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

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Abstract

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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Abbreviations

Cl :

Lift-force coefficient

Cd :

Drag-force coefficient

Cm :

Pitching-moment coefficient

L tot :

Total length of rocket

L n :

Length of nose

L rw :

Length of tailfin root

L tw :

Length of tailfin tip

λ lw :

Sweepback of tailfin’s leading edge

λ tw :

Sweepback of tailfin’s trailing edge

X 0w :

Position of tailfin

x cp :

Position of pressure center

Ma :

Mach number

Re :

Reynolds number

α :

Angle of attack

Lm:

Length of body (calibers)

L t :

Length of tail

L rc :

Length of canard root

L tc :

Length of canard tip

λ lc :

Sweepback of canard’s leading edge

λ tc :

Sweepback of canard’s trailing edge

X 0c :

Position of canard

x G :

Position of gravity center

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Acknowledgments

This work is supported by the National Natural Science Foundation of China (Grant No. 11502114), China Postdoctoral Science Foundation funded project (Grant No. 2015 M581797),the Natural Science Foundation of Jiangsu Province (Grant No. BK20131348) and Key Laboratory Foundation of the People’s Republic of China (Grant No. 9140C300206120C30110).

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Authors and Affiliations

  1. School of Energy and Power Engineering, Nanjing University of Science and Technology, No. 200, Xiao Lingwei Street, Nanjing, Jiangsu, 210094, China

    Cao Runduo & Zhang Xiaobing

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  1. Cao Runduo
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  2. Zhang Xiaobing
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Correspondence to Zhang Xiaobing.

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Runduo, C., Xiaobing, Z. Multi-objective optimization of the aerodynamic shape of a long-range guided rocket. Struct Multidisc Optim 57, 1779–1792 (2018). https://doi.org/10.1007/s00158-017-1845-7

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  • DOI: https://doi.org/10.1007/s00158-017-1845-7

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