Roll reversal phenomenon control in flight vehicles

Mirzaei, Mojtaba

doi:10.1016/j.ast.2018.05.059

Cited by 2 publications

(2 citation statements)

References 33 publications

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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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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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show abstract

“…This effect between the canards and the fins is called rolling coupling effect, which will considerably reduce and even eliminate the rolling-control efficiency of the canards. 6 Lesieutre pointed out in 1987 that the canard-controlled missiles at low angles of attack with roll-or yaw-control fin deflections have an induced roll moment on the tail fins. 7 In 1988, using the MISSILE 3 engineering prediction method and Missile Datcom (program), respectively, Lesieutre 8 and Blake 9 predicted the induced roll and analyzed the vortex influence on the canard controlled missile.…”

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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Roll reversal phenomenon control in flight vehicles

Cited by 2 publications

References 33 publications

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

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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