Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating

Vidanović, Nenad; Rašuo, Boško; Kastratović, Gordana; Grbović, Aleksandar; Puharić, Mirjana; Maksimović, Katarina

doi:10.2514/1.a34575

Cited by 17 publications

(9 citation statements)

References 59 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…MDO problem of the missiles should be essentially defined as a multi-objective as well as a highly multi-point study. The present study observes two similar formulations of the optimization problem (ftsi_o and ftsi*_o case studies), which resulted in a significant difference between achieved results regarding objectives [4]. This dually defined optimization problem represents a searching routine for the best possible aerodynamic shape of the fin structure.…”

Section: Methodsmentioning

confidence: 66%

“…The proposed multi-disciplinary feasible method represents a single-level method driven by an embedded multi-objective genetic algorithm supported by surrogate modeling techniques [1][2][3][4]. Established optimization framework improves overall design processes and ensures significantly improved missile structure, where safety and reliability in extreme flight phases are satisfied.…”

Section: Introductionmentioning

confidence: 99%

“…Ballistic missile model with initial (dashed line), fsi_o (solid line), ftsi_o (dotted line) and ftsi*_o (dash-dot line) optimized fin shapes for overall multi-point study[4].…”

mentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic‐thermal/structural design optimization of missile fin configuration during supersonic flight condition

Rašuo

Vidanović

Kastratović

et al. 2021

Proc Appl Math and Mech

Self Cite

View full text Add to dashboard Cite

The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multi-modular numerical environment developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimisation (MDO) purposes, in a manner that thermally induced structural responses in a current study are taken into consideration. The present study concerns with a broader observation of critical multi-point flight conditions and represents a more realistic scenario which presents one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modelling and optimisation. This means that thermo-mechanical effects of the missile fin structure are observed and implemented into established numerical environment. Numerical modelling of FSI/FTSI and MDO within an industry-accepted design tool was resulted in powerful monolithic environment which with adopted multi-point regimes and multi-criteria settings is used for aerodynamic-thermal/structural optimisation. The multidisciplinary shape optimisation, with respect to predefined objectives and constrains, was carried out in order to achieve global improvement of missile initial aerodynamic and to prevent aerothermally-induced critical responses of the fin configuration.

show abstract

Section: Methodsmentioning

confidence: 66%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic‐thermal/structural design optimization of missile fin configuration during supersonic flight condition

Rašuo

Vidanović

Kastratović

et al. 2021

Proc Appl Math and Mech

Self Cite

View full text Add to dashboard Cite

show abstract

“…Many researchers applied a variety of optimization methods to improve the performance of systems with a different degree of complexity and belonging to different domains [25-28] using appropriate analytical and numerical tools [29]. The defined multiobjective optimization task ( 27) is considered as a mixed variable nonlinear constrained optimization problem containing 5 continuous and 2 discrete variables.…”

Section: Numerical Experiments and Discussionmentioning

confidence: 99%

Multicriteria optimal selection of a hydraulic cylinder for drive mechanisms

Mitrev¹,

Todorov²

2021

FME Transactions

View full text Add to dashboard Cite

The paper reports the optimization synthesis of a hydraulically actuated drive mechanism. A mathematical model of the mechanism using vector closure equations is developed. Based on the functional purpose of the mechanism, a set of geometric and force/moment requirements are defined which must be met by a proper selection of a standardized hydraulic cylinder and its points of attachment. A multiobjective design optimization task is defined with three objective functions whose minimum is searched - the mass of the hydraulic cylinder, the squared total deviation of the developed by the hydraulic cylinder moments from the predefined values of the external moments and the force in the hydraulic cylinder. The defined multiobjective optimization task is considered as a mixed variable nonlinear constrained optimization problem containing 5 continuous and 2 discrete variables and the multistage Monte Carlo method is used for its solution. Using different weighting schemes several Pareto-optimal compromise solutions are obtained.

show abstract

“…The composite laminates due to their high specific strength and stiffness are increasingly used in weight-sensitive applications such as aircraft and space vehicles [1][2][3]. Most of these vehicles have to operate in hostile thermal environments; as a result, the structural components of these vehicles are subjected to thermal loads [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Buckling and postbuckling behavior of shell type structures under thermo mechanical loads

Vasic

Maksimović²,

Maksimović³

et al. 2021

THERM SCI

View full text Add to dashboard Cite

The thermomechanical buckling and postbuckling behavior of layered composite shell type structure are considered with the finite element method (FEM) under the combination of temperature load and applied mechanical loads. To account for through-thickness shear deformation effects, the thermal elastic, Higher-Order Shear deformation Theory (HOST) is used in this study. The refined higher order theories, that takes into account the effect of transverse normal deformation, is used to develop discrete finite element models for the thermal buckling analysis of composite laminates. Attention in this study is focused on analyzing the temperature effects on buckling and postbuckling behavior of thin shell structural components. Special attention in this paper is focused on studying of values of the hole in curved panel on thermal buckling behavior and consequently to expend and upgrade previously conducted investigation. Using FEM, a broader observation of the critical temperature of loss of stability depending on the size of the hole was conducted. The presented numerical results based on HOST can be used as versatile and accurate method for buckling and postbuckling analyzes of thin-walled laminated plates under thermo-mechanical loads.

show abstract

Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating

Cited by 17 publications

References 59 publications

Aerodynamic‐thermal/structural design optimization of missile fin configuration during supersonic flight condition

Aerodynamic‐thermal/structural design optimization of missile fin configuration during supersonic flight condition

Multicriteria optimal selection of a hydraulic cylinder for drive mechanisms

Buckling and postbuckling behavior of shell type structures under thermo mechanical loads

Contact Info

Product

Resources

About