COMPARATIVE STRUCTURAL OPTIMIZATION STUDY OF COMPOSITE AND ALUMINUM HORIZONTAL TAIL PLANE OF A HELICOPTER

2019-11-11
Arpacıoğlu, Bertan
Kayran, Altan
This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS and the finite element model of the horizontal tail plane is created by using MSC.PATRAN. According to the characteristics of materials, design variables are chosen. For the aluminum horizontal tail, thickness and flange areas are used as the design variables; and for composite horizontal tail, attention is mainly focused on the ply numbers and ply orientation angles of the laminated composite panels. By considering the manufacturability issues, discrete design variables are used. For three different mesh densities, different initial values of the design variables, and similar design constraints, optimizations are repeated and the results of optimizations are examined and compared with each other. In the optimizations performed, constraints are taken as strength and local buckling constraints. It is shown that the optimization methodology used in this study gives confident results for optimizing structures in the preliminary design phase.

Suggestions

Structural optimization of composite and aluminum horizontal tail plane of a helicopter
Arpacıoğlu, Bertan; Kayran, Altan; Department of Aerospace Engineering (2019)
This thesis presents structural optimization studies of aluminum and composite material horizontal tail plane structure of a helicopter by using MSC.NASTRAN optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS ...
Manufacturing and structural analysis of a lightweight sandwich composite UAV wing
Turgut, Tahir; Kayran, Altan; Department of Aerospace Engineering (2007)
This thesis work deals with manufacturing a lightweight composite unmanned aerial vehicle (UAV) wing, material characterization of the composites used in the UAV wing, and preliminary structural analysis of the UAV wing. Manufacturing is performed at the composite laboratory founded in the Department of Aerospace Engineering, and with hand lay-up and vacuum bagging method at room temperature the wing is produced. This study encloses the detailed manufacturing process of the UAV wing from the mold manufactur...
Trajectory computation of small solid particles released and carried by flowfields of helicopters in forward flight
Pekel, Yusuf Okan; Özyörük, Yusuf; Department of Aerospace Engineering (2010)
In this thesis, trajectory computations of chaff particles ejected from a medium weight utility helicopter are performed using computational fluid dynamics. Since these chaff particles are ejected from a helicopter and carried by its flow field, it is necessary to compute and include the effects of the helicopter flow field in general and engine hot gases, main and tail rotor wakes in particular. The commercial code FLUENT is used for flow field and trajectory computations. Both main rotor and tail rotor ar...
Mechanical characterization of additively manufactured Ti-6Al-4V aircraft structural components produced by electron beam melting
Yılmaz, Fatih; Şahin, Melin; Gürses, Ercan; Department of Aerospace Engineering (2022-8-25)
Weight reduction of structural parts is one of the most important efforts of design and analysis studies to improve fuel efficiency and flight performance of aerospace vehicles through topology optimization creating complex geometric designs that are lighter but cannot be produced via conventional manufacturing methods. Instead, the manufacturing of the resulting designs is possible with additive manufacturing methods where the final product is obtained by adding layer upon layer to obtain close to the near...
Aerodynamic optimization of horizontal axis wind turbine blades by using CST method, BEM theory and genetic algorithm
Oğuz, Keriman; Sezer Uzol, Nilay; Department of Aerospace Engineering (2019)
In this thesis, an aerodynamic design and optimization study for rotor airfoils and blades of Horizontal Axis Wind Turbines (HAWTs) is performed by using different airfoil representations and genetic algorithm. Two airfoil representations, the Class-Shape Transformation (CST) method and the Parametric Section (PARSEC) method, are used for the airfoil geometry designs. Their aerodynamic data is obtained by a potential flow solver software, XFOIL. The Blade Element Momentum (BEM) theory is used to calculate t...
Citation Formats
B. Arpacıoğlu and A. Kayran, “COMPARATIVE STRUCTURAL OPTIMIZATION STUDY OF COMPOSITE AND ALUMINUM HORIZONTAL TAIL PLANE OF A HELICOPTER,” 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/56385.