Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Wang, Yuchen; Wang, Wei; Ji, Yi; Zhang, Jian; Wang, Xiaokang

doi:10.1002/asjc.2907

Cited by 2 publications

(1 citation statement)

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“…3 supplemented the stability study of rolling missiles with the attitude autopilot, and verified the stability boundary through numerical simulations. Wang et al 4 analyzed the uncertainty from cross-coupling effect of rolling missiles with the angle-of-attack (AOA) feedback autopilot which are controlled by aerodynamic force, and put forward a decoupling method to strengthen the coning motion stability. On the basis of AOA feedback three-loop autopilot, parasitic effect caused by radar radome slope were taken into account through mathematical derivation and numerical simulations in Ref.…”

Section: Introductionmentioning

confidence: 99%

Research on dynamic stability of rolling missiles employing direct/aerodynamic force compound control

Bai,

Lin,

Zheng

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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The direct/aerodynamic force compound control can enhance the maneuverability and response characteristics of missiles, and the dynamic stabilization is the precondition of normal operation for rolling missiles. Aiming at the stability problem caused by the cross-coupling effect of rolling missiles employing direct/aerodynamic force compound control, proposing a typical topological control system structure described by the complex coefficient theory, and deducing the dynamic stability conditions. Firstly, the mathematic model is established based on the kinematics and dynamics theories of rotating airframes and the direct/aerodynamic force compound control mechanism. Then, a three-loop autopilot and the direct/aerodynamic force ratio distribution method are designed to establish the complex summation model of the compound control system by selecting suitable complex variables. Furthermore, deducing the dynamic stability conditions and verifying them by numerical simulations. Finally, the stable regions of the rolling missile in different cases are obtained and found to be influenced by many factors, such as parameters of the autopilot, hybrid force distribution proportion and rolling rate. The derived dynamic stability criterion is effective for evaluating the stability of rolling missiles employing direct/aerodynamic force compound control and the research method used in this paper can provide reference for the stability study of strongly coupled nonlinear systems.

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Section: Introductionmentioning

confidence: 99%

Research on dynamic stability of rolling missiles employing direct/aerodynamic force compound control

Bai,

Lin,

Zheng

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

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Research and Flight Test on the Terminal Guidance Control Technology for Cruising Unmanned Aerial Vehicles

Cai,

Yang,

Guo

et al. 2024

Aerospace

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The Cruising Unmanned Aerial Vehicle (CUAV) exemplifies an advanced system integrating UAV and munitions technology. The primary challenge lies in devising strategies to achieve precision strikes. Achieving precision strikes is a critical combat mission for CUAV and serves as the primary focus of this research. This paper introduces a three-loop pseudo-angle-of-attack acceleration autopilot design with proportional–integral (PI) correction, overcoming the limitations of existing two-loop and three-loop systems. The existing two-loop acceleration autopilot with PI correction suffers from low robustness, whereas the three-loop autopilot exhibits slow response to acceleration deviations. The proposed design overcomes these shortcomings by optimizing the autopilot for high-dynamic and fast-response scenarios. The design methodology leverages pole assignment, referencing the pole co-circle method and accommodating servo bandwidth limitations. A comparison of the designed three-loop acceleration autopilot with PI correction with other acceleration autopilots reveals superior accuracy advantages. The reliability and robustness of the proposed autopilot were validated through flight tests, achieving a drop point accuracy of less than 0.5 m. This study demonstrates the engineering application of a pseudo-angle-of-attack three-loop acceleration autopilot with PI correction, designed using the pole assignment method, on a short-range CUAV. Future efforts will focus on optimizing the autopilot to further enhance its adaptability and robustness.

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Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Cited by 2 publications

References 37 publications

Research on dynamic stability of rolling missiles employing direct/aerodynamic force compound control

Research on dynamic stability of rolling missiles employing direct/aerodynamic force compound control

Research and Flight Test on the Terminal Guidance Control Technology for Cruising Unmanned Aerial Vehicles

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