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《Ordnance Industry Automation》 2017-10
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Study of Algorithm for SINS/GPS Integrated Navigation System in Launch Inertial Coordinate System

Yin Dequan;Xiong Zhi;Shi Lijuan;Lin Aijun;Yu Feng;College of Automation Engineering, Nanjing University of Aeronautics & Astronautics;College of Astronautics, Nanjing University of Aeronautics & Astronautics;  
Traditional strapdown inertial navigation algorithm based on geography coordinate system can not directly obtain the navigation parameters under launch inertial coordinate system. It's difficult for high orbiters such as aerospace vehicles to be provided with high precision, high reliability navigation system. Therefore, this paper carried out a research on the strapdown inertial navigation algorithm under launch inertial coordinate system and established SINS/GPS inertial navigation model on the basis of extended Kalman filter. The navigation measurement information obtained by the sensors under launch inertial coordinate system was directly used to calculate position and attitude of the aircraft. To verify the validity of the integrated navigation algorithm, the hardware platform based on XSENS inertial device, GPS receiver and STM32 embedded system was established. Experimental results indicated that the SINS/GPS integrated navigation system under launch inertial coordinate system can achieve higher navigation precision. Thus algorithm proposed in this paper is valid and reasonable.
【Fund】: 国家自然科学基金(61533009 61374115);; 江苏省六大人才高峰资助(2013-JY-013);; 江苏高校优势学科建设工程;; 中央高校基本科研业务费专项资金(NP2015406 NP20152212);; 南京航空航天大学大学研究生创新基地(实验室)开放基金资助(kfjj20150315)
【CateGory Index】: TN967.2
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