鸭舵式二维修正弹无控段共振机理研究及气动优化

郭含; 彭志凌; 柳文安; 李广才; 陶瑞萍

doi:10.12382/bgxb.2026.0534

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鸭舵式二维修正弹无控段共振机理研究及气动优化

更新时间：2026-08-21

- 鸭舵式二维修正弹无控段共振机理研究及气动优化
- Resonance Mechanism and Aerodynamic Optimization of a Canard-Type Two-Dimensional Trajectory Correction Projectile in the Uncontrolled Flight Phase
- 兵工学报 2026年
- 作者机构：
  
  1. 中北大学机电工程学院,山西,太原,030051
  2. 中国兵器工业集团淮海工业集团有限公司,山西,长治,046012
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2026.0534
  中图分类号： TJ011.3
- 收稿：2026-06-16，
  
  网络首发：2026-08-21，
- 稿件说明：
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郭含，彭志凌，柳文安，等. 鸭舵式二维修正弹无控段共振机理研究及气动优化[J/OL]. 兵工学报, 2026(2026-08-21). https://doi.org/10.12382/bgxb.2026.0534.

GUO H, PENG Z L, LIU W A, et al. Resonance mechanism and aerodynamic optimization of a canard-type two-dimensional trajectory correction projectile in the uncontrolled flight phase[J/OL]. Acta Armamentarii, 2026(2026-08-21). https://doi.org/10.12382/bgxb.2026.0534. (in Chinese)
郭含，彭志凌，柳文安，等. 鸭舵式二维修正弹无控段共振机理研究及气动优化[J/OL]. 兵工学报, 2026(2026-08-21). https://doi.org/10.12382/bgxb.2026.0534. DOI：

GUO H, PENG Z L, LIU W A, et al. Resonance mechanism and aerodynamic optimization of a canard-type two-dimensional trajectory correction projectile in the uncontrolled flight phase[J/OL]. Acta Armamentarii, 2026(2026-08-21). https://doi.org/10.12382/bgxb.2026.0534. (in Chinese) DOI：

摘要

针对鸭式二维修正双旋弹无控段速度与加速度周期性波动问题，从刚体角运动与非线性气动力学出发研究其共振机理与外形优化方法。利用复攻角理论揭示了鸭舵扰动与弹体固有频率共振引发弹道波动的机理，在转速与速度刚性约束下，提出减小舵翼翼展、增大舵偏角调控方案，并基于CFD方法对5种典型外形开展仿真对比。结果表明：缩减翼展可提高俯仰力矩导数，抬升弹体固有频率以规避共振；合理增大舵偏角可匹配操纵力矩变化，使力矩处于适宜范围。该方案有效抑制了弹道参数波动，整体气动特性良好，可在保障修正功能的同时提升飞行稳定性。

Abstract

Aiming at periodic fluctuation of velocity and acceleration for canard-configured two-dimensional correction dual-spin projectiles in uncontrolled flight phase

the resonance mechanism and shape optimization method were studied based on rigid-body angular motion and nonlinear aerodynamics. Complex angle of attack theory revealed how canard disturbance resonates with projectile natural frequency and causes ballistic fluctuation. A canardspanreduction and deflection angle increase scheme was proposed under fixed flight speed and spin rate constraints. Computational Fluid Dynamics (CFD) simulations compared five typical projectile shapes. The results showed that reduced canard span raises pitching moment derivative and projectile natural frequency to avoid resonance

and properly increased deflection angle optimizes control moment. This scheme restrains ballistic fluctuation

maintains good aerodynamic performance

improves flight stability while ensuring correction capability

and provides

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