Aircraft Design Optimization for Commercial Air Travel Under Multi-Domain Uncertainties

Abstract Key issues relating to the Supersonic Business Jet (SBJ) concept are reviewed with the intent to assess the readiness of enabling technologies and hence the concept itself. The multidisciplinary nature of aircraft design precludes an in-depth analysis of each specific aspect, which could individually be the subject of a separate discipline review, hence an overview is presented. The review looks at the market, environmental issues, with particular reference to the sonic boom phenomenon & solutions, technological issues, including prediction methods, flight testing, systems, certification and interested aerospace companies and design organisations. It is apparent that the need to reduce the sonic boom signature is vital if the vehicle is to be permitted to operate over land and hence be economically viable. It is clear that sonic boom acceptability requirements must be set if resources are to be effectively focused and designs are to converge. Despite this challenge, considerable investment is aimed at de-risking many of the enabling technologies and raising readiness levels. Many technologies are moving beyond theoretical and numerical analysis into the experimental and flight test domains. Collaboration between the civil and military sectors is increasing. Clearly, supersonic air travel is not an efficient means of personal conveyance; however, concerns for the environment are difficult to balance against the ‘value of time’ benefits offered by the SBJ concept. Air travel, of which this is a specialised form, is important to the global economy. Continued effort in the areas of human factors, customer demand and certification & requirements would be beneficial.

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Design of an Aircraft Brake Component Using an Interactive Multidisciplinary Design Optimization Framework

Journal of Mechanical Design ◽

10.1115/1.533554 ◽

2000 ◽

Vol 122 (1) ◽

pp. 70-76 ◽

Cited By ~ 7

Author(s):

Marc A. Stelmack ◽

Stephen M. Batill ◽

Bryan C. Beck

Keyword(s):

Design Optimization ◽

Multidisciplinary Design Optimization ◽

Aircraft Design ◽

Multidisciplinary Design ◽

Analysis Software ◽

Commercial Aircraft ◽

Design Improvement ◽

Optimization Framework ◽

Design Engineers ◽

Performance Requirements

A multidisciplinary design optimization (MDO) framework has been used to design an aircraft brake assembly. This was done using a user-interactive implementation of the framework in which design information was obtained from analysis software used in industry but not developed for an MDO application. The design included a number of performance requirements associated with a brake that has been produced for a commercial aircraft. Design improvement was achieved using a practical number of system realizations and the interaction between the optimization algorithm and the design engineers was maintained throughout the process. [S1050-0472(00)00201-4]

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Preliminary Sub-Systems Design Integrated in a Multidisciplinary Design Optimization Framework

Transactions on Aerospace Research ◽

10.2478/tar-2017-0025 ◽

2017 ◽

Vol 2017 (4) ◽

pp. 9-23

Author(s):

Marco Fioriti ◽

Luca Boggero ◽

Sabrina Corpino

Keyword(s):

Design Optimization ◽

Multidisciplinary Design Optimization ◽

Systems Design ◽

Aircraft Design ◽

Multidisciplinary Design ◽

Design Parameters ◽

Preliminary Design ◽

Horizon 2020 ◽

Optimization Framework ◽

Complex Subject

Abstract The aircraft design is a complex subject since several and completely different design disciplines are involved in the project. Many efforts are made to harmonize and optimize the design trying to combine all disciplines together at the same level of detail. Within the ongoing AGILE (Horizon 2020) research, an aircraft MDO (Multidisciplinary Design Optimization) process is setting up connecting several design tools and competences together. Each tool covers a different design discipline such as aerodynamics, structure, propulsion and systems. This paper focuses on the integration of the sub-system design discipline with the others in order to obtain a complete and optimized aircraft preliminary design. All design parameters used to integrate the sub-system branch with the others are discussed as for their redefinition within the different detail level of the design.

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Integrated uncertainty techniques in aircraft derivative design optimization.

10.32920/ryerson.14645310.v1 ◽

2021 ◽

Author(s):

Hyeong-Uk Park

Keyword(s):

Sensitivity Analysis ◽

Design Optimization ◽

Design Process ◽

Aircraft Design ◽

Collaborative Optimization ◽

Aircraft Manufacturing ◽

Analysis Tools ◽

Design Variables ◽

The Cost ◽

Aircraft Conceptual Design

Aircraft manufacturing companies have to consider multiple derivatives to satisfy various market requirements. They modify or extend an existing aircraft to meet the new market demands while keeping the development time and the cost to a minimum. Many researchers have studied the derivative design process, but these research considered the baseline and the derivatives together, while using the whole set of design variables. Therefore, an efficient process that can reduce the cost and the time for the aircraft derivative design is needed. In this dissertation, Aircraft Derivative Design Optimization process (ADDOPT) was developed which obtains the global changes from the local changes in the aircraft design to develop the aircraft derivatives efficiently. The sensitivity analysis was implemented to ignore design variables that have low impact on the objective function. This avoids wasting computational effort and time on low priority variables for design requirements and objectives. Additionally, the classification of uncertainty from its characteristics and sources of uncertainty involved in the aircraft design process were suggested to consider with design optimization. Uncertainty from the fidelity of analysis tools was applied in design optimization to increase the probability of optimization results. To handle uncertainty in low fidelity analysis tools on aircraft conceptual design optimization, Reliability Based Design Optimization (RBDO) and Possibility Based Design Optimization (PBDO) methods were performed. In this research, Extended Fourier Amplitude Sensitivity Test (eFAST) method was implemented in ADDOPT for Global Sensitivity Analysis (GSA) method and Collaborative Optimization (CO) based framework with RBDO and PBDO were also used. These methods were evaluated using numerical examples. ADDOPT was carried through on the civil jet aircraft derivative design. The objective of the optimization problem was to increase cruise range while satisfying the requirement such as the number of passengers. The proposed process reduced computation effort by reducing the number of design variables and achieved the target probability of failure when considering uncertainty from low fidelity analysis tools.

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