Design Developments for Advanced General Aviation Aircraft

Roskam, J.; Gomer, Charles

doi:10.4271/911022

Cited by 2 publications

(2 citation statements)

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“…In the first iteration of the sizing process, since the aircraft layout is not defined yet, and no aerodynamic information is available, a guess of the required thrust and wing area is made, which is simply a constant value of T/W and W/s obtained from similar aircraft. In subsequent iterations, the classical formulation of the matching diagram presented by Roskam [11] is used. The user can select which of these requirements should be considered in the sizing process and can adjust the requirements' values and settings.…”

Section: Sizingmentioning

confidence: 99%

“…On the other hand, aircraft design is an iterative process by nature, and the design loop should be repeated until the design converges. Applying the traditional design methods manually, such as Roskam [11], Torenbeek [12], and Raymer [13], would be time-consuming and computationally inefficient. This issue intensifies when the problem includes optimization, which may require the examination of thousands of design sets.…”

Section: Introductionmentioning

confidence: 99%

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A Framework for Aircraft Conceptual Design and Multidisciplinary Optimization

Hosseini,

Vaziry-Zanjany,

Ovesy

2024

Aerospace

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In this research, the architecture and the functionalities of the LAMBDA (Laboratory of Aircraft Multidisciplinary Knowledge-Based Design and Analysis) framework for the design, analysis, and optimization of civil aircraft are presented. The framework is developed in MATLAB R2022a and comprises a modular architecture, which gives the potential for the use of different methods and fidelities for each discipline. The methods can be selected from a set of built-in methods or custom user-defined scripts. Disciplinary modules of the LAMBDA (Laboratory of Aircraft Multidisciplinary Knowledge-Based Design and Analysis) are Requirements, Weight, Sizing, Geometry, Aerodynamics, Engine, Performance, Cost, Emission, and Optimization. This framework has been used for different types of design and optimization problems. When it is applied for the design and optimization of a novel regional TBW (Truss-Braced Wing) aircraft, the operating cost has been reduced by 7.7% in the optimum configuration compared to the base configuration.

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Section: Sizingmentioning

confidence: 99%