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

Cao, Runduo; Zhang, Xiaobing

doi:10.1007/s00158-017-1845-7

Cited by 11 publications

(2 citation statements)

References 26 publications

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“…Anderson et al (2000) proposed also optimization study for missile aerodynamic using Pareto genetic algorithm. Runduo and Xiaobing (2018) performed aerodynamic shape optimization for a rocket. Non-dominated sorting genetic algorithm (NSGA-II) and the real coding genetic algorithm (RGA) were used and the results of the study showed that the lift-to-drag ratio was increased and the maneuverability was improved as a result of optimization process.…”

Section: Introductionmentioning

confidence: 99%

CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

Şumnu

Güzelbey

2021

JAFM

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The wing of missile can be considered as an effective factor for determination of lift to drag ratio. However, there are few studies that investigate wing effect on missile aerodynamics. Therefore, the purpose of this study is to indicate wing effect on the missile aerodynamics and optimize wing geometry for enhancement of aerodynamic efficiency. The missile designed tail-fin configuration is selected from a previous study which contains experimental data. In the beginning of study, Computational Fluid Dynamics (CFD) simulations of selected missile are performed and compared with experimental data. Wing is then mounted to the selected missile and CFD solution is repeated for modified missile at 6º angle of attach (AoA) and subsonic and supersonic speeds. The modified missile shows good performance in point of aerodynamics when compared with baseline missile model. In addition, wing geometry is optimized to improve aerodynamic performance using Multi-Objective Genetic Algorithm (MOGA). Objective functions are determined as lift and drag coefficients. Wing geometry parameters are determined as design variables for optimization. After the optimization process, the results are showed that the aerodynamic coefficients are improved when compared with baseline geometry. In addition, response surface analysis is presented to show which design parameters are more effective on drag and lift forces. The findings of study show that optimum results are more efficient in terms of performance. CFD solution method and the optimization procedure can be applied to design or optimize for different geometry.

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Section: Introductionmentioning

confidence: 99%

CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

Şumnu

Güzelbey

2021

JAFM

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“…The predictions of aerodynamic coefficients were obtained by using both AERODSN routine and Missile DATCOM software packages. Runduo and Xiaobing [11] studied the aerodynamic shape optimization subject. To solve this multiobjective optimization problem, they used nondominated sorting genetic algorithm (NSGA-II) and real-coded genetic algorithm (RGA) methods.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Shape Optimization of a Missile Using a Multiobjective Genetic Algorithm

Şumnu

Güzelbey

Öğücü

2020

International Journal of Aerospace Engineering

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The aim of this paper is to demonstrate the effects of the shape optimization on the missile performance at supersonic speeds. The N1G missile model shape variation, which decreased its aerodynamic drag and increased its aerodynamic lift at supersonic flow under determined constraints, was numerically investigated. Missile geometry was selected from a literature study for optimization in terms of aerodynamics. Missile aerodynamic coefficient prediction was performed to verify and compare with existing experimental results at supersonic Mach numbers using SST k-omega, realizable k-epsilon, and Spalart-Allmaras turbulence models. In the optimization process, the missile body and fin design parameters need to be estimated to design optimum missile geometry. Lift and drag coefficients were considered objective function. Input and output parameters were collected to obtain design points. Multiobjective Genetic Algorithm (MOGA) was used to optimize missile geometry. The front part of the body, the main body, and tailfins were improved to find an optimum missile model at supersonic speeds. The optimization results showed that a lift-to-drag coefficient ratio, which determines the performance of a missile, was improved about 11-17 percent at supersonic Mach numbers.

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A Novel Launching System Applying a Relay Chamber Technology and Its Optimization

Cao

Zhang

2019

Propellants Explo Pyrotec

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This paper investigates a novel launching system with a relay chamber using optimization method. For revealing the influences of new structures on the overall interior ballistic performance, the launching process of this novel system is modeled and a series of different schemes are simulated. In view of more design variables to be involved and conflicting objectives to be achieved, complete optimization of the interior ballistic performance is a complex process. A popular standard particle swarm optimization algorithm is used to obtain an optimal loading condition, together with a proper design of the relay chamber. Furthermore, for an existing cannon gun without modifying its structure, the charge system is re‐designed and simulated using the SPSO algorithm in this novel method and conventional method respectively. Compared with the original scheme, both optimal schemes could get higher muzzle velocity, while the novel method could improve by 16.5 % and the conventional method could improve by only 5.7 %. It means that this novel launch system could improve the interior ballistics performance obviously and it still has considerable potential to be ameliorated.

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

Cited by 11 publications

References 26 publications

CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

Aerodynamic Shape Optimization of a Missile Using a Multiobjective Genetic Algorithm

A Novel Launching System Applying a Relay Chamber Technology and Its Optimization

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