The Effect of Tail Fin Parameters on the Induced Roll of a Canard-Controlled Missile

McDaniel, Melissa; Evans, Christine; Arsenal, Redstone; Lesieutre, Dan J.

doi:10.2514/6.2010-4226

Cited by 26 publications

(6 citation statements)

References 4 publications

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“…6-9) and the Missile Distributed Loads (MISDL) codes (Refs. [10][11][12][13][14][15][16]. These were developed by NEAR and have been validated with flight data for numerous applications.…”

Section: Aerodynamic Prediction Methodsmentioning

confidence: 99%

Trailing Vortex-Induced Loads During Close Encounters in Cruise

Mendenhall

Lesieutre

Kelly

2015

33rd AIAA Applied Aerodynamics Conference

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“…6-9) and the Missile Distributed Loads (MISDL) codes (Refs. [10][11][12][13][14][15][16]. These were developed by NEAR and have been validated with flight data for numerous applications.…”

Section: Aerodynamic Prediction Methodsmentioning

confidence: 99%

Trailing Vortex-Induced Loads During Close Encounters in Cruise

Mendenhall

Lesieutre

Kelly

2015

33rd AIAA Applied Aerodynamics Conference

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“…The second method is to amend the geometric parameters or aerodynamic shapes of the fins. Most decoupling designs of changing geometric parameters are to decrease the fin span (Blair et al, 1983;McDaniel et al, 2010), while this measure would reduce the lifting characteristics and static stability of the missile. Some special shapes of the fin are designed to reduce the reverse rolling moment, such as the ring fin (Burt, 1976) and the grid fin (Spirito et al, 2003).…”

Section: Introductionmentioning

confidence: 99%

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

Zhang

Lei

Yin³

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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When the canard-controlled missile is conducting roll control, the asymmetric downwash induced by the canard impacts on the fins and produces a reverse rolling moment, resulting in the aerodynamic coupling between the canards and the fins. The rolling coupling can cause the reduction and even failure of the missile roll control. However, the current rolling decoupling methods always have adverse effects on the lift-drag ratio or flight stability of the missile. Based on the numerical simulation, this paper proposes a new method to reduce the roll coupling by adding a jet system between the canards and the fins. The effect of jet control was obtained under different freestream conditions. The influence of jet control factors on the missile aerodynamic characteristics was investigated and analyzed. The outcomes demonstrate that the jet control can effectively decrease the roll coupling between the canards and the fins, and eliminate the reverse rolling problem in most cases. With the same mass flow rate, the control effect is better at lower Mach number. Jet location and jet mode have a higher influence on the control effect. An optimal mass flow rate exists for the best control efficiency. This decoupling method is simple in structure and can reduce the side force and yawing moment without destroying the lift-drag ratio.

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“…10 In 2010, McDaniel investigated the parameters of the tail fin that affect the rolling moment properties. 11 Silton undertook the study of the impact of the canard trailing vortex flow interactions on the aerodynamic performance of a body-fin-canard projectile. [12][13][14] The loss of rollcontrol authority with combined pitch and roll deflections was investigated by Lesieutre in 2017 for a canard-controlled projectile at transonic speed.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of aerodynamic characteristics of free-spinning tail projectile with canards roll control

Jiawei

Lei

Niu

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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To reduce aerodynamic coupling between the canards and the tail fins of a canard-controlled projectile, the afterbody of the projectile is decoupled from the forebody by a bearing structure, namely, a free-spinning tail. A series of numerical simulations was conducted for different angles of attack using NASA’s canard-controlled projectile with a free-spinning tail. The results were then compared with the wind tunnel test data. The spin rate of the free-spinning tail shows that, with the canard roll control, the tail section will rotate at lower angles of attack and “lock-in” at higher ones, demonstrating nonlinearization between the rotating rate and the angle of attack. According to a flow structure analysis, the circular flow velocity induced by canards is responsible for the non-linear characteristics of the tail. Moreover, the change in position of the circular flow velocity results in a reverse of the rolling moment of the “+” fixed tail projectile at different angles of attack. Furthermore, a comparison of the aerodynamic characteristics of the fixed (“+” and “x”) and free-spinning tail configurations proves that when the tail is spinning, all the aerodynamic coefficients of the free-spinning tail projectile are between those of the “+” and “x” fixed tail projectiles. The longitudinal difference in aerodynamic characteristics is related to the rolling angle, whereas the lateral difference is related to both the rolling angle and rotation rate. When the tail section “locks-in,” different rolling angles lead to different characteristics in both the longitudinal and lateral directions.

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The Effect of Tail Fin Parameters on the Induced Roll of a Canard-Controlled Missile

Cited by 26 publications

References 4 publications

Trailing Vortex-Induced Loads During Close Encounters in Cruise

Trailing Vortex-Induced Loads During Close Encounters in Cruise

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

Numerical investigation of aerodynamic characteristics of free-spinning tail projectile with canards roll control

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