Numerical study on the aerodynamic coupling effects of spinning and coning motions for a finned vehicle

Liu, Tingting; Wu, Xiaojiang; Lei, Juanmian; Yin, Jintao

doi:10.1016/j.ast.2018.03.027

Cited by 7 publications

(2 citation statements)

References 3 publications

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“…Aerodynamic characteristics of the projectile with the tail free rolling. To investigate the cause of aerodynamic characteristics difference between the free-spinning tail projectile and the fixed tail projectile, the transient aerodynamic force and moment of the spinning projectile are estimated using equations ( 9) and ( 10), as follows 36,37 :…”

Section: Study Of the Free-spinning Tail Projectile's Aerodynamic Characteristicsmentioning

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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Section: Study Of the Free-spinning Tail Projectile's Aerodynamic Characteristicsmentioning

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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“…The aerodynamic and structural characteristics were respectively obtained by the Euler equation and the modal superposition method. Other numerical studies have predominantly explored the influence of aeroelasticity on the flight and control performance of projectiles [19][20][21][22][23][24][25][26]. In summary, previous investigations have encountered challenges in conducting two-way fluid-structure interaction calculations due to the intricate nature of the dynamic processes involved in spinning projectiles.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Response of Spinning Projectiles with Large Slenderness Ratio at Supersonic Speed

Liu

Lei

et al. 2023

Aerospace

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Obvious aeroelastic deformation occurs in spinning projectiles with large slenderness ratio, which seriously affects flight stability and maneuverability. This paper investigates the aeroelastic response of spinning projectiles with large slenderness ratio under supersonic speed. Based on a dynamic mesh method, an unsteady numerical simulation method is developed to study the aeroelasticity of spinning projectiles by coupling aerodynamics and structural dynamics. The numerical simulation method is well validated by the experimental results of AGARD 445.6 wing flutter. Then, the aeroelastic response of spinning projectiles with large slenderness ratio is numerically explored under different flight conditions. The aeroelastic response is obtained, revealing the presence of beat vibrations and variations in response frequency. Furthermore, the influence mechanism of flight conditions on the aeroelastic response is analyzed. The results suggest that the coupling of the first two modes of the projectile caused by the spinning motion leads to the occurrence of beat vibrations in the aeroelastic response; the coupling degree of the first two modes decreases as the angle of attack increases and it increases with the increase in spinning speed; and the time−averaged deformation caused by the time−averaged aerodynamic force is beneficial to the convergence of the aeroelastic response of spinning projectiles, while the rotation−induced Magnus effect is counterproductive.

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Parameters estimation methodology for the nonlinear rolling motion of finned cylindrical body

Abadir

Yusuf

Pontillo

et al. 2019

Aerospace Science and Technology

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Numerical study on the aerodynamic coupling effects of spinning and coning motions for a finned vehicle

Cited by 7 publications

References 3 publications

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

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

Aeroelastic Response of Spinning Projectiles with Large Slenderness Ratio at Supersonic Speed

Parameters estimation methodology for the nonlinear rolling motion of finned cylindrical body

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