Movement Characteristics of a Dual-Spin Guided Projectile Subjected to a Lateral Impulse

Yang, Zhiwei; Wang, Liangming; Chen, Jianwei

doi:10.3390/aerospace8100309

Cited by 3 publications

(2 citation statements)

References 24 publications

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“…Te diferential equations for the rocket projectile rotation around the center of mass [28][29][30] are as follows:…”

Section: Dynamic Modelling Of Rocket Projectile With Isolated Rotatin...mentioning

confidence: 99%

“…As the projectile is under the action of gravity, the height defection angles of the projectile velocity bend downward, which results in a changed attack angle. Equation (29) describes this change, and the results are shown in Figures 6 and 7, and the initial conditions are δ 10 � δ 20 � 0, v 0 � 280m/s, and θ a0 � 0.07πrad.…”

Section: Stability Of Projectile Caused By Gravitymentioning

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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“…Te diferential equations for the rocket projectile rotation around the center of mass [28][29][30] are as follows:…”

Section: Dynamic Modelling Of Rocket Projectile With Isolated Rotatin...mentioning

confidence: 99%

Section: Stability Of Projectile Caused By Gravitymentioning

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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Guidance and Control of a Spinning 155mm Artillery Shell

Rehman

Asghar²,

Abid

et al. 2022

2022 17th International Conference on Emerging Technologies (ICET)

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Adaptive Attitude Roll Control of Guided Projectile Based on a Novel Unidirectional Global Sliding Mode Algorithm

Guo,

Wang,

2024

Aerospace

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Aimed at addressing the strong nonlinearity and strong external disturbances that cause flight control issues in conventional guided projectiles, as well as the slow response and structural vibrations that often occur in sliding mode control systems, which have a detrimental impact on the control effect and ultimate hit precision, a new type of fast and robust control algorithm with a unidirectional mode has been designed. The objective is to design an optimized aerodynamic shape for the projectile and to establish a dynamic model of the roll channel and a motion model of the entire trajectory. The dynamics of a new global terminal sliding mode are proposed, and an adaptive parameter term is realized by calculating the state of the critical sliding mode surface, which ensures that the tracking error converges within a finite time. Its combination with an adaptive approaching law is used to further speed up convergence while damping the structural vibration of the system. The bias error of the roll angle is constructed as the controller and simulation calculations are conducted on the basis of the aforementioned framework. The stability and time convergence of the control system are demonstrated through Lyapunov theory. The results indicate that, in comparison to the conventional terminal sliding mode controller, the designed controller exhibits a markedly rapid convergence rate and stronger robustness in tracking the command signal. Moreover, it also maintains a stable motion attitude of the projectile throughout the entire process. The superior control effect under different guidance schemes and the strong external disturbances also further reflect the anti-jamming capability and tracking performance of the system.

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Movement Characteristics of a Dual-Spin Guided Projectile Subjected to a Lateral Impulse

Cited by 3 publications

References 24 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

Guidance and Control of a Spinning 155mm Artillery Shell

Adaptive Attitude Roll Control of Guided Projectile Based on a Novel Unidirectional Global Sliding Mode Algorithm

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