摘要
捷联惯导/卫星系统/天文系统(SINS/GNSS/CNS)实现了优势互补,是提高弹道导弹命中精度的一种重要导航方法。设计基于UD_UKF滤波的组合导航系统无重置联邦滤波器,在发射惯性坐标系下建立SINS/GNSS/CNS组合导航的数学模型,对比分析SINS/CNS、SINS/GNSS及SINS/GNSS/CNS对惯导参数误差、位置误差、速度误差以及初始失准角的估计。仿真结果表明,SINS/GNSS/CNS不仅能够大大提高命中精度,而且还能够对初始失准角进行有效估计,满足导弹机动快速发射需求。
SINS/GNSS/CNS is an important navigation method for improving hitting accuracy of ballistic missile by achieving integrated advantages.A non-reset federated filter of integrated navigation system based on UD_UKF was designed.The mathematical model of SINS/GNSS/CNS was established in launch inertial coordinates.The estimations of sins parameters error,velocity error,position error and initial misalignment angle by SINS,SINS/GNSS,SINS/CNS and SINS/GNSS/CNS are compared and analysed.The simulation results indicate that SINS/GNSS/CNS not only improves the hitting accuracy evidently but also evaluates the initial misalignment angle effectively,satisfying the missile＇s prompt maneuver launch requirement.
出处
《导弹与航天运载技术》
北大核心
2011年第2期24-28,共5页
Missiles and Space Vehicles
