CFD Analysis of a Supersonic Projectile with Deflectable Nose Control

Shoesmith, Benjamin; Birch, Trevor; Mifsud, Michael; Meunier, Mikael; Shaw, Scott

doi:10.2514/6.2006-3200

Cited by 28 publications

(4 citation statements)

References 7 publications

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“…In recent years, many different active control mechanisms for guided projectiles have been investigated, including moveable canards and other lifting surface appendages [1][2][3], deployable pins [4,5], gas jet or explosive thrusters [6][7][8], and translation or rotation of internal components [9]. Although each of these devices are capable of altering the projectile trajectory in some desired manner, this paper focuses on the microspoiler mechanism for high-speed finned projectiles previously investigated by Dykes et al [10].…”

Section: Nomenclature C Lpmentioning

confidence: 99%

Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Scheuermann¹,

Costello²,

Silton³

et al. 2015

Journal of Spacecraft and Rockets

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Section: Nomenclature C Lpmentioning

confidence: 99%

Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Scheuermann¹,

Costello²,

Silton³

et al. 2015

Journal of Spacecraft and Rockets

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“…At higher angle of attack, the general trends are similar; there is a large increase in load over the forebody surface that can be scaled with the magnitude of the nose deflection. Downstream of the nose-body junction, the expansion of flow on the windward side leads to a region of reduced loading compared to that of the baseline configuration (Shoesmith and Birch, 2006).…”

Section: Resultsmentioning

confidence: 99%

“…This is followed by a region where the loading is approximately zero and finally negative loading on the tail section as a result of the downwash is generated over the fins by the fore-body. It can clearly be seen that for the higher angle of attack case, a low-pressure region is formed just downstream of the nose-body junction as a result of the flow expanding around the corner created by the nose deflection (Shoesmith and Birch, 2006).…”

Section: Resultsmentioning

confidence: 99%

Aerodynamic performance improvement of a canard control missile

Tahani

Masdari

Kazemi

2017

AEAT

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Purpose This paper aims to analyze the influence of the changings in geometrical parameters on the aerodynamic performance of the control canard projectiles. Design/methodology/approach Because of the mentioned point, the range of projectiles increment has a considerable importance, and the design algorithm of a control canard projectile was first written. Then, were studied the effects of canard geometric parameters such as aspect ratio, taper ratio and deflectable nose on lift to drag coefficient ratio, static margin based on the slender body theory and cross section flow. Findings The code results show that aspect ratio increment, results in an increase in lift-to-drag ratio of the missile, but increase in canard taper ratio results in increasing of lift-to-drag ratio at 1° angle of attack, while during increasing the canard taper ratio up to 0.67 at 4° angle of attack, lift to drag first reaches to maximum and then decreases. Also, static margin decreases with canard taper ratio and aspect ratio increment. The developed results for this type of missile were compared with same experimental and computational fluid dynamic (CFD) results and appreciated agreement with other results at angles of attack between 0° and 6°. Practical implications To design a control canard missile, the effect of each geometric parameter of canard needs to be estimated. For this purpose, the suitable algorithm is used. In this paper, the effects of canard geometric parameters, such as aspect ratio, taper ratio and deflectable nose on lift-to-drag coefficient ratio and static margin, were studied with help of the slender body theory and cross-section flow. Originality/value The contribution of this paper is to predict the aerodynamic characteristics for the control canard missile. In this study, the effect of the design parameter on aerodynamic characteristics can be estimated, and the effect of geometrical characteristics has been analyzed with a suitable algorithm. Also, the best lift-to-drag coefficient for the NASA Tandem Control Missile at Mach 1.75 was selected at various angles of attack. The developed results for this type of missile were compared with same experimental and CFD results.

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“…Military equipment development is moving towards systematization, informatization and intelligence. The defense science and technology research is focusing on developing smart munitions, which can identify selected target and make trajectory correction intelligently through using simple guided method and trajectory self-adaptive [1][2][3][4][5][6]. Nose deflection is a new missile steering method [7,8].…”

Section: Introductionmentioning

confidence: 99%

Design and Research of Wind Tunnel Test for Deflectable Nose

Zhang

Wang

Cao

et al. 2013

AMM

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A wind tunnel test is designed to study aerodynamic effects of one individual rocket with deflectable nose. The test measures pressure with U-bend tube which is cost effective. Using rubber tubes in different lengths to measure pressure distributions of a flat-plate, and calculating how rubber tube affects the measurement, in order to modify the measured surface pressure of the nose. The surface pressure varies on different points while yawing angle and attack angle changes, the changing regularity could provide data for following numerical simulation and trajectory control.

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CFD Analysis of a Supersonic Projectile with Deflectable Nose Control

Cited by 28 publications

References 7 publications

Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Aerodynamic performance improvement of a canard control missile

Design and Research of Wind Tunnel Test for Deflectable Nose

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