基于滑模变结构的无人机导引律仿真研究  

Simulation Study on the Guidance Law of UCAV Based on Sliding Mode Variable Structure

作　　者：徐啟云 王洁[1] 王鹏飞[1] 郝文渊[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《航空兵器》2017年第1期45-49,共5页Aero Weaponry

基　　金：航空科学基金项目(20120196006)

摘　　要：为了提高无人机导引律控制的稳定性,采用滑模变结构导引律控制方法。根据一定的假设条件,建立无人机三自由度模型,根据运动模型和初始状态得到实际飞行轨迹。由滑模变结构导引律得到无人机的期望轨迹,通过实际轨迹与期望轨迹之间的误差来驱动控制。仿真结果表明,无人机在导引律控制过程中控制量变化平稳,验证了该方法的有效性和合理性。In order to improve the stability of the guidance law control of UCAV, the guidance law control method of sliding mode variable structure is adopted. According to centain assumptions, the three degree of freedom model for UCAV is established, and the actual flight trajectory is obtained based on the motion model and the initial state. The expected trajectory of UCAV is obtained based on sliding mode variable structure guidance law, and the control is driven by the error between the actual trajectory and the expected trajectory. The simulation results show that the control states vary smoothly in the control process of guidance law, and the validity and rationality of the proposed method are verified.

关 键 词：无人机 相对运动模型 滑模变结构 导引律 

分 类 号：V249[航空宇航科学与技术—飞行器设计]