两种滤波方法在SINS/GPS组合导航中的分析比较

本文针对SINS/GPS组合导航系统中卡尔曼滤波发散的情况:介绍并分析了自适应滤波和H∞滤波算法原理,并进行仿真计算,验证了这两种滤波用于SINS/GPS组合导航系统的可行性和有效性,对实际应用中组合导航系统滤波器的设计具有一定的指导意义。     

基于双差伪距/伪距率的GPS/SINS紧组合导航

GPS/SINS组合导航系统的观测模型直接关系着导航系统的精度。提出了一种基于双差伪距/伪距率的GPS/SINS紧组合观测模型。分析了采用双差伪距和采用双差伪距/伪距率两种观测模型对组合导航输出参数精度的影响。实测数据结果表明,采用双差伪距和采用双差伪距/伪距率作为观测值均能实现组合导航系统的收敛。引入双差伪距率观测值明显改善了系统的可观测性,不仅提高了组合导航中速度和姿态角的估计精度,也加快了速度误差和姿态角误差估计的收敛速度。     

基于多尺度预处理的GPS/SINS组合导航系统

基于多尺度分析的思想,以离散小波变换为工具,利用小波对惯性元件输出的信息进行并行阈值消噪以削弱惯性元件误差对SINS及组合系统性能的影响;然后,对GPS输出的信息进行并行多尺度预处理,并结合传统的Kalman滤波方法,对系统进行综合滤波;将上述方法引入到GPS/SINS组合导航系统中,利用实测数据进行验证,并给出了基于不同方法的大量实验曲线。实验结果表明,该方法可以有效削弱惯性元件以及GPS误差对系统的影响,提高了GPS/SINS组合导航系的精度和可靠性。     

本期导读

利用掩星和地基GPS研究日食电离层效应(王泽民,等)一文利用COSMIC掩星GPS数据和地基CORS网GPS数据来共同分析2009-07-22发生在亚洲东部和太平洋西部的日全食,进而分析了日食期间电离层效应的物理过程。基于多尺度预处理的GPS/SINS组合导航系统(李廷军,等)一文基于多尺度分析的思想,以离散小波变换为工具,利用小波对惯性元件输出的信息进行并行阈值消噪以削弱惯性元件误差对SINS及组合系统性能的影响;对GPS输出的信息进行并行多尺度预处理,并结合传统的Kal man滤波方法,对系统进行综合滤波;将上述方法引入到GPS/SINS组合导航系统中,利用实测数据进行验证,并给出了基于不     

基于SINS／GPS的无人机组合导航系统建模与仿真

根据无人机的飞行特点以及SINS(捷联惯导)和GPS(全球定位系统)的优缺点,利用轨迹发生器设计无人机的飞行轨迹,建立基于SINS/GPS的无人机组合导航系统,依据卡尔曼滤波的相关原理对系统进行数学建模和计算仿真,验证无人机SINS/GPS组合导航系统的可靠性。     

两种滤波方法在SINS/GPS组合导航中的应用与比较

本文针对SINS/GPS组合导航系统中卡尔曼滤波发散的情况,引入了自适应滤波和H∞滤波,分析了它们各自的特性,最后进行仿真计算,验证了这两种滤波用于SINS/GPS组合导航系统的可行性和有效性,对实际应用中组合导航系统滤波器的设计具有一定的指导意义.     

基于GPS软件接收机的SINS／GPS紧组合系统仿真

为了系统验证SINS／GPS紧组合系统的性能,基于GPS软件接收机,进行了仿真系统构建。仿真系统由轨迹发生器、GPS中频信号模拟器、IMU信号模拟器、GPS软件接收机、SINS导航解算模块、组合滤波算法和导航性能分析模块等部分构成,其中详细设计了GPS软件接收机中的捕获和跟踪算法、SINS解算以及基于伪距和伪距率的组合滤波算法。仿真结果表明：紧组合导航系统收敛性较好,能够一定程度上抑制惯导系统误差的积累,有较好的导航性能。设计的该系统满足紧组合导航系统性能验证的需要,也为后续的超紧组合研究奠定了良好的基础。     

六、测量仪器

CH20020666 利用联邦滤波器设计 SINS/RDSS/GPS 组合导航系统/刘广军(信息工程大学测绘学院)∥武汉大学学报信息科学版.—2001(5).—441～445,458介绍了 Carlson 提出的分布式联邦滤波器理论,讨论了两类系统设计类型和4种配置模式的特性。首次提出SINS/RDSS/GPS 组合导航的设想,并对各子系统特点进行了探讨和对 SINS/RDSS 子系统进行了建模,建议在实际开发中采用 NR 配置模式,该模式属于 A 类联邦滤波系统。通过算例验证了 NR 模式融合结果的近似最优性、优良的容错性和故障探测能力。图5参16     

CNS/SINS组合导航系统仿真分析

天文导航和捷联惯性导航(CNS/SINS)相结合构成的组合导航系统,实现导航优势的互补,提高导航的精度和可靠性。文中阐述在惯性系下,以弹道导弹为研究对象而建立CNS/SINS组合导航的数学模型,并利用MATLAB编程设计基于离散型卡尔曼滤波的组合导航系统仿真,对比SINS和CNS/SINS对载体位置误差、速度误差以及姿态角估计的影响,进而验证CNS/SINS组合导航系统的可靠性。     

两种滤波方法在SINS／GPS组合导航中的应用与比较

针对SINS／GPS组合导航系统中卡尔曼滤波发散的情况,引入了自适应滤波和H∞滤波,分析了它们各自的特性,最后进行仿真计算,验证了这两种滤波用于SINS／GPS组合导航系统的可行性和有效性,对实际应用中组合导航系统滤波器的设计具有一定的指导意义。     

Performance of GPS and GPS/SINS navigation in the CE-5T1 skip re-entry mission

A CE-5T1 spacecraft completed a high-speed skip re-entry to the earth after a circumlunar flight on October 31, 2014. In addition to the strapdown inertial navigation system (SINS), a lightweight GPS receiver with rapid acquisition was developed as a navigation sensor in the re-entry capsule. The GPS receiver effectively solved the poor accuracy problem of long-term navigation using only the SINS. In contrast to ground users and low-earth-orbit spacecraft, numerous factors, including high altitude and kinetic characteristics in high-speed skip re-entry, are important for GPS positioning feasibility and were presented in accordance with the flight data. GPS solutions started at nearly 4900 km orbital altitude during the phases of re-entry process. These solutions were combined by an inertial measurement unit in a loosely coupled integrated navigation method and SINS navigation initialization. A simplified GPS/SINS navigation filter for limited resources was effectively developed and implemented on board for spacecraft application. Flight data estimation analyses, including trajectory, attitude, position distribution of GPS satellite, and navigation accuracy, were presented. The estimated accuracy of position was better than 42 m, and the accuracy of velocity was better than 0.1 m/s.     

一种低成本、低精度SINS/GPS组合导航系统及试验研究

在SINS（捷联式惯性导航系统）与GPS组合时，航向角的可观测性较弱，经过卡尔曼滤波后，航向角误差虽有所改善，但仍呈发散趋势，当采用低成本、低精度SINS时，该趋势进一步加剧。为了抑制该发散趋势，针对某型低成本、低精度SINS硬件组成（包括AHRS（姿态和航向参考系统）与IMU（惯性测量器件））的特点，提出了利用AHRS代替SINS航向角信息的方法。实际静态与动态试验表明，利用该方法可有效地抑制组合系统航向角的发散趋势，定位精度较高。     

GPS浮标/SINS组合水下导航与定姿若干问题讨论

介绍了GPS浮标／SINS组合用于水下设备的导航与定姿的优点,推导了水下设备载体坐标系与GPS定位的WGS84坐标系的转换关系,并根据陆地GPS／SINS力学编排的原理推导了水下GPS／SINS的误差状态方程。     

State transformation extended Kalman filter for GPS/SINS tightly coupled integration

Extended Kalman filter (EKF) is a widely used estimator for integrated navigation systems, and it works well in general situations. However, in adverse conditions such as partially observable environments and highly dynamic maneuvers, the performance of the traditional EKF-based strap-down inertial navigation system (SINS)/GPS integrated navigation system is easily to be affected by the dynamic changes of the specific force, thus leading to the problem of error covariance inconsistency. Though the inconsistency problem can be overcome to some extent if the system matrix, the states and the error covariance matrix are propagated as fast as possible in the SINS calculation rate, the problem cannot be fully solved. State transformation extended Kalman filter (ST-EKF) mechanization, with a new converted velocity error model for the SINS, is proposed, which can also be used to solve the inconsistency problem. In the ST-EKF, the specific force vector in the system error model is replaced by the nearly constant gravity vector for local navigation. Since the propagation and the updating of the ST-EKF can be executed simultaneously in the updating interval, the computation cost is greatly reduced compared with the traditional EKF. Experiments for the GPS/SINS tightly coupled navigation, including linear vibration Monte Carlo test and an unmanned aerial vehicle flight test, are implemented to evaluate the performance of the proposed ST-EKF. The results show that the proposed ST-EKF has superior performance to the traditional EKF, especially in partially observable situations.     

Integrated Navigation System and Experiment of a Low-Cost and Low-Accuracy SINS/GPS

When SINS (strap-down inertial navigation system) is combined with GPS, the observability of the course angle is weak. Although the course angle error is improved to some extent through Kalman filtering, the course angle still assumes a divergent trend. This trend is aggravated further when using low-cost and low-accuracy SINS. In order to restrain this trend, a method that uses AHRS to substitute for SINS course angle information is put forward aimed at the hardware component characteristic of the low-cost and low-accuracy SINS including AHRS (attitude and heading reference system) and IMU (inertial measurement unit). Real static and dynamic experiments show that the method can restrain the divergent trend of the navigation system angle effectively, and the positioning accuracy is high.