船用平台式INS光学标校初始对准方法研究

为了解决航海型平台式惯性导航系统（INS）非自主式初始对准问题，建立了不同观测量条件下统一的INS初始对准方程。通过系统可观测性分析，得出增加外部姿态角的观测信息将有效提高INS平台失准角和惯性元件误差的估计能力的结论。设计出一种独特的可测量低动态载体两维姿态的高精度光学测量系统（OCS）用以提高航海型平台式INS初始对准精度。建立OCS／GPS／计程仪（LOG）／INS初始对准卡尔曼滤波器，并进行了基于部分试验数据的数字仿真，与传统的基于位置和速度的GPS／LOG／INS初始对准方法相比，基于OCS的系统不仅缩短了对准时间，还有效改善了系统惯性元件的误差估计精度。     

支持虚拟企业组建的DSS与CSCW集成框架

针对虚拟企业组建过程复杂, 需要决策支持系统支持的 特殊情况， 分析了CSCW对DSS的制约, 利用CSCW提供的多种技术和工具支持虚拟企业组建决策, 提出一种CSCW与DSS的集成框架. 并通过对集成框架进行评估与分析发现， 该方法是高效、 可行的.     

GPS/INS在火车安全告警系统中的应用

为了弥补目前火车车辆运行中人工统计调度工作量大、效率低等缺陷，提出了一种基于全球定位系统和惯性导航技术(GPS／INS)的火车安全告警系统的设计方案；重点讨论了GPS／INS在信息融合时所使用的卡尔曼滤波方法，避免了独立的惯性导航系统无限位置误差和GPS的1Hz慢速数据修正的问题；利用原有国家铁路网数据库进行数据修正，进一步提高了系统的精度．在此基础上设计的火车安全告警系统就能够简捷、准确地计算车辆运行里程，当车辆达到维修等级时自动进行报警提示，从而降低火车车辆调度工作的工作量及运行风险．     

中国公司治理的路径依赖——理论与实证分析

1Introduction　Now ,in orbitspacecraftsdeveloprapidlyinqualityandquantity,whilethegroundTT&Cresourceisrelativelylimi ted .Therefore ,torealizespacecraftautonomousnavigationandpositioningseemsespeciallytobeimportant.Itisoneoftheimportantaspectstoincreasethein orbitspacecraftself containedability .　ExtensiveattentionshavebeenpaidtotheapplicationofGPSinthisarea,andquiteanumberofachievementshavebeengained ,butitisonlythebeginning .　FortheutilizationofGPSinspacecraftnavigationandpo sitioning …     

面向海上移动目标的空天协同连续观测模型

由于视距限制,对海上移动目标进行连续观测与定位探测难度较大.现有方法通过卫星和无人机等单平台对目标进行观测,不能解决面向海上移动目标连续观测的问题.针对当前单个平台的不足,本文构建了面向海上移动目标的空天协同连续观测模型,并提出了空天协同连续观测策略.空天协同连续观测策略抽取出卫星规划、无人机飞行计划、观测序列、区域预测以及路径规划等五个子问题,并对其进行建模求解.仿真实验表明,该方法大大降低了目标的平均观测周期,有效解决了海上移动目标连续观测问题.     

满足客流需求的地铁列车延误协同调整方法

以尽快疏散客流为出发点,提出协同调整城市轨道交通初始延误列车前方列车的方法.基于列车能力与客流需求的交互关系、运行约束和调整时间约束,协调考虑车内乘客和站台乘客,以全部乘客总旅行时间最小为目标建立了整数规划模型,并构建多列车、多车站时刻调整的组合动态规划求解算法.实例验证结果表明了模型与算法的有效性,与其他方法相比,该协同调整方法得到了更少的乘客旅行时间.     

旋转弹引信用卫星定位接收信号旋转解调方法

为解决旋转弹飞行中的高旋转、高动态条件会造成卫星定位接收系统无法正常定位的问题,针对旋转、动态环境开展了旋转弹卫星定位接收信号旋转解调方法的研究.详细分析了旋转条件对卫星定位信号接收的影响,并针对旋转特性设计了旋转跟踪解调环,用于对旋转的跟踪与解调,给出了旋转弹卫星定位信号接收系统的设计方案,基于Simulink实现了旋转弹卫星定位信号接收系统的仿真,并给出了相应的仿真与实验结果.结果表明,设计的以旋转跟踪环为核心的旋转弹卫星定位信号接收系统,在中心频率为200 Hz的情况下跟踪范围可达到±40 Hz,较好地满足了转速在200转/s左右的旋转弹信号接收要求.      

New rapid transfer alignment method for SINS of airborne weapon systems

Transfer alignment is an effective alignment method for the strapdown inertial navigation system （SINS） of airborne weapon systems. The traditional transfer alignment methods for large misalignment angles alignment use nonlinear transfer align- ment models and incorporate nonlinear filtering. A rapid transfer alignment method with linear models and linear filtering for ar- bitrary misalignment angles is presented. Through the attitude quaternion decomposition, the purpose of transfer alignment is converted to estimate a constant quaternion. Employing special manipulations on measurement equation, velocity and attitude linear measurement equations are derived. Then the linear trans- fer alignment model for arbitrary misalignment angles is built. An adaptive Kalman filter is developed to handle modeling errors of the measurement noise statistics. Simulation results show feasibili- ty and effectiveness of the proposed method, which provides an alternative rapid transfer alignment method for airborne weapons.     

中俄（NSFC-RFBR）基础研究合作现状分析和未来合作展望

本文回顾了2003—2012年中俄（NSFC-RFBR）双边合作项目的背景、类别与机制。对双边合作交流项目和双边研讨会项目资助情况进行了统计分析,总结了项目资助成果。针对存在的问题与不足进行了思考,并对加强双方未来合作的途径提出了若干建议。为双方进一步提升合作水平,促进实质性双边合作提供了信息参考。     

Self-alignment of full skewed RSINS：observability analysis and full-observable Kalman filter

Traditional orthogonal strapdown inertial navigation sys-tem （SINS） cannot achieve satisfactory self-alignment accuracy in the stationary base： taking more than 5 minutes and al the iner-tial sensors biases cannot get ful observability except the up-axis accelerometer. However, the ful skewed redundant SINS （RSINS） can not only enhance the reliability of the system, but also improve the accuracy of the system, such as the initial alignment. Firstly, the observability of the system state includes attitude errors and al the inertial sensors biases are analyzed with the global perspective method： any three gyroscopes and three accelerometers can be assembled into an independent subordinate SINS （sub-SINS）;the system state can be uniquely confirmed by the coupling connec-tions of al the sub-SINSs;the attitude errors and random constant biases of al the inertial sensors are observable. However, the ran-dom noises of the inertial sensors are not taken into account in the above analyzing process. Secondly, the ful-observable Kalman filter which can be applied to the actual RSINS containing random noises is established; the system state includes the position, ve-locity, attitude errors of al the sub-SINSs and the random constant biases of the redundant inertial sensors. At last, the initial self-alignment process of a typical four-redundancy ful skewed RSINS is simulated： the horizontal attitudes （pitch, rol ） errors and yaw error can be exactly evaluated within 80 s and 100 s respectively, while the random constant biases of gyroscopes and accelero-meters can be precisely evaluated within 120 s. For the ful skewed RSINS, the self-alignment accuracy is greatly improved, mean-while the self-alignment time is widely shortened.