为全面、准确、直观地发布实时航标助航信息,应用计算机网络技术、现代通信技术以及GPS,AIS,ECDIS和Web等关键技术,设计开发航标助航信息发布系统.该系统符合国际海事组织(International Maritime Organization,IMO)提出的数字航海战略...为全面、准确、直观地发布实时航标助航信息,应用计算机网络技术、现代通信技术以及GPS,AIS,ECDIS和Web等关键技术,设计开发航标助航信息发布系统.该系统符合国际海事组织(International Maritime Organization,IMO)提出的数字航海战略框架,适应国际航标协会(Interna-tional Association of Lighthouse Authorities,IALA)现代航标发展方向,满足IALA有关推荐标准的要求.该系统实现基于图像建模与绘制(Image-Based Modeling and Rendering,IBMR)航标的360°航道全景图(虚拟三维)、基于遥感(Remote Sensing,RS)影像图的航标航道显示和基于自动识别系统(Automatic Identification System,AIS)的实体航标和虚拟航标信息显示等资料的综合显示功能.用户在互联网上借助通用的网络浏览器就可了解科学、全面、及时、准确、生动、直观的航标助航信息,从而提高海上交通安全指数和港口、船舶的营运效率.展开更多
The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air to air missiles have been investigated recently. In comparison with those investigations existing in current publi...The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air to air missiles have been investigated recently. In comparison with those investigations existing in current publications, a new tightly coupled SINS/GPS integration navigation system for air to air missiles, based on the decorrelated pseudo range approach, is presented in this paper. Because of high jamming and dynamic of air to air missiles, inertial velocity aiding GPS receiver is used to provide a more accurate, jam resistant measurement for midcourse guidance systems. A tracking error estimator is designed to distinguish the correlation that existed between pseudo range measurements and inertial information. It is found better to regard inertial velocity aiding errors as the noise of which statistical properties are unknown. So using mixed Kalman/minimax filtering theory, one can obtain the new tracking error estimator with simple and robust algorithm through constructing a composite filter consisting of two parts: Kalman filter for the noise of known statistics and minimax filter for the unknown. In order to ensure this simple estimator stability, a new method is proposed to choose its parameters, based on Khargonekars work. Moreover, it is demonstrated that the given method also ensures the proposed estimator optimality. All the work mentioned above is involved in the tightly coupled SINS/GPS integration midcourse system design in which a set of low accuracy inertial components is shared by SINS and autopilot. Simulation results of a certain type of air to air missile are presented. Due to decorrelation by the tracking error estimator, only small white noise of pseudo range measurements remains. So it is shown that application of the new midcourse guidance system results in better guidance accuracy, higher jam resistance.展开更多
文摘为全面、准确、直观地发布实时航标助航信息,应用计算机网络技术、现代通信技术以及GPS,AIS,ECDIS和Web等关键技术,设计开发航标助航信息发布系统.该系统符合国际海事组织(International Maritime Organization,IMO)提出的数字航海战略框架,适应国际航标协会(Interna-tional Association of Lighthouse Authorities,IALA)现代航标发展方向,满足IALA有关推荐标准的要求.该系统实现基于图像建模与绘制(Image-Based Modeling and Rendering,IBMR)航标的360°航道全景图(虚拟三维)、基于遥感(Remote Sensing,RS)影像图的航标航道显示和基于自动识别系统(Automatic Identification System,AIS)的实体航标和虚拟航标信息显示等资料的综合显示功能.用户在互联网上借助通用的网络浏览器就可了解科学、全面、及时、准确、生动、直观的航标助航信息,从而提高海上交通安全指数和港口、船舶的营运效率.
文摘The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air to air missiles have been investigated recently. In comparison with those investigations existing in current publications, a new tightly coupled SINS/GPS integration navigation system for air to air missiles, based on the decorrelated pseudo range approach, is presented in this paper. Because of high jamming and dynamic of air to air missiles, inertial velocity aiding GPS receiver is used to provide a more accurate, jam resistant measurement for midcourse guidance systems. A tracking error estimator is designed to distinguish the correlation that existed between pseudo range measurements and inertial information. It is found better to regard inertial velocity aiding errors as the noise of which statistical properties are unknown. So using mixed Kalman/minimax filtering theory, one can obtain the new tracking error estimator with simple and robust algorithm through constructing a composite filter consisting of two parts: Kalman filter for the noise of known statistics and minimax filter for the unknown. In order to ensure this simple estimator stability, a new method is proposed to choose its parameters, based on Khargonekars work. Moreover, it is demonstrated that the given method also ensures the proposed estimator optimality. All the work mentioned above is involved in the tightly coupled SINS/GPS integration midcourse system design in which a set of low accuracy inertial components is shared by SINS and autopilot. Simulation results of a certain type of air to air missile are presented. Due to decorrelation by the tracking error estimator, only small white noise of pseudo range measurements remains. So it is shown that application of the new midcourse guidance system results in better guidance accuracy, higher jam resistance.
