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	A Novel Adaptive Noise Covariance Matrix Estimation and Filtering Method: Application to Multiobject Tracking 期刊论文 OAI收割 IEEE TRANSACTIONS ON INTELLIGENT VEHICLES, 2024, 卷号: 9 作者: Jiang, Chao; Wang, Zhiling; Liang, Huawei; Wang, Yajun \| 收藏 \| 浏览/下载：8/0 \| 提交时间：2024/11/20 Covariance matrices Noise measurement Estimation Correlation Filtering Calibration Technological innovation Kalman filtering adaptive estimation process and measurement noise covariance matrices multiobject tracking
	RL-AKF: An Adaptive Kalman Filter Navigation Algorithm Based on Reinforcement Learning for Ground Vehicles 期刊论文 OAI收割 REMOTE SENSING, 2020, 卷号: 12, 期号: 11, 页码: 25 作者: Gao, Xile; Luo, Haiyong; Ning, Bokun; Zhao, Fang; Bao, Linfeng \| 收藏 \| 浏览/下载：37/0 \| 提交时间：2020/12/10 integrated navigation Kalman filter process noise covariance estimation reinforcement learning deep deterministic policy gradient
	Automatic Calibration of Process Noise Matrix and Measurement Noise Covariance for Multi-GNSS Precise Point Positioning 期刊论文 OAI收割 MATHEMATICS, 2020, 卷号: 8, 期号: 4, 页码: 20 作者: Zhang, Xinggang; Li, Pan; Tu, Rui; Lu, Xiaochun; Ge, Maorong \| 收藏 \| 浏览/下载：23/0 \| 提交时间：2020/09/01 EM-algorithm multi-GNSS PPP process noise observation covariance matrix extended Kalman filter machine learning
	An Adaptive UKF Algorithm for the State and Parameter Estimations of a Mobile Robot 期刊论文 OAI收割自动化学报, 2008, 卷号: 34, 期号: 1, 页码: 72-79 作者: Song Q(宋崎); Han JD(韩建达) 收藏 \| 浏览/下载：18/0 \| 提交时间：2012/05/29 Adaptive Unscented Kalman filter (UKF) innovation MIT rule process covariance
	Application of CMOS APS star tracker with large FOV in attitude and angular velocity determination (EI CONFERENCE) 会议论文 OAI收割 Advanced Sensor Systems and Applications III, November 12, 2007 - November 14, 2007, Beijing, China Lu D.; Guang J.; Shaoju W.; Tao C. 收藏 \| 浏览/下载：30/0 \| 提交时间：2013/03/25 The paper deals with the spacecraft attitude determination problem using a new kind of star tracker with large FOV based on CMOS APS. Star tracker has been developed since 1970s and proved to be the most accurate sensor ever used in the spacecraft attitude determination systems. But the traditional CCD star tracker also has some disadvantages such as small FOV high power consumption low sample rate and low working angular rate limit which prevent the use of CCD star tracker in attitude large angle maneuvering process. The new kind of star tracker based on CMOS APS has no such disadvantages and is more applicable on modern low-cost agile small satellites. Its higher sample rate and working angular rate limit over traditional CCD star tracker make it more adapt for spacecraft angular velocity determination. Because of the large FOV of the star tracker the mathematical model of traditional CCD star tracker with a small FOV is not appropriate. So a new mathematical model was quoted to fit the star tracker with a large FOV. An alternative adaptive algorithm was also introduced in the paper. It can help the EKF algorithm work lacking of accurate covariance of the observation noise. An optimal estimation algorithm was used to estimate the angular velocity directly from the star tracker measurements. Mathematic simulation results indicate the CMOS APS star tracker can give accurate attitude information and estimated angular rate. The method can be used as the chief attitude determination system design of low-cost satellite without gyros or be used as a backup strategy in the event of gyro failures to enhance the reliability of the attitude determination system.
	An adaptive UKF algorithm and its application in mobile robot control 会议论文 OAI收割 IEEE International Conference on Robotics and Biomimetics (ROBIO 2006), Kunming, China, December 17-20, 2006 作者: Song Q(宋崎); Qi JT(齐俊桐); Han JD(韩建达) 收藏 \| 浏览/下载：17/0 \| 提交时间：2012/06/06 adaptive UKF innovation MIT process covariance
	Design of GPS/INS integrated navigation system based on multisensor information fusion (EI CONFERENCE) 会议论文 OAI收割 6th World Congress on Intelligent Control and Automation, WCICA 2006, June 21, 2006 - June 23, 2006, Dalian, China Chunmei H.; Yantao T.; Wanxin S.; Mao L. 收藏 \| 浏览/下载：38/0 \| 提交时间：2013/03/25 Two kinds of design methods of GPS/INS integrated navigation system are presented that is GPS/INS integrative system and integrated navigation system based on information fusion. By analyzing mathematics model of the first system error we found that inertia velocity error would cause code loop track error. Consequently the pseudo range meterage error is interrelated with inertia velocity error which is complex to calculate. If this relativity is ignored in the state equation and observation equation of this system it must affect the estimated precision of the kalman filter and maybe the system is unstable. Therefore the second integrated navigation method is introduced. It adopts information fusion federal kalman filter and covariance. And consider the above pertinence to analyze the navigation performance of the integration system. Then it gives the flow of federal kalman filter algorithm. By analyzing the conclusion is that velocity error of integrated navigation system drops from 0.5m/s to below 0.05m/s and improves the precision and reliability of the navigation system effectively well continuity and real-time capability. It provides an effective way for data analysis and process of fusion navigation system. 2006 IEEE.