Aerodynamic Shape Optimization System of a Canard-Controlled Missile Using Trajectory-Dependent Aerodynamic Coefficients

Yang, Young Rok; Jung, Sung-Ki; Cho, Tae Hwan; Myong, R.S.

doi:10.2514/1.a32064

Cited by 16 publications

(5 citation statements)

References 10 publications

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“…Yang et al optimized the range of a canardcontrolled missile by optimizing its aerodynamic shape benefiting from the genetic algorithm method [1]. Tanrıkulu and Ercan offered an optimal external configuration design method to optimize the range, stability, and warhead performance of missiles [2].…”

Section: Introductionmentioning

confidence: 99%

Balistik Mühimmat Menzillerinin Hızlandırıcı Fırlatıcı Konsepti Kullanılarak Uzatılmasının Analizi

Tola

Beyazpinar

Akin

2021

Journal of Aviation

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In this study, the feasibility of a new launcher concept that provides range extension for outdated ballistic munitions by speeding up them before their ignition is examined in detail. To analyze the efficiency of the new concept, multi-variable and single-variable optimization processes are conducted using the Multi-Objective Genetic Algorithm Method in the ModeFrontier environment. Launch angle, ejection velocity of the munition from the launcher, and ignition delay of the rocket motor after the ejection process are determined as design variables. An in-house MATLAB script is prepared and validated to perform numerical solutions of the munition's two-dimensional trajectory. As a result of the optimization processes, graphical results are prepared to examine the effects of each design variable on munition's range and to make a comparison between the flight trajectories of the munitions which are launched from classical and accelerator launchers. It is concluded that usage of the accelerator launcher concept provides approximately 20% range extension for the generic munition examined in this research when compared to the classical launcher. Since this new concept can easily be adapted to different types of outdated ballistic munitions and the cost of the accelerator launcher development process will probably less than the cost required to develop new munitions, it will be reasonable to develop accelerator launchers such as electromagnetic accelerators or catapult launchers in near future.

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Section: Introductionmentioning

confidence: 99%

Balistik Mühimmat Menzillerinin Hızlandırıcı Fırlatıcı Konsepti Kullanılarak Uzatılmasının Analizi

Tola

Beyazpinar

Akin

2021

Journal of Aviation

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“…To solve this multiobjective optimization problem, they used nondominated sorting genetic algorithm (NSGA-II) and real-coded genetic algorithm (RGA) methods. Similarly, Yang et al [12] made an effort on an aerodynamic shape optimization approach to modify the canards and tailfins of a guided missile by aiming to maximize the range. For this purpose, he interlinked the real-coded adaptive range genetic algorithm method with trajectory analysis.…”

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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“…After unfolding a set of lifting surfaces, the projectile starts a subsonic gliding stage, where the ammunition spins and is fin-stabilized up to target. To improve the capability of the ammunition, an optimization process (Yang et al , 2012; Fowler and Rogers, 2015) has to be conducted on the whole geometry. In conceptual design stages, this process should be rapidly performed thanks to aerodynamic database, by means of a parametric study (Silton and Fresconi, 2014, 2015).…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic prediction of a projectile fitted with fins

Decrocq

Martinez

Albisser

et al. 2018

HFF

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Purpose The present paper deals with weapon aerodynamics and aims to describe preliminary studies that were conducted for developing the next generation of long-range guided ammunition. Over history, ballistic research scientists were constantly investigating new artillery systems capable of overcoming limitations of range, accuracy and manoeuvrability. While futuristic technologies are increasingly under development, numerous issues concerning current powdered systems still need to be addressed. In this context, the present work deals with the design and the optimization of a new concept of long-range projectile with regard to multidisciplinary fields, including flight scenario, steering strategy, mechanical actuators or size of payload. Design/methodology/approach Investigations are conducted for configurations that combine existing full calibre 155 mm guided artillery shell with a set of lifting surfaces. As the capability of the ammunition highly depends on lifting surfaces in terms of number, shape or position, a parametric study has to be conducted for determining the best aerodynamic architecture. To speed-up this process, initial estimations are conducted thanks to low computational cost methods suitable for preliminary design requirements, in terms of time, accuracy and flexibility. The WASP code (Wing-Aerodynamic-eStimation-for-Projectiles) has been developed for rapidly predicting aerodynamic coefficients (static and dynamic) of a set of lifting surfaces fitted on a projectile fuselage, as a function of geometry and flight conditions, up to transonic velocities. Findings In the present study, WASP predictions at Mach 0.7 of both normal force and pitching moment coefficients are assessed for two configurations. Originality/value Analysis is conducted by gathering results from WASP, computational-fluid-dynamics (CFD) simulations, wind-tunnel experiments and free-flight tests. Obtained results demonstrate the ability of WASP code to be used for preliminary design steps.

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Aerodynamic Shape Optimization System of a Canard-Controlled Missile Using Trajectory-Dependent Aerodynamic Coefficients

Cited by 16 publications

References 10 publications

Balistik Mühimmat Menzillerinin Hızlandırıcı Fırlatıcı Konsepti Kullanılarak Uzatılmasının Analizi

Balistik Mühimmat Menzillerinin Hızlandırıcı Fırlatıcı Konsepti Kullanılarak Uzatılmasının Analizi

Aerodynamic Shape Optimization of a Missile Using a Multiobjective Genetic Algorithm

Aerodynamic prediction of a projectile fitted with fins

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