ANALYSIS OF AERODYNAMIC CHARACTERISTICS FOR CANARD CONTROLLED MISSILE WITH FREE-ROTATING TAIL

Y. Kim; K.T. Kang

doi:10.6112/kscfe.2025.30.1.082

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Original Article

ANALYSIS OF AERODYNAMIC CHARACTERISTICS FOR CANARD CONTROLLED MISSILE WITH FREE-ROTATING TAIL 자유 회전 꼬리날개가 적용된 카나드 제어 유도탄의 공력 특성 분석

31 March 2025. pp. 82-94

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Abstract

Free-rotating tail fins have been widely employed in canard controlled guided missiles to mitigate unintended canard-induced moments reducing control effort. However, aerodynamic characteristics of free-rotating tail remain not fully understood due to complex interaction with the missile body and canard control surfaces. This study investigates the fundamental aerodynamic characteristics of free-rotating tail through wind tunnel experiments and CFD analysis of a canard controlled missile with fixed tail and free-rotating tail. CFD simulations are conducted at Mach numbers 1.2, 1.6 and 3.0 using RANS models for fixed tail(x-tail and +-tail) and URANS with a sliding mesh approach for free-rotating tail. The aerodynamic coefficients of CFD results show good agreement with those of wind tunnel measurements. Based on the results, the fundamental aerodynamic characteristics of missiles with free-rotating tail are characterized, and an efficient aerodynamic evaluation approach is discussed.

Keywords

Canard controlled missile

Free-rotating tail

Missile aerodynamics

Computational fluid dynamics

Reynolds averaged Navier-Stokes

Unsteady Reynolds averaged Navier-Stokes

키워드

카나드 제어 유도탄

자유 회전 꼬리날개

유도탄 공력

전산유체역학

RANS

URANS

References

1976, Burt, J.R., Jr., "The Effectiveness of Canards for Roll Control," U.S. Army Missile Command Technical Report RD-77-8.

1978, Blair, A.B., Jr., "Wind-Tunnel Investigation at Supersonic Speeds of a Canard-Controlled Missile With Fixed and Free-Rolling Tail Fins," NASA TP 1316.

1985, Blair, A. B.,Jr., "Wind-Tunnel Investigation at Supersonic Speeds of a Remote-Controlled Canard Missile With Fixed and Free-Rolling Tail Brake Torque System," NASA TP 2401.

2002, Lesieutre, D.J., Love, J.F. and Dillenius, M.F., "Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-Control and Rolling-Tail Missiles ," AIAA 2002-4511.

10.2514/6.2002-4511

2003, Murman, S.M. and Aftosmis, M.J., "Cartesian-Grid Simulations of a Canard-Controlled Missile with a Spinning Tail," AIAA-2003-3670.

10.2514/6.2003-367014557565

2020, Zhang, J., Lei, J. and Niu, J., "Numerical Investigation of Aerodynamic Characteristics of Free-Spinning Tail Projectile, with Canards Roll Control," J. Aerosp. Eng., Vol.235, No.6, pp.687-702.

10.1177/0954410020953316

2013, Lee, J.K., Cho, C.Y. and Lee, D.K., "Rotational Characteristics of a Model with Free-to-Roll Tail Fins at Supersonic Wind Tunnel Testing," 2013 KSAS Spring Conference, Jeju, Korea.

2014, Lee, E., Kang, K.T. and Lee, K.S., "Prediction of Rotation Rate of Free-Rolling Tail Using CFD," Proceeding of ACFD10, Jeju, Korea.

2020, STAR-CCM+ 15.06, User Guide.

Information

Publisher :Korean Society for Computational Fluids Engineering
Publisher(Ko) :한국전산유체공학회
Journal Title :Journal of Computational Fluids Engineering
Journal Title(Ko) :한국전산유체공학회지
Volume : 30
No :1
Pages :82-94
Received Date : 2025-02-26
Revised Date : 2025-03-24
Accepted Date : 2025-03-25
DOI :https://doi.org/10.6112/kscfe.2025.30.1.082

Journal of Computational Fluids Engineering ISSN:1598-6071(Print) 3022-6252(Online) 한국전산유체공학회지

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