Studies on Morphing Aircraft Design including Engine parameters using Genetic Algorithm

2014 ◽  
Author(s):  
Amareshwara Sainadh Chamarthi ◽  
Rajkumar S. Pant
Keyword(s):  
Genetic Algorithm ◽  
Aircraft Design ◽  
Morphing Aircraft

scholarly journals Improved Immune Genetic Algorithm to Optimize the Design of Wing Structure of Competition Aircraft

2021 ◽  
Vol 2137 (1) ◽  
pp. 012075
Author(s):  
Xi Feng ◽  
Yafeng Zhang
Keyword(s):  
Genetic Algorithm ◽  
Aircraft Design ◽  
Flight Test ◽  
Optimization Methods ◽  
Optimization Method ◽  
Design Parameters ◽  
Immune Genetic Algorithm ◽  
Maximum Deformation ◽  
Design Variables ◽  
Wing Structure

Abstract An improved immune genetic algorithm is used to design and optimize the wing structure parameters of a competition aircraft. According to the requirements of aircraft design, multi-objective optimization index is established. On this basis, the basic steps of using immune algorithm to optimize the main design parameters of aircraft wing structure are proposed, and the optimization of the wing parameters of a competition aircraft is used as an example for simulation calculation. The design variables in the optimization are the size of the wing components, and the optimization goal is to minimize the weight of the wing and the maximum deformation of the wing structure. Research shows that compared with traditional optimization methods; the improved immune genetic algorithm is a very effective optimization method. At the same time, a prototype is made to check the validity and feasibility of the design. Flight test results show that the optimization method is very effective. Although the method is proposed for competition aircraft, it is also applicable to other types of aircraft.

OPTIMAL GEOMETRICAL DESIGN OF AIRCRAFT USING GENETIC ALGORITHMS

2003 ◽  
Vol 26 (4) ◽  
pp. 373-388 ◽  
Author(s):  
Nicholas Ali ◽  
Kamran Behdinan
Keyword(s):  
Genetic Algorithm ◽  
Penalty Method ◽  
Aircraft Design ◽  
Cost Effective ◽  
Design Parameters ◽  
Adaptive Penalty ◽  
Search Tool ◽  
And Performance ◽  
Aircraft Sizing ◽  
Adaptive Penalty Method

With the advent of computers and search and optimization tools such as the genetic algorithm, the ability to manipulate numerous aircraft design parameters in a reasonable amount of time is feasible. From this angle, the lengthy time and effort spent creating and integrating aerodynamics codes, sizing routines, and performance modules, can be mitigated by the use of a genetic algorithm. Consequently, a genetic algorithm has been created and employed as a cost effective tool to explore possible aircraft geometries in the conceptual design process of the aircraft. A program has been developed to address most aspects of aircraft design such as aircraft sizing and configuration, performance, and propulsion, to name a few. These codes have been integrated into a genetic algorithm, which performs the task of searching and optimizing. The adaptive penalty method has been employed to handle all constraints imposed on the design. In addition, adjustments for varying degrees of selection and crossover intensities and types have been studied. A design study has also been carried out to compare an existing aircraft shape with the genetic algorithm optimized aircraft shape and configuration. Results indicate that the genetic algorithm is a powerful multi-disciplinary optimization and search tool, capable of simultaneously managing and varying numerous aircraft design parameters. Moreover, the genetic algorithm is capable of finding aircraft geometries and configurations that are both efficient and cost effective.

Conceptual design of UAV using Kriging based multi-objective genetic algorithm

2008 ◽  
Vol 112 (1137) ◽  
pp. 653-662 ◽  
Author(s):  
S. Rajagopal ◽  
R. Ganguli
Keyword(s):  
Genetic Algorithm ◽  
Conceptual Design ◽  
Empirical Relation ◽  
Aircraft Design ◽  
Function Evaluation ◽  
Maximum Speed ◽  
Nsga Ii ◽  
Multi Objective ◽  
Multi Objective Genetic Algorithm ◽  
Multidisciplinary Design Optimisation

Abstract This paper highlights unmanned aerial vehicle (UAV) conceptual design using the multi-objective genetic algorithm (MOGA). The design problem is formulated as a multidisciplinary design optimisation (MDO) problem by coupling aerodynamic and structural analysis. The UAV considered in this paper is a low speed, long endurance aircraft. The optimisation problem uses endurance maximization and wing weight minimisation as dual objective functions. In this multi-objective optimisation, aspect ratio, wing loading, taper ratio, thickness-to-chord ratio, loiter velocity and loiter altitude are considered as design variables with stall speed, maximum speed and rate of climb as constraints. The MDO system integrates the aircraft design code, RDS and an empirical relation for objective function evaluation. In this study, the optimisation problem is solved in two approaches. In the first approach, the RDS code is directly integrated in the optimisation loop. In the second approach, Kriging model is employed. The second approach is fast and efficient as the meta-model reduces the time of computation. A relatively new multi-objective evolutionary algorithm named NSGA-II (non-dominated sorting genetic algorithm) is used to capture the full Pareto front for the dual objective problem. As a result of optimisation using multi-objective genetic algorithm, several non-dominated solutions indicating number of useful Pareto optimal designs is identified.

Morphing Aircraft: An Improbable Dream?

2014 ◽  
Author(s):  
Michael I. Friswell
Keyword(s):  
Smart Materials ◽  
Aircraft Design ◽  
System Level ◽  
Accurate Analysis ◽  
Bird Flight ◽  
Limited Region ◽  
Morphing Aircraft ◽  
Wing Sweep ◽  
Aircraft Performance ◽  
Morphing Technology

Compliant aircraft, with a range of deformations comparable to birds, has been a dream for many years. Earlier aviation pioneers tried to replicate aspects of bird flight, but higher air speeds and larger payloads have required aircraft design to deviate from their biological inspiration. The design of conventional fixed wing aircraft can only be optimized for a limited region of the flight envelope; mechanisms such as deployable flaps and wing sweep are used extensively to enlarge this envelope. The development of more accurate analysis tools, advanced smart materials, and the increasingly demands for improved aircraft performance, are driving research into compliant morphing aircraft. These aircraft have the potential to adapt and optimize their shape to improve flight performance or achieve multi-objective mission roles. However this technology has rarely been adopted on production aircraft. This paper will critically review the progress made to date on compliant morphing aircraft research, and summarize the challenges that need to be addressed before such technology can be adopted widely. In particular the need to demonstrate system level performance benefits for morphing technology is emphasized.

Effect of Actuating Forces on Aeroelastic Characteristics of a Morphing Aircraft Wing

2011 ◽  
Vol 52-54 ◽  
pp. 308-317 ◽  
Author(s):  
Suwin Sleesongsom ◽  
Sujin Bureerat
Keyword(s):  
Flight Control ◽  
Mechanical Characteristics ◽  
Aircraft Design ◽  
Design Parameters ◽  
Morphing Aircraft ◽  
Control Effectiveness ◽  
Wing Structure ◽  
External Forces ◽  
Lift Control ◽  
External Loads

An aircraft with morphing or adaptive wings can achieve its flight control through structural flexibility. In order to carry out such aircraft control, the wing structure is actuated by an external force. This leads to a change in aircraft aeroelastic and mechanical characteristics during flight such as lift, control effectiveness, divergence, flutter, buckling, and stress. The objective of this research is to demonstrate the aeroelastic and mechanical behaviors of a wing being actuated by external forces. Static and dynamic aeroelastic models of a wing structure subject to external loads are derived. An un-swept rectangular wing box, using a twisting morphing concept, is used for the demonstration. By applying various values of an actuator moment to the wing, aircraft design parameters e.g. flutter, divergence, lift effectiveness, buckling factor, and stress are computed. The investigation shows that the actuating force has an impact on the aeroelastic and mechanical characteristics. This effect should be taken into account during the design/optimization process of a morphing aircraft structure.

scholarly journals Scheduling of Aircraft Design Project: A Comparison of Critical Path Method, Design Structure Matrix and Genetic Algorithm Approaches

2018 ◽  
Vol 248 ◽  
pp. 03011 ◽  
Author(s):  
Ariani Amalia ◽  
M. Dachyar ◽  
Farizal
Keyword(s):  
Genetic Algorithm ◽  
Critical Path ◽  
Aircraft Design ◽  
Alternative Methods ◽  
Combination Method ◽  
Design Structure Matrix ◽  
Critical Path Method ◽  
Structure Matrix ◽  
Design Project ◽  
Design Structure

The purpose of this study to minimize the overall duration of aircraft design project in Indonesia. This study proposes a combination method of Design Structure Matrix (DSM) and Genetic Algorithm (GA) for scheduling aircraft design project activities. DSM is used to identify the information flow between project activities. GA use reworks data, which was the result output of DSM, and activity duration to optimize the task sequence by considering the human resource constraints. A comparative analysis was conducted between the schedule based on DSM and GA and schedule based on Critical Path Method. Combination of DSM and GA obtained 63 days shorter project durations compared to CPM. This research is convenient for design projects scheduling with limited resources that can be obtained by using alternative methods other than traditional methods.

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