The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration

LI Hongyun; SHEN Qiang; DENG Zilong; LIANG Chen

doi:10.12382/bgxb.2025.0102

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The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration

更新时间：2026-04-24

- The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration
- Acta Armamentarii Vol. 47, Issue 2, Pages: 250102(2026)
- 作者机构：
  
  北京理工大学机电学院，北京 100081
  机电动态控制重点实验室，北京 100081
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2025.0102
  CLC： TJ012.3
- Received：18 February 2025，
  
  Online First：25 December 2025，
  
  Published：28 February 2026
- 稿件说明：
移动端阅览
LI Hongyun, SHEN Qiang, DENG Zilong, et al. The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration[J]. Acta Armamentarii, 2026, 47(2): 250102.
DOI：

LI Hongyun, SHEN Qiang, DENG Zilong, et al. The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration[J]. Acta Armamentarii, 2026, 47(2): 250102. DOI： 10.12382/bgxb.2025.0102.

摘要

针对鸭式布局旋转稳定弹在时变滚转角指令下的攻角响应问题，基于小攻角假设建立弹丸状态空间模型，并求解脉冲响应矩阵。在时域中，利用卷积定理构建攻角响应的通用解析模型；在频域中，分析周期指令输入可能引发的共振机理。为明确鸭舵结构参数、气动参数和控制参数对攻角的影响规律，推导了攻角幅值的参数化解析解。研究结果表明：建立的攻角通用解析模型可准确计算时变、固定和周期滚转角指令下的攻角响应。增大鸭舵组件的舵偏角、控制力作用点距弹丸质心的距离或升力系数导数，均会导致攻角幅值增大。在飞行过程中，应尽量避免滚转角频繁变化，并可对攻角幅值进行限制以保证飞行稳定性；此外，当滚转角指令连续变化时，应避免其变化频率接近弹丸固有频率，以防止攻角幅值剧烈增大。仿真结果验证了理论的正确性，该研究为鸭式布局旋转稳定弹的角运动特性研究提供了补充。

Abstract

To address the angle of attack response of spin-stabilized projectiles with canard configuration under time-varying roll angle commands

a state-space model of the projectile is established based on the small angle of attack assumption

and the impulse response matrix is solved. In the time domain

a general analytical model for the angle of attack response is constructed using the convolution theorem

and in the frequency domain

the potential resonance mechanism induced by periodic command inputs is analyzed. To clarify the influence of canard structural parameters

aerodynamic parameters

and control parameters on the angle of attack

a parameterized analytical solution for the amplitude of the angle of attack is derived. The results show that the established general analytical model can accurately calculate the angle of attack response under time-varying

fixed and periodic roll angle commands. Increasing the deflection angle of the canard

the distance from the action point of control force to the projectile's center of mass

and the derivative of lift coefficient will all lead to an increase in the amplitude of the angle of attack. During flight

the frequent changes in the roll angle should be avoided as far as possible

and the amplitude of the angle of attack should be limited to ensure the flight stability. In addition

when the roll angle command changes continuously

it is necessary to prevent its change frequency from approaching the inherent frequency of the projectile to avoid a sharp increase in the amplitude of the angle of attack. The simulated results verify the correctness of the theory

and this research supplements the studies on the angular motion characteristics of spin-stabilized projectiles with canard configuration.

关键词

Keywords

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