一种GPS定位信息可用性的实时判定方法

基于GPS接收机输出数据,采用3级AR模型来预测下一时刻的GPS输出值,并与实际的输出值相比较,以一定的检测门限,判断当前时刻定位信息的可用性。通过仿真证明该方法的有效性,为GPS的可用性判定提供了一种方法。     

干扰精确制导导弹方法的研究

在海湾战争、科索沃战争及不久前的伊拉克战争中 ,精确制导导弹是美国远程空中打击力量的重要组成部分 ,对一些重大军事、通信目标进行了强有力的摧毁。美军的精确制导导弹发挥了重大作用 ,只要没有干扰 ,可实施对目标的“弹无虚发、百发百中”。因而研究如何对其实施有效干扰将对提高军事、通信等目标的生存能力具有重要意义。针对其特点 ,进行了详细分析 ,并提出了一些有效的干扰方法     

无人机下滑着陆DGPS/INS导航及引导系统的仿真与试验研究

介绍了一种采用输出校正方式DGPS/INS组合导航系统引导无人机下滑着陆的方案。给出了该方案的数学模型,对组合导航系统进行了数字仿真,并在数字仿真的基础上进行了动态跑车试验,验证了所设计的输出校正方式DGPS/INS组合导航系统能够满足引导无人机自动下滑着陆的精度要求。     

Coordinated in situ measurements of plasma irregularities and ground based scintillation observations at the crest of equatorial anomaly

First comparison of in situ density fluctuations measured by the DEMETER satellite with ground based GPS receiver measurements at the equatorial anomaly station Bhopal (geographic coordinates (23.2°N, 77.6°E); geomagnetic coordinates (14.29°N, 151.12°E)) for the low solar activity year 2005, are presented in this paper. Calculation of the diurnal maximum of the strength of the equatorial electrojet, which can serve as precursor to ionospheric scintillations in the anomaly region is also done. The Langmuir Probe experiment and Plasma Analyzer onboard DEMETER measure the electron and ion densities respectively. Irregularities in electron density distribution cause scintillations on transionospheric links and there exists a close relationship between an irregularity and scintillation. In 40% of the cases, DEMETER detects the irregularity structures (dNe/Ne ? 5% and dNi/Ni (O⁺) ? 5%) and GPS L band scintillations (S4 ? 0.2) are also observed around the same time, for the low solar activity period. It is found that maximum irregularity intensity is obtained in the geomagnetic latitude range of 10–20° for both electron density and ion density. As the GPS signals pass through this irregularity structure, scintillations are recorded by the GPS receiver installed at the equatorial anomaly station, Bhopal it is interesting to note that in situ density fluctuations observed on magnetic flux tubes that pass over Bhopal can be used as indicator of ionospheric scintillations at that site. Many cases of density fluctuations and associated scintillations have been observed during the descending low solar activity period. The percentage occurrence of density irregularities and scintillations shows good correspondence with diurnal maximum of the strength of electrojet, however this varies with different seasons with maximum correspondence in summer (up to 66%) followed by equinox (up to 50%) and winter (up to 46%). Also, there is a threshold value of EEJ strength to produce density irregularities ((dNe/Ne)_max ? 5%) and for moderate to strong scintillations (S4 ? 0.3) to occur. For winter this value is found to be ∼40 nT whereas for equinox and summer it is around 50 nT.     

GPS/SINS超紧组合导航的性能分析

GPS接收机在高动态环境下很容易失锁,特别是载体的高动态造成的应力对接收机载波跟踪环影响很大。为了解决高动态环境下的组合导航,分析了GPS接收机载波跟踪环的测量误差和跟踪门限,采用惯导速度辅助GPS接收机跟踪环路的超紧组合结构。超紧组合需要涉及到GPS接收机跟踪环内部编排及高动态环境下的实验数据,难度较大。针对超紧组合仿真专门开发了GPS实时软件接收机、高动态GPS中频信号仿真器和惯导模拟器并构建了一个完整的GPS/SINS超紧组合仿真系统。仿真结果表明,该超紧组合导航系统可以跟踪50g的加速度和10倍音速。     

发射系下SINS/GPS/CNS组合导航系统联邦粒子滤波算法

传统的扩展卡尔曼滤波(Extended Kalman filter, EKF)算法应用于未来高超、空天飞行器的组合导航系统时,因其模型线性化展开会导致模型不准确,从而引起导航精度下降;采用蒙特卡洛方法来实现递推贝叶斯估计问题的粒子滤波(Particle filter,PF)算法能有效避免引入线性化误差,具有一定的优势。据此,针对高超、空天飞行器在发射过程中通常需要直接获得发射惯性系下的高精度导航参数的需求,提高发射惯性系下弹载组合导航系统滤波算法的精确性就尤为重要,PF滤波算法无需对非线性系统进行线性化展开即可直接实现对非线性系统的状态误差估计。为此,本文将PF滤波算法引入空天飞行器SINS/GPS/CNS多信息融合组合导航系统,设计了发射系下基于联邦滤波器的PF滤波算法,实现了对组合导航系统状态参数的直接建模估计。算法仿真结果表明,相较于发射系下SINS/GPS/CNS组合导航系统联邦EKF滤波算法,PF滤波算法有效提高了组合导航系统滤波精度。