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.

Conceptual Design for the Performance Optimization of Compound Coaxial Helicopter

2016 ◽  
Vol 826 ◽  
pp. 40-44 ◽  
Author(s):  
Fei Cao ◽  
Ming Chen ◽  
Mei Li Wen Wu
Keyword(s):  
Conceptual Design ◽  
Performance Optimization ◽  
Design Method ◽  
Aircraft Design ◽  
Design Parameters ◽  
Design Work ◽  
Design And Optimization ◽  
Conceptual Design Phase ◽  
And Performance ◽  
Coaxial Helicopter

The purpose of this paper is to study the conceptual design and optimization of a compound coaxial helicopter. At the conceptual design phase, the compound coaxial helicopter design work was based on the conventional helicopter and fix-wing aircraft design method. The intersection of these aspects makes the design work more complex, thus, a program for the sizing and performance optimization was developed for the aircraft. The program included the total weight design, aerodynamic analysis, flight dynamics analysis, performance calculation and particle swarm optimization analysis. Under the restricted condition of the flight performance requirements, optimize the design parameters which make the weight efficiency factor decrease. Therefore, the study of optimum design process was warranted.

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.

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.

Advanced aircraft performance analysis

2018 ◽  
Vol 90 (4) ◽  
pp. 627-638 ◽  
Author(s):  
Marc Immer ◽  
Philipp Georg Juretzko
Keyword(s):  
Performance Analysis ◽  
Design Process ◽  
Performance Optimization ◽  
Electric Propulsion ◽  
Vertical Plane ◽  
Aircraft Design ◽  
Efficient Design ◽  
Content Type ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

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.

Estimation of Lateral/Directional Static Stability Characteristics of a Turboprop Aircraft at one Engine Inoperative Condition

2016 ◽  
Vol 842 ◽  
pp. 208-216 ◽  
Author(s):  
Ratna Ayu Wandini ◽  
Taufiq Mulyanto ◽  
Hari Muhammad
Keyword(s):  
Short Distance ◽  
Fuel Efficiency ◽  
Aircraft Design ◽  
Static Stability ◽  
Slip Angle ◽  
High Fuel Efficiency ◽  
Stability And Control ◽  
Conceptual Design Phase ◽  
The Stability ◽  
And Control

Twin engines turboprop aircraft provides the most beneficial solution to meet the needs of short distance flight due to high fuel efficiency [1]. One of the emergency conditions which has to be considered for this type of the aircraft when one engine is out operating or one engine inoperative because it involves the safety of flight. Furthermore, a safe flight with one engine inoperative is regulated by FAR/CASR Part 25 and has to be complied during certification .Stability and control characteristics of a turboprop aircraft will change significantly if one engine inoperative condition occurs during cruise phase. The rudder and/or aileron deflections to counter the yawing and rolling moments due to the thrust of the operating engine must satisfy. Recognizing the importance of that consideration, this research will estimate the stability and control characteristics of lateral/directional in one engine inoperative condition on new turboprop 80-pax aircraft design concept.This paper presents procedures for estimating the lateral/directional static stability characteristics of a 80-pax turboprop aircraft during the conceptual design phase. The size of the rudder and aileron have to be iterated to fullfil the requirements at a condition when one engine is not operative. The rudder and the aileron deflections are estimated as functions of airspeed, roll angle, side slip angle and thrust setting. It will be shown in this paper that the required rudder deflection as well as aileron deflection can satisfy to balance the forces and moments due to asymmetrical thrust condition and the minimum control speed of the aircraft can be maintained as well.

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.

scholarly journals A Novel Latin Hypercube Algorithm via Translational Propagation

2014 ◽  
Vol 2014 ◽  
pp. 1-15 ◽  
Author(s):  
Guang Pan ◽  
Pengcheng Ye ◽  
Peng Wang
Keyword(s):  
Computation Time ◽  
Latin Hypercube Design ◽  
Latin Hypercube ◽  
Space Filling ◽  
Enumeration Algorithm ◽  
Latin Hypercube Designs ◽  
Initial Block ◽  
Optimal Latin Hypercube Design ◽  
Computationally Expensive ◽  
Formal Optimization

Metamodels have been widely used in engineering design to facilitate analysis and optimization of complex systems that involve computationally expensive simulation programs. The accuracy of metamodels is directly related to the experimental designs used. Optimal Latin hypercube designs are frequently used and have been shown to have good space-filling and projective properties. However, the high cost in constructing them limits their use. In this paper, a methodology for creating novel Latin hypercube designs via translational propagation and successive local enumeration algorithm (TPSLE) is developed without using formal optimization. TPSLE algorithm is based on the inspiration that a near optimal Latin Hypercube design can be constructed by a simple initial block with a few points generated by algorithm SLE as a building block. In fact, TPSLE algorithm offers a balanced trade-off between the efficiency and sampling performance. The proposed algorithm is compared to two existing algorithms and is found to be much more efficient in terms of the computation time and has acceptable space-filling and projective properties.

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