Optimization of Light Weight Aircraft Wing Structure (original) (raw)

Aerodynamic design and structural optimization of a wing for an Unmanned Aerial Vehicle (UAV)

IOP Conference Series: Materials Science and Engineering, 2020

This paper summarizes the process of structural design, analyses and optimization for weight reduction of a UAV wing. A semi-monocoque wing structure that consists of ribs, spars and skin are efficiently optimized for Weight minimization without reducing the Strength to weight ratio. Initially a solid wing surface is designed with the air foil co-ordinates of NACA 2412. The CFD Analysis is carried out to get pressure distribution on various arrangements of wing by changing angles of attack. From the CFD results the variation of coefficient of lift for different angle of attack is determined. The pressure fields obtained from CFD analysis is imposed on structural members for structural analysis. Optimization of this wing is done considering various cases until the required performance is obtained. The results are obtained for the optimized wing and this helps in obtaining reduced weight of the wing and increased strength to weight ratio. Results show that substantial improvement has ...

The optimal design of UAV wing structure

AIP Conference Proceedings, 2018

The paper presents an optimal design of UAV wing, made of composite materials. The aim of the optimization is to improve strength and stiffness together with reduction of the weight of the structure. Three different types of functionals, which depend on stress, stiffness and the total mass are defined. The paper presents an application of the inhouse implementation of the evolutionary multi-objective algorithm in optimization of the UAV wing structure. Values of the functionals are calculated on the basis of results obtained from numerical simulations. Numerical FEM model, consisting of different composite materials is created. Adequacy of the numerical model is verified by results obtained from the experiment, performed on a tensile testing machine. Examples of multi-objective optimization by means of Pareto-optimal set of solutions are presented.

Airfoil Analysis and Effect of Wing Shape Optimization on Aerodynamic Parameters in a Steady Flight

Global Journal of Researches in Engineering, 2021

The work in this paper deals with reconstructing and optimizing the wing geometry of an Unmanned Combat Aerial Vehicle for improved performance and reviewing the impact of the modification on flight parameters in a steady flight. The behavior of airfoils at planned flight conditions under I.S.A. is checked in XFLR5 software. Following up by 2-D CFD and boundary layer analysis of former and new airfoil, dimensions of the wing are re-developed, keeping the fuselage and tail structure same. The existing wing and the optimized wing design is analyzed by Vortex Lattice Method and Triangular Panel Method, with an objective to make the shape of the wing aerodynamically suitable for an increased Lift to Drag ratio and thereby minimizing drag coefficients.

Optimal design and cfd analysis of wing of a smallscale uav to obtainmaximum efficiency

In the recent past small-scale Unmanned Aerial Vehicles (or Unmanned Aerial System as it is called presently) have evolved as an important tool in non-conventional fields like agriculture, e-Commerce, policing, medical logistics in addition to military applications. This paper presents the complete methodology (very limited article exists) applied to optimally design the wing of a small scale Unmanned Aerial Vehicle with help of widely used CFD software, ANSYS to maximize its efficiency. In this study, the application of computational methods in the iterative design process is successfully explored. The various design parameters and features of wing also have been explored with help of CFD analysis to derive the advantages. The strength and stiffness analysis of the UAV wing has also been carried out using ANSYS. The modelling of wing and associated parts were carried out on CATIA. The final design of the wing has two spars, 20 ribs a side with mid wing root strengthening, near elliptical planform and has an all composite structure. The wing is lighter in weight as compared to a similar wing made from Aluminum view weight optimization, and strong enough to meet all in-flight load conditions with safety margins. This paper demonstrates the design process/methodology to optimally design an efficient small-scale UAV.

A Mathematical Formulation and Solution of the Optimized Wing Aero-structural Problem

In this research the design of a class of aircraft wing with a constant taper angle is formulated as a constrained optimization problem. The design variables for the optimization problem are the placements of the internal components and geometric dimensions of the wing. The cost function is the weight of the wing consisting of the weights of the front spar, the rear spar and the reinforced skin. The design constraints imposed on the optimization process are the bending stresses in the spars, the shear stresses and the angle of twist in the ribs. All the design calculations are non-dimensionalized with a corresponding calculation of a rectangular planform wing, which is a member of the class of wings studied. The optimization of the dimensionless weight of the wing, defined in terms of ten design variables, is implemented using Nelder and Mead technique. Simplified versions of the optimization problem for 1D and 2D cases are presented to serve as the basis for the validation of the s...

Evaluation of Novel Wing Design for UAV

Viable design alternative for the existing and fast growing UAVs, which are optimized for unmanned flight, is of great demand. Designing of a small scale UAV alternative to the AAI Aerosonde UAV has been considered changing the wing tail configuration of the vehicle analyzing both structural and aerodynamic performance improvements using COMSOL Multiphysics. Various Non-Planar design alternatives have been considered and box wing configuration has been proven to be the best suited for the application. Variations in the design with box wing configuration have been analyzed by using Tornado scrip in Matlab and the important configurations have been analyzed using the CFD module for aerodynamics and Multiphysics for structural performance. The NACA 0012, Ahmed body models have been very much helpful in learning COMSOL and applying it to the present situation for reducing the solving time and increasing the accuracy of solving the problem

Unmanned Air Vehicle (UAV) Wing Design and Manufacture

This paper documents the development of a UAV wing, encompassing the entire process from design to manufacture, and finally its implementation on an aircraft. Beginning with wing design and analysis, requirements are first identified and related concepts are formulated. A literature survey is then conducted to establish focus for analysis.

Design, Structural Optimization and Loads Assessment for a Flying Wing

2018

This paper presents a summary of the evolution of aeroelastic models for flying wing configurations. Two different flying wing configurations have been studied and synergies with other DLR projects have been used to validate important parts of the loads process. A newly developed in-house software for aircraft loads extends the aeroelastic design process in combination with a parametric model generation software and a structural optimization sequence. During the progress from the DLR-F19-S towards the MULDICON, the numerical methods evolved as well, mainly aiming for higher fidelity to ensure a thorough and sophisticated design. Design and loads related studies were performed with national and international partners from industry and academia. This paper gives an overview on aspect and modeling strategies that distinguish flying wings from classical wing-fuselage-empennage configurations. Finally, an outlook is given on the next steps and on ongoing work.

AERO-STRUCTURAL OPTIMIZATION OF AIRCRAFT WING BY FINITE ELEMENT METHOD

New and innovative designs must be explored to meet the aircraft requirements lower weight and more cost effective structure for future airplanes. For these reasons, present study aims to deals with the structural analysis for predicting the structural behavior of aircraft wing with ribs and stringers. With an helpful of aerodynamic principles, aircraft wing with ribs and stringers were analyzed by considering two criteria, one is varying load conditions and the other method is varying structural materials. For structural and aero–elastic response analysis, finite element method is used in ANSYS software with efficient computation. Wing behavior of total deformation (δ) , equivalent (von Mises) stress (σ v) , equivalent elastic strain (ε), ultimate tensile stress (UTS) and wing twist to be simulated. From the computational results, better performance aircraft structure material, in terms of light weight, low fuel consumption and cost-benefit to save economy is identified.