Research on Control Force Aerodynamic Model of a Guided Rocket With an Isolated-rotating Tail Rudder

Wang, Chen; Ding, Libo; Zhang, He; Li, Xiao; Zhang, Shihao

doi:10.1007/s42405-021-00414-7

Cited by 4 publications

(2 citation statements)

References 34 publications

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“…Research into the development of isolated rotating tail rudder rockets helps compensate for the shortcomings of unguided, man-portable, antiarmor weapons due to their low precision and short range while keeping costs low. Te caliber of the considered rocket is approximately 80 mm and is used primarily to strike fxed or low-speed moving targets within 2000 m. Te overall layout of the rocket is shown in Figure 1(a) [26]. Te device is composed of a seeker, projectile body, and tail segment.…”

Section: Periodic Control Force Principle Of Isolated Rotating Tail R...mentioning

confidence: 99%

“…where c x , c y , c z , m z , m zz , m xz 1 , m xz 2 , and m y represent the drag coefcient, lift coefcient, Magnus force coefcient, static moment coefcient, equatorial damping moment coefcient, projectile body pole damping moment coefcient, tail pole damping moment coefcient, and tail Magnus moment coefcient, respectively, and ρ, S, l, and d represent the air density, characteristic area, reference length, and projectile diameter, respectively. For small caliber rocket projectiles, the order of magnitude for each parameter at small angles of attack and subsonic velocities is shown in Table 1 [26].…”

Section: Diferential Equation Of Projectile Body Angular Motionmentioning

confidence: 99%

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Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Wang

Ding

Feng

et al. 2023

Mathematical Problems in Engineering

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A trajectory-corrected rocket projectile with an isolated rotating tail rudder provides a new concept for a low-cost trajectory correction and guidance due to its simplified guidance principle. To study the angular motion characteristics of a trajectory-corrected rocket projectile with an isolated rotating tail rudder under the action of a periodic control force, the angular motion differential equation described in the complex plane is derived based on the rigid body trajectory equation. Furthermore, the effects of the initial conditions, gravity, and an asymmetric tail on the flight stability of the projectile in an uncorrected trajectory state are studied. The critical rotational speed of the tail rudder, which makes the projectile unstable due to the Magnus moment, and the rotational speed of the tail rudder, which causes projectile resonance, are derived. The transient and steady-state solutions of the angular motion of the projectile under trajectory correction and the variation law of the velocity direction for the projectile centroid are obtained. Finally, an example is given to verify the conclusions of this study. This research has important guiding significance for trajectory analysis, guidance control, and guidance law designs for isolated rotating rudder trajectory-corrected rocket projectiles.

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Section: Periodic Control Force Principle Of Isolated Rotating Tail R...mentioning

confidence: 99%

Section: Diferential Equation Of Projectile Body Angular Motionmentioning

confidence: 99%

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Wang

Ding

Feng

et al. 2023

Mathematical Problems in Engineering

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Magnus Effect over Aerodynamic Components of Spinning Missile

Gao

Lei

Yin

2022

Int. J. Aeronaut. Space Sci.

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To reveal the flow mechanism of the Magnus effect of the spinning missile, the flow field under supersonic conditions was numerically simulated based on the unsteady Reynolds-time-averaged Navier–Stokes equation, and the implicit dual-time stepping method and sliding mesh method were used. Validation was performed to ensure the reliability of the numerical methods. The results of the numerical simulation and the wind-tunnel experimental data coincided quite well. The aerodynamic characteristics of various configurations while spinning were calculated. The effect of aerodynamic components and aerodynamic interference between components on the Magnus effect were analyzed. The results indicate that for the projectile body, the interference of the canard enlarges the time-averaged side force; when the slenderness ratio becomes large, from the view of the base, the left leeward separation vortex is close to the surface, resulting in a low-pressure region, and the direction of the side force and yawing moment are changed. The fin installation angle can weaken the body Magnus effect to some extent. For the projectile fin, the influence of leeward separation vortices on the fin depends on their relative positions. The fin installation angle can weaken and even cause the reversal of the side force direction.

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Coupled Kernel Extreme Learning Machine and Cuckoo Search for Aerodynamic Modeling and Stability Analysis of Spinning Projectiles

Liu,

Lei

2024

Int. J. Aeronaut. Space Sci.

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Research on Control Force Aerodynamic Model of a Guided Rocket With an Isolated-rotating Tail Rudder

Cited by 4 publications

References 34 publications

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Magnus Effect over Aerodynamic Components of Spinning Missile

Coupled Kernel Extreme Learning Machine and Cuckoo Search for Aerodynamic Modeling and Stability Analysis of Spinning Projectiles

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