Integrated aerodynamics/structure/stability optimization of large aircraft in conceptual design

2017 ◽  
Vol 232 (4) ◽  
pp. 745-756 ◽  
Author(s):  
Zhi-Qiang Wan ◽  
Xiao-Zhe Wang ◽  
Chao Yang
Keyword(s):  
Aircraft Design ◽  
Optimization Method ◽  
Correction Method ◽  
Structure Stability ◽  
Total Drag ◽  
Structure And Stability ◽  
Integrated Optimization ◽  
A Value ◽  
Beam Frame ◽  
Large Aircraft

The multidisciplinary design optimization is suitable for modern large aircraft, and it has the potential in conceptual phase of aircraft design especially. An integrated optimization method considering the disciplines of aerodynamics, structure and stability for large aircraft design in conceptual phase is presented. The objective is the minimum stiffness of a beam-frame wing structure subject to aeroelasticity, aerodynamics, and stability constraints. The aeroelastic responses are computed by commercial software MSC. Nastran, and the cruise stability is evaluated by the linear small-disturbance equations. A viscous-inviscid iteration method, which is composed of a computational fluid dynamics tool solving the Euler equations and a viscous correction method, is used for computing the flow over the model. The method ensures effective and rapid computation. In this paper, a complete aircraft model is optimized, and all the responses are computed in the trim condition with a fixed maximum takeoff weight. Genetic algorithm is utilized for global optimizations, and the optimal jig shape, the elastic axis positions and the stiffness distribution can be attained adequately. The results show that the method has a value of application in engineering optimizations. For the satisfaction of the total drag and stability constraints, the structure weight usually needs a price to pay. The integrated optimization captures the tradeoff between aerodynamics, structure and stability, and the repeated design can be avoided.

Conceptual Design of a 200 Passenger Blended Wing Body Aircraft

2014 ◽  
Author(s):  
Sami Ammar ◽  
Jean-Yves Trépanier
Keyword(s):  
Dynamic Stability ◽  
Conceptual Design ◽  
Aircraft Design ◽  
Optimization Methods ◽  
Integrated Optimization ◽  
Aerodynamic Analysis ◽  
Performance Improvements ◽  
Static And Dynamic Stability ◽  
Blended Wing Body ◽  
Large Aircraft

The Blended Wing Body (BWB) aircraft is based on the flying wing concept. For this aircraft the literature has reported performance improvements compared to conventional aircraft. However, most BWB studies have focused on large aircraft and it is not sure whether the gains are the same for smaller aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a stable aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB aircraft.

scholarly journals Metaheuristic Approaches to Solve a Complex Aircraft Performance Optimization Problem

2019 ◽  
Vol 9 (15) ◽  
pp. 2979 ◽  
Author(s):  
Guirong Dong ◽  
Xiaozhe Wang ◽  
Dianzi Liu
Keyword(s):  
Performance Optimization ◽  
Carbon Dioxide Emissions ◽  
Aircraft Design ◽  
Latin Hypercube Design ◽  
Conceptual Design Phase ◽  
Multidisciplinary Analysis ◽  
Optimal Latin Hypercube Design ◽  
Wing Geometry ◽  
Beam Frame ◽  
Large Aircraft

The increasing demands for travelling comfort and reduction of carbon dioxide emissions have been considered substantially in the stage of conceptual aircraft design. However, the design of a modern aircraft is a multidisciplinary process, which requires the coordination of information from several specific disciplines, such as structures, aerodynamics, control, etc. To address this problem with adequate accuracy, the multidisciplinary analysis and optimization (MAO) method is usually applied as a systematic and robust approach to solve such complex design issues arising from industries. Since MAO method is tedious and computationally expensive, genetic programming (GP)-based metamodeling techniques incorporating MAO are proposed as an effective approach to minimize the wing stiffness of a large aircraft subject to aerodynamic, aeroelastic and stability constraints in the conceptual design phase. Based on the linear small-disturbance theory, the state-space equation is employed for stability analysis. In the process of multidisciplinary analysis, aeroelastic response simulations are performed using Nastran. To construct metamodels representing the responses of the interests with high accuracy as well as less computational burden, optimal Latin hypercube design of experiments (DoE) is applied to determine the optimized distribution of sampling points. Following that, parametric optimization is carried out on metamodels to obtain the optimal wing geometry shape, elastic axis positions and stiffness distribution, and then the solution is verified by finite element simulations. Finally, the superiority of the GP-based metamodel technique over genetic algorithm is demonstrated by multidisciplinary design optimization of a representative beam-frame wing structure in terms of accuracy and efficiency. The results also show that GP metamodel-based strategy for solving MAO problems can provide valuable insights to tailoring parameters for the effective design of a large aircraft in the conceptual phase.

A new jig-shape optimization method for the high aspect ratio wing

2018 ◽  
Vol 91 (1) ◽  
pp. 124-133
Author(s):  
Zhe Yuan ◽  
Shihui Huo ◽  
Jianting Ren
Keyword(s):  
Aspect Ratio ◽  
Shape Optimization ◽  
High Aspect Ratio ◽  
Optimization Design ◽  
Design Method ◽  
Aircraft Design ◽  
Optimization Method ◽  
Attack Angle ◽  
Structural Deformation ◽  
Content Type

Purpose Computational efficiency is always the major concern in aircraft design. The purpose of this research is to investigate an efficient jig-shape optimization design method. A new jig-shape optimization method is presented in the current study and its application on the high aspect ratio wing is discussed. Design/methodology/approach First, the effects of bending and torsion on aerodynamic distribution were discussed. The effect of bending deformation was equivalent to the change of attack angle through a new equivalent method. The equivalent attack angle showed a linear dependence on the quadratic function of bending. Then, a new jig-shape optimization method taking integrated structural deformation into account was proposed. The method was realized by four substeps: object decomposition, optimization design, inversion and evaluation. Findings After the new jig-shape optimization design, both aerodynamic distribution and structural configuration have satisfactory results. Meanwhile, the method takes both bending and torsion deformation into account. Practical implications The new jig-shape optimization method can be well used for the high aspect ratio wing. Originality/value The new method is an innovation based on the traditional single parameter design method. It is suitable for engineering application.

scholarly journals Development of the Low Toxic Cross Polar Air Transport using Innovative Hydrogen Projection for Large Aircraft and Airships

2021 ◽  
Vol 2 (6) ◽  
pp. 1-4
Author(s):  
Ponyaev L
Keyword(s):  
International Law ◽  
Low Cost ◽  
Minimum Weight ◽  
Aircraft Design ◽  
Air Transportation ◽  
Air Transport ◽  
Airport Infrastructure ◽  
Design Options ◽  
Transportation Routes ◽  
Large Aircraft

The new shortly and low cost Regular Airlines Cargo & PAX directions via Arctic Cross Polar Air Transportation Routes of the future High Ecology Efficiency and Safety ICAO Strategy will be base on the more perspective for Trans Continental Airlines Operations by IATA International Law Regulations and World Climate Protect Law. Using the more shortly directions of Trans Polar Flight for Long-Haul Aircrafts (LHA) Routes by leader Airlines Sky Teams with Aeroflot are request to find new Geometrical Layout of Aircraft Design Industrial Projections & Products Lines. The increase in the dimension of LHA came into conflict with modern Airport Infrastructure and led to the search for alternative Arctic Planes & Dirigibles Options for constructively layout circuit solutions with protection of minimum weight and drag issues in order to deal with this contradiction. Computer Digital Aircraft Structural-Parametric Analysis of the influence of Aviation Infrastructure Constraints in the basing of LHA on the choice of alternative Design Options for Lift Fuselage Body or Flying-V layout was carried out.

scholarly journals PARTICLE SIZE DISTRIBUTION CORRECTION METHOD USING A SIMULATED ANNEALING TECHNIQUE

2011 ◽  
Vol 10 (1-2) ◽  
pp. 39
Author(s):  
A. N. Diógenes ◽  
L. O. E. dos Santos ◽  
C. P. Fernandes
Keyword(s):  
Particle Size ◽  
Distribution Function ◽  
Simulated Annealing ◽  
Particle Size Distribution ◽  
Size Distribution ◽  
Optimization Method ◽  
Correction Method ◽  
Logistic Function ◽  
Three Dimensions ◽  
Circular Particle

The procedure for obtaining the particle size distribution by visual inspection of a sample involves stereological errors, given the cut of the sample. A cut particle, supposedly spherical, with radius R, will be counted as a circular particle with radius r, r≤R. The difference between r and R depends on how far from the center of the sphere the cut was performed. This introduces errors when the extrapolation of the properties from two to three dimensions during the analysis of a sample. The usual method is to correct the distribution by probabilistic functions, which have large errors. This paper presents a method to reduce the error inherent to this problem. The method is to compute a simulation of the preparation process in a sample whose structure can be described by non-penetrating spheres of various diameters which meet a known probability distribution function, for example, a log-logistic function, or even a constant function. For each distribution radius, a number of spheres is generated and virtually cut, generating a bi-dimensional (2D) distribution. The 2D curves of the spheres distribution obtained in this simulation are compared with that obtained by the experimental procedure and then the parameters of the threedimensional distribution function are adjusted until the 2D curves are similar to the experimental one using the optimization method Simulated Annealing for the curve-fitting. In future this method will be applied to the analysis of the oil reservoir rocks.

An Explicit Method for the Packing Limit Management in Dense Gas-Solid Flow CFD Simulations on Both Structured and Unstructured Grids

2007 ◽  
Vol 5 (1) ◽  
Author(s):  
Alberto Passalacqua ◽  
Luca Marmo
Keyword(s):  
Volume Fraction ◽  
Correction Method ◽  
Computational Grids ◽  
Fluidised Bed ◽  
Explicit Method ◽  
Dense Gas ◽  
Cfd Simulations ◽  
A Value ◽  
Uniform Grids ◽  
Superficial Gas Velocity

An explicit method for limiting the volume fraction of the dispersed phase in the CFD simulations of dense gas-solid flows is described and validated both on structured and unstructured computational grids. The procedure is based on the excess solids volume correction method proposed by Lettieri et al. (2003), which has been extended in this work to non-uniform grids made of cells having different shape and size. The method has been implemented in OpenFOAM and validated through the simulation of a fluidised bed in which the superficial gas velocity has been reduced to a value close to zero.

IFCIP: An integrated optimization method for planning filters in fluid power systems under uncertainty

2011 ◽  
Vol 43 (3) ◽  
pp. 329-348 ◽  
Author(s):  
S. L. Nie ◽  
Y. L. Zheng ◽  
Y. P. Li ◽  
S. Peng ◽  
G. H. Huang
Keyword(s):  
Power Systems ◽  
Optimization Method ◽  
Fluid Power ◽  
Integrated Optimization ◽  
Fluid Power Systems

The Optimization of Chain of Talents on the Development of Large Aircraft

2012 ◽  
Vol 452-453 ◽  
pp. 613-617
Author(s):  
An Wei Sun ◽  
Yi Huang
Keyword(s):  
Aircraft Design ◽  
Development Project ◽  
Aviation Industry ◽  
High Tech ◽  
High Tech Industry ◽  
Long Period ◽  
High Investment ◽  
Technology And Economy ◽  
Distinct Features ◽  
Large Aircraft

The aviation industry is a typically high-tech industry, which rallies a large number of high-tech achievements of mankind. Its distinct features are the high investment, long period and strong pulling function to industry. The development of large aircraft has currently become an important economic development project to promote the successful combination of technology and economy. The resources of talents are an important guarantee for this industry. First, this article studies the meaning of the talents and the chain of talents, on this basis, analyzes the chain of talents by means of SWOT, further explores optimization strategies of the chain of talents in order to serve for the large aircraft design talent strategies of our country.

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