Multi-objective optimization of the aerodynamic shape of a long-range guided rocket

The parameter values associated with the optimal aerodynamic shape of a long-range guided rocket (LGR) are different from those of an unguided rocket because the shapes and design objectives are different. Here we establish a multi-objective optimization model of the aerodynamic shape of an LGR for...

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Bibliographic Details
Published inStructural and multidisciplinary optimization Vol. 57; no. 4; pp. 1779 - 1792
Main Authors Runduo, Cao, Xiaobing, Zhang
Format Journal Article
LanguageEnglish
Published Berlin/Heidelberg Springer Berlin Heidelberg 01.04.2018
Springer Nature B.V
Subjects
Aerodynamic stability
Aerodynamics
Airships
Appliance industry
Classification
Computational fluid dynamics
Computational Mathematics and Numerical Analysis
Cooling
Engineering
Engineering Design
Genetic algorithms
Industrial Application
Maneuverability
Manufacturing
Mathematical models
Missile defense
Multiple objective analysis
Parameter identification
Shape optimization
Sorting algorithms
Theoretical and Applied Mechanics
Wind tunnel testing
Wind tunnels
NSGA-II
Multi-objective optimization
Aerodynamic shape design
Long-range guided rockets
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Summary:The parameter values associated with the optimal aerodynamic shape of a long-range guided rocket (LGR) are different from those of an unguided rocket because the shapes and design objectives are different. Here we establish a multi-objective optimization model of the aerodynamic shape of an LGR for the purpose. Moreover, a rapid aerodynamic calculation method is used, which is much more efficient than wind-tunnel tests or computational fluid dynamics (CFD). Previously, the aerodynamic shape of an unguided rocket would be optimized by identifying one parameter as a single objective and regarding the others as constraints. Here, we use version II of the non-dominated sorting genetic algorithm (NSGA-II) and the real-coding genetic algorithm (RGA) to solve this multi-objective optimization problem (MOP). The results obtained by the two algorithms show an improved lift/drag ratio of the LGR with optimal aerodynamic shape, better maneuverability, and acceptable stability. Furthermore, the optimum and original schemes are calculated using CFD, and the pressure contours show that the results are qualitatively correct. This method can be used to design the optimal aerodynamic shape of this type of rocket.
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ISSN:1615-147X
1615-1488
DOI:10.1007/s00158-017-1845-7