Parametric and topology optimization of polymer composite load bearing elements of rear part of aircraft fuselage structure

Htet, Tun Lin; Prosuntsov, P. V.

doi:10.1063/5.0035742

XLIV ACADEMIC SPACE CONFERENCE: Dedicated to the Memory of Academician S.P. Korolev and Other Outstanding Russian Scientists – 2021

DOI: 10.1063/5.0035742

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Parametric and topology optimization of polymer composite load bearing elements of rear part of aircraft fuselage structure

Tun Lin Htet¹,

P. V. Prosuntsov²

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2024

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Cited by 5 publications

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Design of a structurally optimized bioinspired structural arrangement of carbon composite fuselage of unmanned aerial vehicle based on parametric modeling

Baranovski,

Zaw

2023

E3S Web of Conf.

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Currently, the industry of unmanned aerial vehicles (UAV) is actively developing. They perform a wide range of different civilian and military tasks. Depending on the task, stringent requirements are imposed on the design, but the key ones are low weight, high strength and survivability. Satisfying these requirements will increase the payload mass and extend the life of the product. This can be ensured by the use of polymer composite materials (PCM) based on carbon fibers and new structural arrangement. This is especially true for the main element of the UAV frame –the fuselage. The work is devoted to an urgent task –the development of a new UAV composite structural layout. Structural-optimized structures are considered: bioinspired, auxetic, grid structures. A comparison of the developed options with the classical structure of the frame is carried out. A variant that exceeds the classical layout in terms of mass and strength up to 25% is selected. Main layout parameters are determined.

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Design of a structurally optimized bioinspired structural arrangement of carbon composite fuselage of unmanned aerial vehicle based on parametric modeling

Baranovski,

Zaw

2023

E3S Web of Conf.

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Numerical two-dimensional optimization of a cylindrical fuselage for bioinspired unmanned aerial vehicle based on non-dominated sorting genetic algorithm-II

Dewangan,

Roy

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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To achieve an aerodynamically efficient design of fuselage for bioinspired unmanned aerial vehicles (UAV), the development of a systematic method is of paramount need. This work presents a multiobjective optimization study for shape parameterization of a 2D fuselage of foldable flapping wing UAV in low Reynolds number (2e05) flight conditions. The novelty of the research work lies in integrating S1223 airfoil characteristics for predicting the efficient shape design of the fuselage. This paper offers four sections; (i) the validation of the ANSYS Fluent model with experiment, (ii) the exploration of design variables using Design of Experiment (Sparse Grid Initialization), (iii) the implementation of response surface method (Genetic Aggregation) to know about dimensional sensitivity among independent and dependent variables and (iv) the application of multiobjective optimization method i.e. NSGA II to optimize the drag and lift coefficient. To identify the superiority, a comparative study between the original and optimized fuselage is presented considering many parameters like pressure contours, velocity contours, pressure coefficients, and streamlines representations. It is evident from various results that the 2D optimum shape significantly minimizes the drag coefficient and increases the lift coefficient. This work also makes room for 3D shape optimization, which helps in prototype fabrication for real-time flight conditions.

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Design Optimization of Shape and Layup Sequence of Polymer Composite Load Bearing Elements of Light Aircraft

Tun

Prosuntsov

2021

PoHEI.MB

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The paper presents the methodology for designing the load bearing elements of tail section of a light aircraft through the sequential application of methods of parametric and topological optimization. First, we analyzed the loads acting on the aircraft at its maneuvering in the vertical and horizontal planes. Then, for these loads, by the parametric optimization method, we selected the locations of ribs of the tail section of the aircraft, which were subsequently used to develop individual forms of ribs based on the topology optimization method. Next, we carried out parametric optimization of layup angles of polymer composite material, intended for the production of ribs. Finally, we developed a structural layout for the load bearing elements of the fuselage, which meets the criteria of minimum weight when restrictions are imposed on the level of stresses in some layers of the composite material.

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Parametric and topology optimization of polymer composite load bearing elements of rear part of aircraft fuselage structure

Cited by 5 publications

References 8 publications

Design of a structurally optimized bioinspired structural arrangement of carbon composite fuselage of unmanned aerial vehicle based on parametric modeling

Design of a structurally optimized bioinspired structural arrangement of carbon composite fuselage of unmanned aerial vehicle based on parametric modeling

Numerical two-dimensional optimization of a cylindrical fuselage for bioinspired unmanned aerial vehicle based on non-dominated sorting genetic algorithm-II

Design Optimization of Shape and Layup Sequence of Polymer Composite Load Bearing Elements of Light Aircraft

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