Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

Silton, Sidra I.; Fresconi, Frank

doi:10.2514/1.a33219

Cited by 21 publications

(6 citation statements)

References 21 publications

(37 reference statements)

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“…The numerical methods used for the investigated model geometry are validated in previous studies against wind-tunnel measurements for the spinning non-finned model (Klatt et al, 2013) as well as for the non-spinning finned model (Mielke et al, 2019(Mielke et al, , 2020. The simulation approach used in this work is already well established and documented in the literature (Bhagwandin, 2016;Cayzac et al, 2011;Cayzac et al, 2013;DeSpirito, 2008;Klatt et al, 2013;Klatt, 2015;Mielke et al, 2020;Pechier et al, 2001;Silton and Fresconi, 2015;Yin et al, 2017;Yin et al, 2018).…”

Section: Simulation Methodsmentioning

confidence: 96%

Magnus effect for roll-decoupled canards on a spinning body of revolution

Klatt

Mielke

Mundt

2020

HFF

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Purpose Spinning slender bodies are affected by lateral Magnus forces and moments when exposed to cross-flow. The effects occurring for spinning bodies of revolution in combination with stabilising or control surfaces such as canards are not yet fully explained. Therefore the present work aims to investigate the phenomena arising from the interactions of a roll-decoupled guidance unit with a spinning rear body are investigated. Design/methodology/approach A generic tangential-ogive-cylinder projectile equipped with deflectable canards on a roll-decoupled nose is investigated by means of 3D Reynolds-averaged Navier–Stokes simulations at Mach number 2 for angles of attack up to 22 degrees. Different canard deflection angles up to 9 degrees are considered. Global aerodynamic coefficients as well as local flow fields are analysed to explain the interactions occurring between the roll-decoupled guidance unit and the spinning rear body. Findings The deflected canards lead to flow interactions resulting in lateral forces and moments even without a spinning motion of the rear part. Depending on the canard deflection angles, these forces act in or against the direction of the classical Magnus effect. For angles of attack smaller than 10 degrees it is possible for the current body geometry to directly superpose the lateral effects resulting from the fins for the non-spinning model with those occurring for the non-finned but spinning model to obtain the total forces and moments acting on a spinning model with canted canards. However, the lateral effects generated on the guidance unit itself are insignificant compared to the canard-induced effects on the rear body. Originality/value A detailed analysis of the interaction effects arising from a decoupled guidance unit containing canards with a non-spinning/spinning rear body is performed and the underlying phenomena are revealed.

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Section: Simulation Methodsmentioning

confidence: 96%

Magnus effect for roll-decoupled canards on a spinning body of revolution

Klatt

Mielke

Mundt

2020

HFF

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“…This downwash induces a large and reverse rolling moment, which in some cases may even exceed the rolling moment produced by the canards and leading to a reverse rolling and control failure (Lesieutre et al, 1988). Therefore, studies on the aerodynamic coupling effect and decoupling measures between the canards and the fins are of great significance (Lesieutre, 2017;Mirzaei, 2018;Silton & Fresconi, 2015;Silton & Fresconi, 2015.…”

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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“…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. 15 One measure to reduce the coupling is via the freespinning tail 16 : mounting a bearing connecting the forebody and the afterbody of the projectile to enable the tail fin to rotate freely about the body axis.…”

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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Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

Cited by 21 publications

References 21 publications

Magnus effect for roll-decoupled canards on a spinning body of revolution

Magnus effect for roll-decoupled canards on a spinning body of revolution

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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