Aerodynamic–structural missile fin optimization

Vidanović, Nenad; Rašuo, Boško; Kastratović, Gordana; Maksimović, Stevan; Ćurčić, Dušan; Samardžić, Marija

doi:10.1016/j.ast.2017.02.010

Cited by 36 publications

(33 citation statements)

References 58 publications

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“…The missile taken to carry out this study was a standard AGARD-B model of slender, four-fin, blunt-nose configuration whose geometry was taken from [1]. The blunt nose was chosen for the missile so as to make the configuration of the missile aerodynamically efficient by minimizing the shock waves generated at the nose-tip by transferring the kinetic energy generated, to the atmosphere, thus reducing the frictional effects and on the missile body.…”

Section: Methodsmentioning

confidence: 99%

“…The missile [1] was modelled in Spaceclaim using basic sketching tools with a length (L) of 763.7mm. The creation of the domain was done to analyze the nature of the flow specifically around the missile model and within the domain so as to obtain more accurate results.…”

Section: Modelingmentioning

confidence: 99%

“…Boundary conditions were set for the pressure far field with respect to the pressure, which was set to be the ambient pressure at an altitude of 10200m as mentioned in the reference paper [1]. Mach number was set as a constant parameter throughout the analysis at all the angles of attack with a value of 2.5.…”

Section: Flow Setupmentioning

confidence: 99%

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Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Gaonkar¹,

Menon²,

Srinivas

2019

ujme

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Missile is a self-propelled vehicle flying at supersonic speeds. Their payloads are usually explosive and are also known as warheads. These warheads are used to destroy a pre-set target. The aim of this paper is to optimize the values of the lift and drag forces on the given missile for better aerodynamic performance, by carrying out numerical simulations over the supersonic missile by varying the angle of attack through a set of suitable boundary conditions, while keeping the Mach number of the missile as a fixed parameter. Aerodynamic performance of the missile is studied by varying the angle of attack from 0 to 12 degrees. For every angle of attack, the coefficient of lift and coefficient of drag variations were studied in detail and were compared with the existing literature survey so as to obtain the maximum value of C L /C D ratio in order to improve the efficiency. A model of the missile was designed to-scale on Space Claim and the flow analysis was done on FLUENT standalone system using ANSYS 16 workbench. The results obtained, were in the form of flow contours of parameters such as velocity, temperature, density, pressure and turbulence. Through these flow contours the maximum and minimum values of all parameters, as well as the variation in these parameters were estimated. From the numerical analysis it was found that maximum value of C L /C D ratio was 2.5 at 12 o angle of attack. It was also found that the velocity increased with increase in angle of attack and increased the efficiency. These results are advantageous upcoming to designers who aim to build aerodynamically efficient missiles.

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Section: Methodsmentioning

confidence: 99%

Section: Modelingmentioning

confidence: 99%

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Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Gaonkar¹,

Menon²,

Srinivas

2019

ujme

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“…Journal homepage: https://content.sciendo.com Today's computer-aided design techniques have many successful integrations of CAD-CAE and optimization tools to implement industrial product design systems [25]- [28]. These design applications were developed to facilitate the structural optimization in the different discipline fields with basically identical concepts and, therefore, designers have benefited more from them.…”

Section: Introductionmentioning

confidence: 99%

Automatic Strain Gauge Balance Design Optimization Approach and Implementation Based on Integration of Software

Xiang

et al. 2020

Measurement Science Review

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The traditional wind tunnel strain balance design cycle is a manual iterative process. With the experience and intuition of the designer, one solution that meets the design requirements can be selected among a small number of design solutions. This paper introduces a novel software integration-based automatic balance design optimization system (ABDOS) and its implementation by integrating professional design knowledge and experience, stepwise optimization strategy, CAD-CAE software, self-developed scripts and tools. The proposed two-step optimization strategy includes the analytical design process (ADP) and the finite element method design process (FEDP). The built-in optimization algorithm drives the design variables change and searches for the optimal structure combination meeting the design objectives. The client-server based network architecture enables local lightweight design input, task management, and result output. The highperformance server combines all design resources to perform all the solution calculations. The development of more than 10 balances that have been completed and a case study show that this method and platform significantly reduce the time for design evaluation and designanalysis-redesign cycles, assisting designers to comprehensively evaluate and improve the performance of the balance.

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“…Furthermore, topology optimization is frequently employed to determine the optimum location of certain structural components under static and aeroelastic loads [8,9]. Additionally, a lot of work has been accomplished for the solution of local structural problems, e.g., buckling issues or lay-up optimization [10][11][12][13][14][15][16][17], aeroelasticity, flutter [18], local optimization of panels or areas with cut-outs [19][20][21] for obtaining lighter designs. The aforementioned studies refer to a 2-spar arrangement only and to some specific structural problems, while the advantages that can be obtained by accommodating additional spar (more than two) in the wingbox as well as the design methodology that has to be followed is not exhaustively covered.…”

Section: Introductionmentioning

confidence: 99%

Towards the Design of a Multispar Composite Wing

Stamatelos

Labeas

2020

Computation

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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.

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Aerodynamic–structural missile fin optimization

Cited by 36 publications

References 58 publications

Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Automatic Strain Gauge Balance Design Optimization Approach and Implementation Based on Integration of Software

Towards the Design of a Multispar Composite Wing

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