大飞机极区惯性/天文组合导航算法  

Stellar-inertial navigation for transpolar large aircraft

作　　者：周琪[1,2] 秦永元[1] 严恭敏[1] 岳亚洲[2] 

机构地区：[1]西北工业大学自动化学院,陕西西安710072 [2]中航工业西安飞行自动控制研究所,陕西西安710065

出　　处：《系统工程与电子技术》2013年第12期2559-2565,共7页Systems Engineering and Electronics

基　　金：航空基金(9140A09031310HK0319)资助课题

摘　　要：针对高纬度地区地理经线收敛,造成传统惯导力学编排在地理极点存在奇异值的问题,结合军用大飞机对全自主、高精度、长航时、全球范围导航能力的需要,提出了极区格网惯性/天文组合导航方案。首先以格林尼治子午线作为航向参考,可避免航向参考线在极点处收敛。在此基础上定义了格网导航坐标系,并推导了格网惯导力学编排及其误差方程,解决了传统力学编排在极区无法工作的难题。其次,利用星跟踪器瞄准线位置矢量在惯导平台坐标系和计算坐标系内的测量和计算之差,作为卡尔曼滤波的量测以估计和校正惯导误差。仿真分析表明,格网惯性/天文组合导航方案在8h内的定位误差小于400m,可满足大飞机极区导航的需要。An approach to polar stellar-inertial navigation utilizing a grid coordinate system is presented. The conventional inertial navigation mechanizations is not suited for transpolar flights due to the convergence of the longitude meridians at the poles which cause a mathematical singularity in the navigation equations. The method proposed here utilizes a grid reference frame and the grid meridians are everywhere parallel to the Green-wich meridian, based on which, the grid mechanization equations and error equations are derived. Since the me-ridians do not converge at the poles, the grid mechanization is well suited for polar navigation. The requirement for military aircraft inertial navigation systems with all-earth, completely self-contained, high precision and long-flight capability can be achieved through aiding with star-tracker. The difference between the inertial plat-form measured and computed lines of sight vectors to a star provides an ideal observation for the stellar-inertial Kalman filter to estimate or correct inertial navigation errors. The simulation results show that the position er-ror propagation is less than 400 m for an 8 h flight and the proposed scheme is effective in polar navigation.

关 键 词：极区导航 格网导航 组合导航 星跟踪器 卡尔曼滤波 

分 类 号：U666.1[交通运输工程—船舶及航道工程]