A tightly coupled rotational SINS/CNS integrated navigation method for aircraft  

作　　者：NING Xiaolin YUAN Weiping LIU Yanhong 

机构地区：[1]School of Instrument and Optoelectronic Engineering, Beihang University

出　　处：《Journal of Systems Engineering and Electronics》2019年第4期770-782,共13页系统工程与电子技术（英文版）

基　　金：supported by the National Natural Science Foundation of China(61722301)

摘　　要：Strapdown inertial navigation system(SINS)/celestial navigation system(CNS)integrated navigation is widely used to achieve long-time and high-precision autonomous navigation for aircraft.In general,SINS/CNS integrated navigation can be divided into two integrated modes:loosely coupled integrated navigation and tightly coupled integrated navigation.Because the loosely coupled SINS/CNS integrated system is only available in the condition of at least three stars,the latter one is becoming a research hotspot.One major challenge of SINS/CNS integrated navigation is obtaining a high-precision horizon reference.To solve this problem,an innovative tightly coupled rotational SINS/CNS integrated navigation method is proposed.In this method,the rotational SINS error equation in the navigation frame is used as the state model,and the starlight vector and star altitude are used as measurements.Semi-physical simulations are conducted to test the performance of this integrated method.Results show that this tightly coupled rotational SINS/CNS method has the best navigation accuracy compared with SINS,rotational SINS,and traditional tightly coupled SINS/CNS integrated navigation method.Strapdown inertial navigation system(SINS)/celestial navigation system(CNS) integrated navigation is widely used to achieve long-time and high-precision autonomous navigation for aircraft. In general, SINS/CNS integrated navigation can be divided into two integrated modes: loosely coupled integrated navigation and tightly coupled integrated navigation. Because the loosely coupled SINS/CNS integrated system is only available in the condition of at least three stars, the latter one is becoming a research hotspot. One major challenge of SINS/CNS integrated navigation is obtaining a high-precision horizon reference. To solve this problem, an innovative tightly coupled rotational SINS/CNS integrated navigation method is proposed. In this method, the rotational SINS error equation in the navigation frame is used as the state model, and the starlight vector and star altitude are used as measurements. Semi-physical simulations are conducted to test the performance of this integrated method. Results show that this tightly coupled rotational SINS/CNS method has the best navigation accuracy compared with SINS, rotational SINS, and traditional tightly coupled SINS/CNS integrated navigation method.

关 键 词：celestial NAVIGATION system(CNS) rotation modulation technology ROTATIONAL STRAPDOWN INERTIAL NAVIGATION system(SINS) ROTATIONAL SINS/CNS integrated NAVIGATION 

分 类 号：V24[航空宇航科学与技术—飞行器设计]