Celestial navigation system is an important autonomous navigation system widely used for deep spaceexploration missions, in which extended Kalman filter and the measurement of angle between celestial bodies areused to...Celestial navigation system is an important autonomous navigation system widely used for deep spaceexploration missions, in which extended Kalman filter and the measurement of angle between celestial bodies areused to estimate the position and velocity of explorer. In a conventional cartesian coordinate, this navigationsystem can not be used to achieve accurate determination of position for linearization errors of nonlinear space-craft motion equation. A new autonomous celestial navigation method has been proposed for lunar satellite usingclassical orbital parameters. The error of linearization is reduced because orbit parameters change much moreslowly than the position and velocity used in the cartesian coordinate. Simulations were made with both the cart-esiane system and a system based on classical orbital parameters using extended Kalman filter under the sameconditions for comparison. The results of comparison demonstrated high precision position determination of lunarsatellite using this new method.展开更多
The autonomous "celestial navigation scheme" for deep space probe departing from the earth and the autonomous "optical navigation scheme" for encountering object celestial body are presented. Then,...The autonomous "celestial navigation scheme" for deep space probe departing from the earth and the autonomous "optical navigation scheme" for encountering object celestial body are presented. Then, aiming at the conditions that large initial estimation errors and non-Gaussian distribution of state or measurement errors may exist in orbit determination process of the two phases, UPF (unscented particle filter) is introduced into the navigation schemes. By tackling nonlinear and non-Gaussian problems, UPF overcomes the accuracy influence brought by the traditional EKF (extended Kalman filter), UKF (unscented Kalman filter), and PF (particle filter) schemes in approximate treatment to nonlinear and non-Gaussian state model and measurement model. The numerical simulations demonstrate the feasibility and higher accuracy of the UPF navigation scheme.展开更多
In order to improve the autonomous navigation capability of satellite,a pulsar/CNS（celestial navigation system） integrated navigation method based on federated unscented Kalman filter（UKF） is proposed.The celestia...In order to improve the autonomous navigation capability of satellite,a pulsar/CNS（celestial navigation system） integrated navigation method based on federated unscented Kalman filter（UKF） is proposed.The celestial navigation is a mature and stable navigation method.However,its position determination performance is not satisfied due to the low accuracy of horizon sensor.Single pulsar navigation is a new navigation method,which can provide highly accurate range measurements.The major drawback of single pulsar navigation is that the system is completely unobservable.As two methods are complementary to each other,the federated UKF is used here for fusing the navigation data from single pulsar navigation and CNS.Compared to the traditional celestial navigation method and single pulsar navigation,the integrated navigation method can provide better navigation performance.The simulation results demonstrate the feasibility and effectiveness of the navigation method.展开更多
To solve the highly nonlinear and non-Gaussian recursive state estimation problem in geomagnetic navigation,the unscented particle filter (UPF) was introduced to navigation system.The simulation indicates that geomagn...To solve the highly nonlinear and non-Gaussian recursive state estimation problem in geomagnetic navigation,the unscented particle filter (UPF) was introduced to navigation system.The simulation indicates that geomagnetic navigation using UPF could complete the position estimation with large initial horizontal position errors.However,this navigation system could only provide the position information.To provide all the kinematics states estimation of aircraft,a novel autonomous navigation algorithm,named unscented particle and Kalman hybrid navigation algorithm (UPKHNA),was proposed for geomagnetic navigation.The UPKHNA used the output of UPF and barometric altimeter as position measurement,and employed the Kalman filter to estimate the kinematics states of aircraft.The simulation shows that geomagnetic navigation using UPKHNA could provide all the kinematics states estimation of aircraft continuously,and the horizontal positioning performance is better than that only using the UPF.展开更多
X射线脉冲星导航利用X射线辐射脉冲到达时间(Time of Arrival,TOA)作为信息输入,星敏感器导航利用星光角距等作为信息输入,是两种不同机理的天文导航方法。提出一种将脉冲星TOA和星敏感器星光角距测量结合的信息融合天文自主导航方法,...X射线脉冲星导航利用X射线辐射脉冲到达时间(Time of Arrival,TOA)作为信息输入,星敏感器导航利用星光角距等作为信息输入,是两种不同机理的天文导航方法。提出一种将脉冲星TOA和星敏感器星光角距测量结合的信息融合天文自主导航方法,设计了一种利用激光光量子模拟脉冲星X射线辐射光子的半物理仿真系统用于算法验证,并基于无迹卡尔曼滤波(Unscented Kalman Filter,UKF)使用真轨道参数做了仿真试验。结果表明,基于UKF的信息融合方法比基于EKF(Extended Kalman Filter)的信息融合方法性能更好,与仅使用脉冲星或星敏感器的导航方法相比,能将位置估计精度分别提高52.7%和43.6%,速度估计精度分别提高82.2%和70.5%。展开更多
基金Sponsored by the National Natural Science Foundation of China(Grant No. 60174031)China National Space Administration
文摘Celestial navigation system is an important autonomous navigation system widely used for deep spaceexploration missions, in which extended Kalman filter and the measurement of angle between celestial bodies areused to estimate the position and velocity of explorer. In a conventional cartesian coordinate, this navigationsystem can not be used to achieve accurate determination of position for linearization errors of nonlinear space-craft motion equation. A new autonomous celestial navigation method has been proposed for lunar satellite usingclassical orbital parameters. The error of linearization is reduced because orbit parameters change much moreslowly than the position and velocity used in the cartesian coordinate. Simulations were made with both the cart-esiane system and a system based on classical orbital parameters using extended Kalman filter under the sameconditions for comparison. The results of comparison demonstrated high precision position determination of lunarsatellite using this new method.
基金the National "863" High Technology Development Project of China (2005AA735080).
文摘The autonomous "celestial navigation scheme" for deep space probe departing from the earth and the autonomous "optical navigation scheme" for encountering object celestial body are presented. Then, aiming at the conditions that large initial estimation errors and non-Gaussian distribution of state or measurement errors may exist in orbit determination process of the two phases, UPF (unscented particle filter) is introduced into the navigation schemes. By tackling nonlinear and non-Gaussian problems, UPF overcomes the accuracy influence brought by the traditional EKF (extended Kalman filter), UKF (unscented Kalman filter), and PF (particle filter) schemes in approximate treatment to nonlinear and non-Gaussian state model and measurement model. The numerical simulations demonstrate the feasibility and higher accuracy of the UPF navigation scheme.
基金supported by the National High Technology Research and Development Program of China(2006AAJ109)Aviation Science Fund(20070818001)
文摘In order to improve the autonomous navigation capability of satellite,a pulsar/CNS（celestial navigation system） integrated navigation method based on federated unscented Kalman filter（UKF） is proposed.The celestial navigation is a mature and stable navigation method.However,its position determination performance is not satisfied due to the low accuracy of horizon sensor.Single pulsar navigation is a new navigation method,which can provide highly accurate range measurements.The major drawback of single pulsar navigation is that the system is completely unobservable.As two methods are complementary to each other,the federated UKF is used here for fusing the navigation data from single pulsar navigation and CNS.Compared to the traditional celestial navigation method and single pulsar navigation,the integrated navigation method can provide better navigation performance.The simulation results demonstrate the feasibility and effectiveness of the navigation method.
基金Project(HIT.NSRIF.2009006) supported by the Fundamental Research Funds for the Central Universities of China
文摘To solve the highly nonlinear and non-Gaussian recursive state estimation problem in geomagnetic navigation,the unscented particle filter (UPF) was introduced to navigation system.The simulation indicates that geomagnetic navigation using UPF could complete the position estimation with large initial horizontal position errors.However,this navigation system could only provide the position information.To provide all the kinematics states estimation of aircraft,a novel autonomous navigation algorithm,named unscented particle and Kalman hybrid navigation algorithm (UPKHNA),was proposed for geomagnetic navigation.The UPKHNA used the output of UPF and barometric altimeter as position measurement,and employed the Kalman filter to estimate the kinematics states of aircraft.The simulation shows that geomagnetic navigation using UPKHNA could provide all the kinematics states estimation of aircraft continuously,and the horizontal positioning performance is better than that only using the UPF.
