基于闭环控制的带翼导弹虚拟飞行数值模拟
收稿日期: 2013-04-18
修回日期: 2013-07-22
网络出版日期: 2013-08-20
基金资助
国家“973”计划（2009CB724104）
Virtual Flight Numerical Simulation of the Basic Finner Projectile with Closed Loop
Received date: 2013-04-18
Revised date: 2013-07-22
Online published: 2013-08-20
Supported by
National Basic Research Program of China (2009CB724104)
通过耦合求解非定常Navier-Stokes方程、刚体六自由度（6DOF）运动方程及舵偏控制律，发展了一套虚拟飞行数值模拟平台，对基本带翼导弹外形进行了虚拟飞行数值模拟研究。流场求解采用基于结构网格的有限体积法，时间推进采用双时间步法，使用刚性重叠动网格技术模拟舵与弹身的相对运动，采用四阶Runger-Kutta方法求解运动方程组，舵偏控制律采用基于比例-积分-微分（PID）的反馈控制。模拟结果表明：发展的虚拟飞行数值模拟平台能够处理包含复杂运动边界的非定常运动问题，可以为非定常气动力建模提供数据、预示飞行器稳定性及检验飞行控制律，该模拟平台具备一定的工程应用价值。
席柯 , 袁武 , 阎超 , 黄宇 . 基于闭环控制的带翼导弹虚拟飞行数值模拟[J]. 航空学报, 2014 , 35(3) : 634 -642 . DOI: 10.7527/S1000-6893.2013.0348
Through the solution by coupling of the unsteady Navier-Stokes equations, the rigid-body six degree-of-freedom (6DOF) motion equations and the rudder deflection control law, a set of platforms is developed and the virtual flight simulation of a basic finner projectile is investigated. The flow solver is a finite-volume solver based on a structure grid with dual time stepping, the chimera method is used to simulate relative motions, the fourth-order Runger-Kutta method is used to solve the motion equations, and the rudder control law using feedback control is based on proportional integral and differential (PID). Simulation results show that the virtual flight simulation platform is capable of solving the complicated unsteady flows with moving boundaries, andproviding data for unsteady aerodynamic modeling, which indicates the stability of the aircraft and test flight control law, and promises a strong prospect for engineering application.
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