检索结果-内蒙古大学图书馆

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

来源：评论

学校读者我要写书评

暂无评论

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

引用

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

来源：评论

学校读者我要写书评

暂无评论

Benefits and Challenges of Electric Propulsion for Commuter Aircraft

引用

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

来源：评论

学校读者我要写书评

暂无评论

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

引用

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

来源：评论

学校读者我要写书评

暂无评论

Automatic Continuous Thrust Control for Supersonic Transport Takeoff Noise Reduction

引用

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

来源：评论

学校读者我要写书评

暂无评论

High-Dimensional Bayesian optimization Using Both Random and Supervised Embeddings

引用

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

来源：评论

学校读者我要写书评

暂无评论

Enforcing Work Conservation in Modular Aeroelastic Coupling For multidisciplinary design optimization

Enforcing Work Conservation in Modular Aeroelastic Coupling ...

引用

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

来源：评论

学校读者我要写书评

暂无评论

multidisciplinary Spacecraft and Trajectory Uncertainty Quantification for an Interplanetary Mission

Multidisciplinary Spacecraft and Trajectory Uncertainty Quan...

引用

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

来源：评论

学校读者我要写书评

暂无评论

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...

引用

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

来源：评论

学校读者我要写书评

暂无评论

Conceptual design of the Hybrid-Electric Subsonic Single Aft Engine (SUSAN) Electrofan Transport Aircraft

Conceptual Design of the Hybrid-Electric Subsonic Single Aft...

引用

AIAA SciTech Forum

作者： Chau, Timothy Duensing, Jared C. Sci & Technol Corp Computat Aerosci Branch Bldg N258 Moffett Field CA 94035 USA NASA Computat Aerosci Branch Ames Res Ctr Bldg N258 Moffett Field CA 94035 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents an update to the conceptual design of the NASA Subsonic Single Aft Engine (SUSAN) Electrofan transport aircraft-a 180 passenger, Mach 0.785 hybrid-electric regional jet with an economy range of 750 nmi and a design range of 2,500 nmi. The concept employs a series/parallel partial hybrid-electric powertrain driven by a fuel-burning aft fuselage propulsor connected to Megawatt-class power generators, which support wing-mounted electric propulsors. The aft fuselage turbofan leverages boundary layer ingestion (BLI) and is designed to deliver 35% of the total aircraft thrust, while the wing propulsors assume underwing distributed electric propulsion (DEP) configurations and are responsible for the remaining 65% aircraft thrust. Investigated in this work is the system level sizing and analysis of the SUSAN Electrofan when accounting for system level trades related to its electrified aircraft propulsion (EAP) systems. Updated disciplinary models and key performance parameters are incorporated, including those related to the power, battery, and thermal systems. A unified propulsion system model is also included, which accounts for the high effective bypass ratio made possible by DEP, and turbofan BLI effects to first order. Conceptual multidisciplinary design analysis and optimization (MDAO) is used to determine the EAP system technology levels required to close the SUSAN Electrofan concept based on the current set of design requirements and assumptions. Comparisons of fuel burn performance to a reference aircraft based on the Boeing 737 MAX 8 are presented, as well as comparisons to a variant resized for the same range capabilities as the SUSAN Electrofan.

关键词： Transport Aircraft Thrust Specific Fuel Consumption Distributed Electric Propulsion Landing Gear Turbofan Engines Numerical Propulsion System Simulation Boundary Layer Ingestion multidisciplinary design analysis and optimization NASA Hybrid Electric Powertrain

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：