scholarly journals Morphing Winglet Design for Aerodynamic Performance Optimization of the CRJ-700 Aircraft. Part 1 – Structural Design

2021 ◽  
Vol 13 (4) ◽  
pp. 113-128
Author(s):  
Paul MEYRAN ◽  
Hugo PAIN ◽  
Ruxandra Mihaela BOTEZ ◽  
Jeremy LALIBERTÉ
Keyword(s):  
Performance Optimization ◽  
Structural Design ◽  
Structural Model ◽  
Aerodynamic Performance ◽  
Structural Components ◽  
Transport Aircraft ◽  
Aerodynamic Loads ◽  
Load Factors ◽  
Morphing Technology ◽  
Maximum Stresses

This study aims to design a morphing winglet structure for the CRJ-700 regional transport aircraft. The morphing technology is applied on winglets to demonstrate a significant increase of the aerodynamic performance of aircraft. From the aerodynamic data of the LARCASE Virtual Research Simulator VRESIM, the aerodynamic benefits in the cruising phase were obtained through a study on the ParaView software. The morphing winglet design was drawn using CATIA V5; this new concept included several structural components, as well as a simple and light mechanism allowing to orientate the winglet angles between 90° and -90° of inclination. The structural model was exported to HyperMesh structural analysis software. Maximum stresses were obtained, and the model demonstrated its resistance to maximum aerodynamic loads as well as load factors of -2G to 7G.

scholarly journals Structural Design and Control of a Morphing Winglet to optimize the Aerodynamic Performance of the CRJ-700 Aircraft. Part 2 – Control

2021 ◽  
Vol 13 (4) ◽  
pp. 129-137
Author(s):  
Paul MEYRAN ◽  
Hugo PAIN ◽  
Ruxandra Mihaela BOTEZ ◽  
Jeremy LALIBERTÉ
Keyword(s):  
Structural Design ◽  
Aerodynamic Performance ◽  
Matlab Simulink ◽  
Flight Data ◽  
Geometrical Data ◽  
Morphing Technology ◽  
And Control

In this study, the morphing technology was applied on winglets for the CRJ-700 transport regional aircraft with the aim to improve its aerodynamic performance. The LARCASE Virtual Research Simulator VRESIM is equipped with highest Level D certified flight data for the CRJ-700. The flight and geometrical data of the CRJ-700 were used to quantify the aerodynamic benefits of the CRJ-700 equipped with a morphing winglet versus its reference winglet. The structural design and the mechanism allowing its rotation were used to allow the orientation of the winglet with angles between 90° and -90°. The control of the orientation of the morphing winglet with its mechanism was finally carried out using the Matlab/ Simulink interface. Therefore, a new concept of morphing winglet was obtained in this research.

scholarly journals Aerodynamic Performance of a Coaxial Hex-Rotor MAV in Hover

Aerospace ◽  
2021 ◽  
Vol 8 (12) ◽  
pp. 378
Author(s):  
Yao Lei ◽  
Jiading Wang ◽  
Wenjie Yang
Keyword(s):  
Performance Optimization ◽  
Structural Design ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Field Analysis ◽  
Test Results ◽  
Compact Structure ◽  
Coaxial Rotor ◽  
Optimum Aerodynamic ◽  
Flow Field Analysis

Micro aerial vehicles (MAVs) usually suffer from several challenges, not least of which are unsatisfactory hover efficiency and limited fly time. This paper discusses the aerodynamic characteristics of a novel Hex-rotor MAV with a coaxial rotor capable of providing higher thrust in a compact structure. To extend the endurance during hover, flow field analysis and aerodynamic performance optimization are conducted by both experiments and numerical simulations with different rotor spacing ratios (i = 0.56, 0.59, 0.63, 0.67, 0.71, 0.77, 0.83, 0.91). The measured parameters are thrust, power, and hover efficiency during the experiments. Retip ranged from 0.7 × 105 to 1.3 × 105 is also studied by Spalart–Allmaras simulations. The test results show that the MAV has the optimum aerodynamic performance at i = 0.56 with Retip = 0.85 × 105. Compared to the MAV with i = 0.98 for Retip = 0.85 × 105, thrust is increased by 5.18% with a reduced power of 3.8%, and hover efficiency is also improved by 12.14%. The simulated results indicate a weakness in inter-rotor interference with the increased rotor spacing. Additionally, the enlarged pressure difference, reduced turbulence, and weakened vortices are responsible for the aerodynamic improvement. This provides an alternative method for increasing the MAV fly time and offers inspiration for future structural design.

scholarly journals Structural Analysis of a Transport Aircraft Wing

2021 ◽  
Vol 13 (1) ◽  
pp. 3-9
Author(s):  
Yassir ABBAS ◽  
Tariq ELSONNI ◽  
Abdul Aziz ABDULMAJID ◽  
Alnazir KHALAFALLH ◽  
Mohammed ALNAZIR
Keyword(s):  
Structural Analysis ◽  
Structural Components ◽  
Safety Factors ◽  
Analysis Software ◽  
Aircraft Wing ◽  
Transport Aircraft ◽  
Aerodynamic Loads ◽  
Wing Model

In this study the procedures of structural analysis of a typical transport aircraft wing has been followed. The wing model has been drawn using CATIA® V5; this model consists of several structural components such as spars, ribs and skin. The model has been exported into structural analysis software ANSYS® 2016. Stresses, strains, deformations and safety factors were obtained for the model. It is found that the obtained stresses caused by the aerodynamic loads on the wing are within the design structural limits where the failure by yield or buckling has not been occurred

Development of a Hypersonic Aircraft Design Optimization Tool

2014 ◽  
Vol 553 ◽  
pp. 847-852 ◽  
Author(s):  
Benjamin J. Morrell ◽  
David J. Munk ◽  
Gareth A. Vio ◽  
Dries Verstraete
Keyword(s):  
Structural Design ◽  
Current Practice ◽  
Thermal Stresses ◽  
Aircraft Design ◽  
Material Strength ◽  
Aircraft Structure ◽  
Aerodynamic Loads ◽  
Design And Optimization ◽  
Hypersonic Aircraft ◽  
Strength And Stiffness

The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aeroelastic deformations in the early design and optimisation of the aircraft structure. This imposes the need for a closer coupling of the aerodynamic and structural design tools than is current practice. The paper presents the development of a multi-disciplinary, closely coupled optimisation suite for hypersonic aircraft. An overview of the setup and structure of the optimization suite is given and the integration between the Tranair solver, used to determine the aerodynamic loads and temperatures, and MSC/NASTRAN, used for the structural sizing and design, will be given.

scholarly journals Black-box Online Aerodynamic Performance Optimization for a Seamless Wing with Distributed Morphing

2022 ◽  
Author(s):  
Oscar Ruland ◽  
Tigran Mkhoyan ◽  
Roeland De Breuker ◽  
Xuerui Wang
Keyword(s):  
Performance Optimization ◽  
Aerodynamic Performance ◽  
Black Box

Nonlinear Fluid-Elastic Behavior of a Flapping Wing With Low-Order Chord-Wise Flexibility

2020 ◽  
Author(s):  
Dipanjan Majumdar ◽  
Chandan Bose ◽  
Sunetra Sarkar
Keyword(s):  
Structural Model ◽  
Flapping Wing ◽  
Elastic Behavior ◽  
Navier Stokes ◽  
Immersed Boundary ◽  
Stream Velocity ◽  
Aerodynamic Loads ◽  
Flow Parameters ◽  
Coupling Strategy ◽  
Nonlinear Fluid

Abstract The present study attempts to capture the fluid-structure interaction dynamics of a chord-wise flexible flapping wing system using a limited mode structural model coupled with a high-fidelity Navier-Stokes (N-S) solver. The wing is modeled as two elliptic rigid foils connected by a non-linear torsional spring that incorporates the chord-wise bending stiffness. The front link is subjected to an active pitching-plunging motion while the rear link undergoes flow-induced passive oscillation. The structural governing equation for the rear link takes the form of a Duffing equation subjected to base excitation and external aerodynamic forcing. The aerodynamic loads on the foil are computed using a discrete forcing Immersed Boundary Method based in-house N-S solver which is coupled with the structural solver by a staggered weak coupling strategy. A bifurcation study is performed considering the free-stream velocity as the control parameter, in the presence of both structural and aerodynamic non-linearities. A dynamical transition in the unsteady flow-field from a periodic reverse-Kármán wake to an aperiodic wake is observed as the flow parameters are varied. The same transition is also reflected in the passive oscillation of the rear foil when analyzed with tools from the dynamical systems theory.

An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Shuyi Zhang ◽  
Bo Yang
Keyword(s):  
Neural Network ◽  
Reynolds Number ◽  
Performance Optimization ◽  
Rotor Blade ◽  
Optimization Method ◽  
Aerodynamic Performance ◽  
Aerodynamic Optimization ◽  
Parametrization Method ◽  
Value Evaluation ◽  
Fitness Value

Abstract In this paper, an improved aerodynamic performance optimization method for 3-D low Reynolds number (Re) rotor blade is proposed. A conventional optimization procedure of blade is usually divided into three parts, such as the parameterization method, the fitness value evaluation and the optimization algorithm. This work is mainly focused on the first two parts. The parametrization method, Camber-FFD, is presented based on the camber parametrization method and the free-form deformation algorithm (FFD). The shape of 3-D blade is parameterized by the incidence angles and the coordinates of the maximum camber points. The fitness value evaluation has been realized with the help of an adaptive topological back propagation multi-layer forward artificial neural network (BP-MLFANN). During the training of BP-MLFANN, the hybrid particle swarm optimization method combined with the modified very fast simulate annealing algorithm (HPSO-MVFSA) is adopted to determine the neural network topology adaptively. To verify the effectiveness of this aerodynamic optimization method, the aerodynamic performance of a 3-D low-Re blade, such as Blade D900, is optimized, and the results are compared and analyzed based on the experiments and simulations. It is proved that this aerodynamic optimization method is feasible.

scholarly journals Differential evolution algorithm for performance optimization of the micro plasma actuator as a microelectromechanical system

2020 ◽  
Vol 10 (1) ◽  
Author(s):  
Javad Omidi ◽  
Karim Mazaheri
Keyword(s):  
Differential Evolution ◽  
Wind Turbine ◽  
Turbine Blade ◽  
Performance Optimization ◽  
Stokes Equations ◽  
Differential Evolution Algorithm ◽  
Aerodynamic Performance ◽  
Wind Turbine Blade ◽  
Electrostatic Model ◽  
Dielectric Thickness

Abstract Dielectric Discharge Barrier (DBD) plasma actuators are considered as one of the best active electro-hydrodynamic control devices, and are considered by many contemporary researchers. Here a simple electrostatic model, which is improved by authors, and uses the Maxwell’s and the Navier–Stokes equations, is proposed for massive optimization computations. This model is used to find the optimum solution for application of a dielectric discharge barrier on a curved surface of a DU25 wind turbine blade airfoil, in a range of 5–18 kV applied voltages, and 0.5 to 13 kHz frequency range. Design variables are selected as the dielectric thickness and material, and thickness and length of the electrodes, and the applied voltage and frequency. The aerodynamic performance, i.e. the lift to drag ratio of the wind turbine blade section is considered as the cost function. A differential evolution optimization algorithm is applied and we have simultaneously found the optimized value of both geometrical and operational parameters. Finally the optimized value at each voltage and frequency are sought, and the optimum aerodynamic performance is derived. The physical effect of each design variable on the aerodynamic performance is discussed. A design relation is proposed to recommend an optimum design for wind turbine applications.

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