Multi-mission Multi-objective Optimization in Commercial Aircraft Conceptual Design

Cai, Yu; Rajaram, Dushhyanth; Mavris, Dimitri N.

doi:10.2514/6.2019-3577

Cited by 14 publications

(6 citation statements)

References 11 publications

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“…C Battery,FC = f Battery,FH (t mission )⋅t mission (18) Where f Battery,FH is the battery maintenance cost per flight hour which is considered as US$ 205 with the assumption of the battery capital cost as 100 $/kWh [25].…”

Section: Economic Analysismentioning

confidence: 99%

“…In order to improve the specified design missions, a multi-mission multi-objective optimization method for commercial aircraft conceptual design was proposed using NSGA II in Ref. [18]. This optimization method compared the difference between exclusively considering metrics of interest from one design mission and that of multiple missions, and further investigated the impact of weightings on optimization results.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Zhang¹,

Roumeliotis²,

Zhang³

et al. 2023

Renewable and Sustainable Energy Reviews

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Section: Economic Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Zhang¹,

Roumeliotis²,

Zhang³

et al. 2023

Renewable and Sustainable Energy Reviews

View full text Add to dashboard Cite

“…Both ECS sized by SDP and MDP sizing method obtain the design variables from the optimization process described in Sec. V. The aircraft selected to perform such analyses is a Large Twin-aisle Aircraft (LTA), whose specification can be found in the authors' previous work [29], with some design information relevant to this work summarized in Table 6.…”

Section: Mdp Sizing Methodology Validation Approachmentioning

confidence: 99%

“…To ensure the vehicle point performance is invariant and its design mission requirements are met, the vehicle is resized for the design mission, maintaining the original design thrust-to-weight ratio and wing loading with the updated ECS pack mass and ram drag. The vehicle sizing and off-design mission performance evaluation is conducted using the Aircraft Sizing and Off-Design Mission Analysis Tool [29], which uses empirical component weight and drag build-up method from NASA's Flight Optimization System (FLOPS) software [30] to compute the basic vehicle empty weight and drag polar. SODA provides an interface to specify the mass of ECS packs and drag increment due to ram air intake as a function of altitude and Mach number.…”

Section: Mission-level Performance Assessmentmentioning

confidence: 99%

A Multi-Design Point Sizing Methodology for Environmental Control Systems

Shi

Cai

Gladin

et al. 2020

AIAA Scitech 2020 Forum

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The environmental control system, which is to provide cabin air supply, conditioning, and pressurization, is the largest consumer of the secondary power in the aircraft. The impacts of the environmental control system designs have been studied for a long time. However, there is not a clear design guideline for it. Many studies have designed or optimized the environmental control system for a single point which was important in terms of vehicle or mission fuel economy. Some other researchers chose the most critical condition for sizing, such as the hot day and ground condition, or hot day with one engine failed. Some research also pointed out that the cooling efficiency can be greatly influenced when operation point is far from its design point. Therefore, a design guideline of the environmental control system is needed. To fill this gap, this paper proposes a multi-design point sizing methodology which sizes the environmental control system based on performance requirements of multiple points instead of those for a single point. This methodology will guarantee that all the requirements through the mission will be satisfied, and the efficiency will not be influenced much when the operation condition moves.

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“…Depending on type of analysis, mission range may be input to solve for ramp weight, or vice versa. The Aircraft Sizing and Off-Design Mission Analysis Tool [29] is selected for mission analysis. In this framework, the mission analysis is performed twice:…”

Section: Fig 8 Generic Mission Profile For Commercial Aircraftmentioning

confidence: 99%

A Certification-Driven Platform for Multidisciplinary Design Space Exploration in Airframe Early Preliminary Design

Sarojini

Xie

Cai

et al. 2020

Aiaa Aviation 2020 Forum

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Following the conceptual phase of aircraft design, sizing and performance estimations shift from historical-based empirical equations to physics-based simulations. The initial aircraft configuration is refined with a larger number of objectives and requirements, and certification regulations play a critical role in defining these. Analysis tools in the early phases of preliminary design have an important trade-off between accuracy, complexity, and computational efficiency. A number of analysis frameworks currently exist with varying levels of fidelity, multidisciplinary coupling, and limitations in the number of disciplines, degrees of freedom, and requirements they are able to implement. To enable efficient design space exploration (DSE), this paper proposes an integrated preliminary design framework that couples aerodynamics, structures, subsystems, aircraft performance, flight dynamics, and certification testing at varying levels of fidelity. This framework serves as a numerical testbed that can be used to explore the aircraft configuration and disciplinary design spaces, strength of disciplinary couplings, and propagate disciplinary uncertainties across the entire aircraft system. The framework is demonstrated using the horizontal tail of a large twin-aisle aircraft as a test case.

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Multi-mission Multi-objective Optimization in Commercial Aircraft Conceptual Design

Cited by 14 publications

References 11 publications

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

Techno-economic-environmental evaluation of aircraft propulsion electrification: Surrogate-based multi-mission optimal design approach

A Multi-Design Point Sizing Methodology for Environmental Control Systems

A Certification-Driven Platform for Multidisciplinary Design Space Exploration in Airframe Early Preliminary Design

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