摘要
本文推导了鸭式布局自旋尾翼弹箭的非线性角运动方程组,并通过Hopf分岔特性分析来研究系统的角运动稳定性.以某型鸭式布局自旋尾翼弹为例,根据计算所得系统特征值的变化及所得Hopf分岔曲线,将角运动稳定性区间划分为稳定收敛域、稳定锥动域和不稳定域,并通过仿真计算加以验证.通过计算Hopf分岔点、极限环分岔点位置随参数的改变,定性研究参数对系统稳定性边界的影响.采用Hurwitz稳定性判据获取不稳定极限环半径,定量研究参数对系统稳定性边界的影响.结果表明:非线性气动力矩系数和控制舵偏角的变化均会对系统的分岔特性有较大影响,设计者应合理选取这些参数从而使其具有良好的气动特性与稳定性.
This paper derives the nonlinear angular motion equations of canard self-rotating projectile and investigates the stability of the system’s angular motion through Hopf bifurcation analysis.Taking a specific model of a canard self-rotating projectile as an example,based on the variation of the system’s eigenvalues and the calculated Hopf bifurcation curve,the angular motion stability region is divided into the stable convergence region,stable coning region,and unstable region,which is further validated through simulation calculations.By calculating the changes in the positions of the Hopf bifurcation point and limit cycle bifurcation point with respect to parameter variations,the qualitative influence of parameters on the system’s stability boundary is studied.Additionally,the unstable limit cycle radius is obtained using the Hurwitz stability criterion,allowing for a quantitative investigation of the influence of parameters on the system’s stability boundary.The results indicate that nonlinear aerodynamic moment coefficients and control deflections significantly affect the system’s bifurcation characteristics.Therefore,designers should carefully select these parameters to ensure optimal aerodynamic performance and stability.
作者
罗中琦
王立峰
张涪
曹天笑
杨鹏
Luo Zhongqi;Wang Lifeng;Zhang Fu;Cao Tianxiao;Yang Peng(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;The 210th Institute of the Sixth Academy of CASIC,Xi’an 710065,China)
出处
《动力学与控制学报》
2025年第6期26-37,共12页
Journal of Dynamics and Control
基金
国家自然科学基金资助项目(U2341230)。
