr Adv Vehicles Blacksburg VA 24061 USA Univ Florida Dept Aerosp Engn Mech & Engn Sci Gainesville FL 32611 USA

Response surface approximations have become very popular as a tool for multidisciplinary optimization, However, the accuracy of these models is a major concern. One method to increase the accuracy of response surface approximations is to construct them only for the portion of the design space that represents reasonable designs, Our paper describes the methodology underlying this reasonable design space approach. This methodology is illustrated using two examples involving multidisciplinary optimization of a high-speed civil transport model, In these examples, low-fidelity analyses are used to estimate the boundary of the reasonable design space. Within the reasonable design space, response surface models are constructed, based on results from higher-fidelity analyses. The accuracy of the response surface models created with and without using the reasonable design space approach is compared, and the advantages of employing response surface models created via the reasonable design space approach are demonstrated.

关键词： High Speed Civil Transport Surface Modeling Robust Design Simulation flight optimization system Control Derivatives Aerodynamic Performance Aircraft Configurations Thickness to Chord Ratio Structural Weight Aspect Ratio

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Allocation and Design of Aircraft for On-Demand Air Transportation with Uncertain Operations

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JOURNAL OF AIRCRAFT 2012年第1期49卷 141-150页

作者： Mane, Muharrem Crossley, William A. Purdue Univ Sch Aeronaut & Astronaut W Lafayette IN 47907 USA

Aircraft manufacturers design aircraft to optimize an identified aircraft-specific performance metric (e.g., takeoff gross weight, acquisition cost, and operating cost) based on design requirements derived from market research and the perceived needs of aircraft operators. This is a loose coupling between the aircraft design problem of the aircraft manufacturer and the assignment or allocation problem of the aircraft operator. Providing a tighter coupling between aircraft operations and aircraft design can concurrently identify the best new aircraft design and the best operational concept using this new aircraft. This paper presents an approach to couple the uncertain aircraft assignment problem of fractional operations and the aircraft design problem of aircraft manufacturers. A solution to this type of problem describes an aircraft design that directly improves operations and identifies operating strategies that influence, and take advantage of, the characteristics of the new aircraft. With this formulation, an aircraft manufacturer could work more closely with a customer to determine the best new aircraft for the operations.

关键词： Transport Aircraft Air Transportation Aircraft Design Process Acquisition Costs Aircraft Operations flight optimization system Business Jet Copilot Aircraft Sizing Aspect Ratio

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Set-Based Approach to Passenger Aircraft Family Design

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JOURNAL OF AIRCRAFT 2017年第1期54卷 310-326页

作者： Riaz, Atif Guenov, Marin D. Molina-Cristobal, Arturo Cranfield Univ Ctr Aeronaut Cranfield MK43 0AL Beds England

Presented is a method for the design of passenger aircraft families. Existing point-based methods found in the literature employ sequential approaches in which a single design solution is selected early and is then iteratively modified until all requirements are satisfied. The challenge with such approaches is that the design is driven toward a solution that, although promising to the optimizer, may be infeasible due to factors not considered by the models. The proposed method generates multiple solutions at the outset. Then, the infeasible solutions are discarded gradually through constraint satisfaction and set intersection. The method has been evaluated through a notional example of a three-member aircraft family design. The conclusion is that point-based design is still seen as preferable for incremental (conventional) designs based on a wealth of validated empirical methods, whereas the proposed approach, although resource-intensive, is seen as more suited to innovative designs.

关键词： Transport Aircraft Aircraft Configurations ECS Maximum Takeoff Weight Airbus flight Control system Thickness to Chord Ratio Power system Heat Pipes flight optimization system

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Optimal Paths for Progressive Aircraft Subsystem Electrification in Early Design

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JOURNAL OF AIRCRAFT 2022年第1期59卷 219-232页

作者： Bendarkar, Mayank V. Rajaram, Dushhyanth Cai, Yu Mavris, Dimitri N. Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Aerosp Syst Design Lab Atlanta GA 30332 USA

The push for more-electric aircraft (MEA) has motivated numerous studies to quantify and optimize the impact of subsystem electrification in early design phases. Past studies on multi-objective optimization of MEA show a clear benefit over conventional architectures when no constraints are placed on the number of subsystems electrified at once. In reality, aircraft manufacturers are more likely to progressively electrify subsystems over multiple aircraft generations. While step-by-step electrification may lead to suboptimal MEA architectures when compared with scenarios with no such imposition on the number of subsystems electrified, little or no literature was found to address the optimal paths toward such electrification changes. This study proposes a mathematically defensible method to analyze different directions of technology evolution focusing on aircraft subsystem electrification. It seeks to enable decision makers to understand the performance tradeoffs between different electrification paths under different scenarios, constraints, and uncertainties. Certain trends in Pareto-optimal MEA architectures and progressive subsystem electrification order (optimal paths) under uncertainty are discussed.

关键词： Commercial Aircraft Hybrid Electric Aircraft Maximum Takeoff Weight ECS Thrust to Weight Ratio Aircraft Configurations Aircraft Design Process Pareto Frontier Energy Density flight optimization system

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An Approach to Evaluating the Impact of Small-core Turbofan Technologies on Engine and Aircraft Performance

An Approach to Evaluating the Impact of Small-core Turbofan ...

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AIAA SciTech Forum

作者： Bennett, Michael A. Chapman, Jeffryes W. Wells, Douglas P. NASA Glenn Res Ctr Prop Syst Anal Branch 21000 Brookpk Rd Cleveland OH 44135 USA NASA Langley Res Ctr Aeronaut Syst Anal Branch Mail Stop 442 Hampton VA 23681 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

NASA's Hybrid Thermally Efficient Core (HyTEC) project aims to accelerate the development of small-core turbofan engine technologies to enable a fuel burn reduction of 5 to 10 percent for next-generation aircraft, compared to 2020s best-in-class technology. This paper presents a demonstration of methods for evaluating the potential performance impact of small-core engine technologies developed under Phase 1 of the HyTEC project. The approach involves model-based systems analysis, where small-core innovations are integrated into baseline turbofan and aircraft systems models, creating a notional vision system. Performance of the vision system is examined at both the engine and vehicle level. The examined performance metrics include: engine bypass ratio, overall pressure ratio, high pressure compressor exit corrected mass flow, and aircraft fuel burn. The CFM LEAP-1B28 and Boeing 737 MAX 8 are chosen as the baseline state-of-the-art systems. Preliminary results map a design space for the small-core vision system and quantify the distinct effects of technologies on the key metrics.

关键词： Turbofan Engines Aircraft Performance Mass Flow Overall Pressure Ratio Commercial Aircraft Turbine Inlet Temperature Numerical Propulsion system Simulation Aerodynamic Design flight optimization system Turbomachinery

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Validation and Calibration of Conceptual Design Tool SUAVE

Validation and Calibration of Conceptual Design Tool SUAVE

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AIAA Aviation Forum

作者： Gallagher, Conor Stuart, Charles Spence, Stephen Fowler, Thomas Univ Dublin Trinity Coll Dublin Dept Mech Mfg & Biomed Engn Dublin Ireland Ryanair Sustainabil & Finance Swords Ireland

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The aim of this study is to provide a comprehensive validation of the conceptual design tool SUAVE, with respect to real world flight data from an extensive flight database of 737-800NG fleet operations. A validation of the initial SUAVE model fuel burn predictions was performed and compared with the actual data. A surrogate propulsion model was developed using NPSS and integrated into SUAVE, which significantly enhanced the model accuracy. A calibration of the SUAVE aerodynamic model coefficients, the propulsion model idle throttle value, and the take-off and landing drag increments was performed which aimed to minimise the fleet-wide fuel burn error with respect to the actual flight data within the database. The model was calibrated using 26 case flights in a training database, and the final calibrated model performance was measured against three unseen test cases within the flight database. A modest reduction in error was observed for the training and test cases, however non-linear error effects in the presence of headwinds and tailwinds affected the model accuracy and limited the potential of the calibration. Despite these effects, a highly accurate model was developed with an average fuel-flow error of 5% with respect to real-world flight data, providing an accurate baseline model from which confident projections of future carbon reductions can be obtained for new aircraft designs.

关键词： flight optimization system Aerodynamic Coefficients Aircraft Design Take off and Landing Aircraft Configurations Rate of Climb Automatic Dependent Surveillance Broadcast Thrust Specific Fuel Consumption Turbofan Fuel Consumption

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