Coning Motion Stability Analysis of Spinning Missiles Considering Elastic Effect

PEI Xinyue; YU Yong; YU Jianqiao

doi:10.12382/bgxb.2025.0177

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Coning Motion Stability Analysis of Spinning Missiles Considering Elastic Effect

更新时间：2026-04-05

- Coning Motion Stability Analysis of Spinning Missiles Considering Elastic Effect
- Acta Armamentarii (2026)
- 作者机构：
  
  北京理工大学空天科学与技术学院,北京,100081
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2025.0177
  CLC： TJ765.2
- Received：13 March 2025，
  
  Online First：05 April 2026，
- 稿件说明：
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裴新月，于勇，于剑桥. 考虑弹性效应的旋转导弹锥形运动稳定性分析[J/OL]. 兵工学报, 2026(2026-04-05). https://doi.org/10.12382/bgxb.2025.0177.

PEI X Y, YU Y, YU J Q. Coning motion stability analysis of spinning missiles considering elastic effect[J/OL]. Acta Armamentarii, 2026(2026-04-05). https://doi.org/10.12382/bgxb.2025.0177. (in Chinese)
裴新月，于勇，于剑桥. 考虑弹性效应的旋转导弹锥形运动稳定性分析[J/OL]. 兵工学报, 2026(2026-04-05). https://doi.org/10.12382/bgxb.2025.0177. DOI：

PEI X Y, YU Y, YU J Q. Coning motion stability analysis of spinning missiles considering elastic effect[J/OL]. Acta Armamentarii, 2026(2026-04-05). https://doi.org/10.12382/bgxb.2025.0177. (in Chinese) DOI：

摘要

随着旋转导弹长细比的增大，旋转导弹的弹性变形也逐渐成为飞行过程中不可忽视的重要因素，弹性效应与旋转导弹刚体运动相互作用会进一步影响弹体的稳定性，对刚-弹耦合的旋转弹进行稳定性分析很有必要。基于刚-弹耦合旋转弹动力学模型，通过合理的假设和小扰动线性化以及固化系数法，建立考虑弹体弹性变形的旋转导弹线性扰动运动方程，通过求解特征点处的特征方程根及自由扰动运动解析解探究弹性效应对旋转导弹锥形运动的影响，并通过特征根法给出弹性旋转导弹锥形运动稳定转速边界，通过仿真验证求解方法的准确性。对比某旋转弹刚体模型和刚-弹耦合模型的稳定性条件，发现旋转弹的稳定转速边界从26.7r/s缩小至22.3r/s，弹体的弹性效应会缩小稳定转速边界的范围，可能导致原本稳定的飞行失稳。

Abstract

With increasing slenderness ratios of spinning missiles

elastic deformation has gradually become a non-negligible factor during flight operations. The interaction between elastic effects and rigid-body motion may further compromise missile stability

necessitating stability investigations that account for rigid-elastic coupling effects. Based on the rigid-elastic coupled dynamic model of spinning missiles

this study establishes linear perturbed motion equations incorporating elastic deformation through reasonable assumptions

small-disturbance linearization

and the frozen coefficient method. By solving characteristic equation roots at critical points and deriving analytical solutions for free perturbed motion

we systematically investigate how elastic effects influence the coning motion of spinning missiles. Furthermore

the characteristic root method is employed to determine the stable rotational speed boundary for elastic spinning missiles

with numerical simulations validating the accuracy of our analytical approach.A comparative analysis of the stability criteria between the rigid-body model and the coupled rigid-elastic model for spinning projectiles reveals that the stability boundary of rotational speed decreases from 26.7 r/s to 22.3 r/s. The elastic effects of the projectile body are shown to reduce the operational range of stable rotational speeds

potentially leading to the destabilization of originally stable flight trajectories.

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