摘要
发展了适合双旋弹虚拟飞行仿真的高保真计算流体力学和刚体动力学耦合平台,以此为基础研究了旋转鸭舵对双旋弹弹道追随稳定性的影响。为了准确刻画双旋弹前后体的差动旋转效应,将滑移网格算法引入自研非结构混合网格流场数值模拟程序HUND3D。通过对双旋弹进行定轴转动非定常模拟,考察了不同鸭舵转速下双旋弹的流动特征与气动特性。通过耦合求解非定常雷诺平均NS方程和七自由度刚体动力学方程,实现了双旋弹不同弯度弹道的虚拟飞行仿真,分析了弹道追随过程的动力学机理,并结合气动特性分析结果研究了控制鸭舵转速改善弹道追随稳定性的策略。研究结果表明:鸭舵旋转所产生的气动干扰,能够显著影响弹体的侧向力与偏航力矩。通过控制前体鸭舵转速以产生有利于弹道追随的偏航力矩,能够在一定程度上改善弹道追随稳定性。
A high-fidelity computational fluid dynamics and rigid-body dynamics coupling platform suitable for virtual flight simulation of dual-spin projectile is developed.Based on this platform,the influence of rotating canards on the trajectory following stability of the dual-spin projectile is studied.To accurately characterize the differential rotation effect of the dual-spin projectile’s fore and aft bodies,a slidingmesh algorithm is introduced into the in-house unstructured mixed grid flow field numerical simulation program HUND3D.By conducting axisymmetric rotational unsteady simulations of the dual-spin projectile and investigating the flow characteristics and aerodynamic properties under different canard rotation speeds,the dynamics mechanism of the trajectory following process is analyzed.Through the coupled solution of unsteady Reynolds-averaged Navier-Stokes equations and seven-degree-of-freedom rigid-body dynamics equations,virtual flight simulations of the dual-spin projectile with different curvature trajectories are realized.The dynamic mechanism of the trajectory tracking process is analyzed,and strategies for improving trajectory following stability by controlling the canard rotation speed based on the analysis of aerodynamic characteristics are studied.The research results indicate that the aerodynamic disturbances generated by canard rotation can significantly affect the lateral force and yawing moment of the projectile.By controlling the rotation speed of the fore canards to produce a yawing moment favorable for trajectory tracking,the trajectory following stability can be improved to a certain extent.
作者
王刚
张润桐
林海珍
席柯
Wang Gang;Zhang Runtong;Lin Haizhen;Xi Ke(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Research Institute of Navigation and Control Technology,Beijing 100089,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China)
出处
《航空兵器》
CSCD
北大核心
2024年第2期71-78,共8页
Aero Weaponry
基金
国家自然科学基金叶企孙科学基金项目(U2141254)。
关键词
双旋弹
虚拟飞行仿真
计算流体力学
滑移网格
侧向力
偏航力矩
追随稳定性
dual-spin projectile
virtual flight simulation
computational fluid dynamics
sliding mesh
lateral force
yawing moment
following stability