摘要
文中基于直接力与气动力复合控制的导弹,提出了空气舵和直接力喷流装置同步工作的混合方式,建立了弹体模型,给出了一种自动驾驶仪的设计方法。自动驾驶仪具有传统的结构形式,内回路为阻尼回路,采用连续的控制方式;外回路为加速度控制回路,采用变结构控制率,以减小弹体参数摄动对输出加速度的影响。仿真结果表明,这种混合方式能够同时提高导弹的最大输出加速度和快速响应能力,自动驾驶仪具有良好的性能。
In this a synchronous blended method for missiles with aero-fin and lateral thrust control is presented.The mathematical model of the missile with this blended control and the details of autopilot design are given.The autopilot has the traditional structure.The iner part is rate loop which adopt continuous control policy,the outer part is accelerometer feedback loop which adopt variable structure control law to decrease the effect of parameter variation.The simulation results show that this blended method could increase the maxmal output acceleration and the fast reponse ability simultaneously,and the autopilot has good performance.
出处
《弹箭与制导学报》
CSCD
北大核心
2005年第2期1-3,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
航空科学基金 ( 0 3 D1 2 0 0 4 )
