ATTITUDE RATE ESTIMATION BY GPS DOPPLER SIGNAL PROCESSING

A method is presented for near-Earth spacecraft or aviation vehicle‘s attiude rate cstimation by using relative Doppler frequency shift of the Global Positioning System(GPS)carrier.It comprises two GPS receiving antennas,a signal processing circuit and an algorithm.The whole system is relatvely simple,the cost and weight,as well power consumption,are very low.     

对角加载对信号源数检测性能的改善

对角加载技术可抑制小特征值对自适应权值的影响来加速自适应波束形成器的收敛性以及抑制导向矢量误差的影响避免信号相消,该技术通常用于稳健的波束形成算法.基于对角加载技术,本文提出了一种信号源数目判定的改进方法,通过对角加载数据协方差阵,可以平滑小快拍数和空间色噪声时的噪声特征值分散程度从而减轻其对信号源数目估计的影响,证明了该估计器的强一致性,分析了加载量对信号源数目估计的影响.最后通过仿真以及实测数据比较了本文方法和已有方法的性能,验证了所提方法的有效性.     

GPS-BASED LEO SATELLITE POSITION AND ATTITUDE DETERMINATION AUGMENTED BY PSEUDOLITES ON EARTH

GPS-based navigation and attitude determination of LEO satellites is presently considered as an alternative to the conventional systems which utilize earth sensors and magnetometers. The onboard GPS receiver determines the orbit position of the LEO satellite by the conventional system of linearized navigation equations, requiring the simultaneous reception of ranging signals from four GPS satellites by a single antenna. For attitude determination, pairs of antennae, suitably mounted on the satellite and feeding a common receiver, form several interferometric baselines. The baselines vectors, defined in a given coordinate system, determine the attitude of the satellite. For each baseline and each GPS satellite, the difference in phase of the received signal carriers is measured. The differencing operation eliminates the receiver clock bias. Solutions for the baseline vectors can be obtained with signals received from only three GPS satellites. If the coverage of a receive antenna is restricted to less than the hemisphere it will not have four GPS satellites in view all the time. It is demonstrated that a GPS pseudolite transmitter located on earth supplements the system, which then provides a usable geometric dilution of precision (GDOP) for position determination and an improved position dilution of precision (PDOP) for attitude determination. Pseudolites can be co-located with the gateways which provide access to the public switched telephone networks (PSTNs) for the LEO communication satellites.     

Satellite attitude determination based on GPS signal-to-noise ratio

A method is presented for coarse attitude determination using the Global Positioning System (GPS) signal-to-noise ratio (SNR) from a single antenna mounted on a near-Earth satellite. It comprises a calibration procedure and a single-point optimal solution for the orientation of the antenna boresight vector. The calibration step creates an empirical mapping of the SNR to the angle between the antenna boresight and the GPS line-of-sight vector, based upon a ground or flight data set. The rms attitude accuracy at the level of 3°-10° is demonstrated with actual flight data from several spacecraft. Performance is shown to depend strongly on the number of GPS signals available and the quality of the calibration mapping function. The method is suitable as a backup attitude sensor for low-cost satellite and terrestrial applications, and as a coarse reference for ambiguity resolution and integrity verification of phase-based GPS attitude-determination algorithms     

The measurement of a large antenna using a spacecraft as a receiver

Two computational methods for obtaining the gain pattern of a large antenna using power levels recorded by a spacecraft are developed from the transmission equation. Nominally, the large antenna is linearly polarized while the spacecraft's receiving antennas are circularly polarized. Since the spacecraft has no attitude control system, the orientation of the receiving antennas is not known a priori nor its orientation the same from orbit to orbit. The first method relies on an independent spacecraft attitude determination system to furnish the orientation of the receiving antennas. It combines this information with receiving-antenna gain measurements to give the power level of the incident radiation. Losses due to polarization mismatch are taken into account, but polarization loss factors are not actually computed. The second method relates simultaneous measurements made by separate channels with separate receiving antennas. By solving a system of equations numerically, one can determine the direction of the incident radiation as well as its power level. This alleviates the need for an attitude determination system. These methods originated in the operations of the spacecraft NUSAT1 (northern Utah Satellite)     

Algorithm of SAR satellite attitude measurement using GPS aided by kinematic vector

In this paper,in order to improve the accuracy of the Synthetic Aperture Radar (SAR) satellite attitude using Global Positioning System (GPS) wide-band carrier phase,the SAR satellite attitude kinematic vector and Kalman filter are introduced.Introducing the state variable function of GPS attitude determination algorithm in SAR satellite by means of kinematic vector and describing the observation function by the GPS wide-band carrier phase,the paper uses the Kalman filter algorithm to obtian the attitude variables of SAR satellite.Compared the simulation results of Kalman filter algorithm with the least square algorithm and explicit solution,it is indicated that the Kalman filter algorithm is the best.     

Baseline Influence on Single-Frequency GPS Precise Heading Estimation

When using the signal from the Global Positioning System (GPS) for precise estimation of a vehicle’s heading, the main challenge is finding the integer ambiguities in the carrier phase measurements. If the distance between the receiver’s antennas, also known as baseline length, is used in the process of solving that challenge, the resulting solution’s stability and precision can be enhanced, particularly for single-frequency L1 receivers. This paper presents a study of the overall influence of this baseline length in the precision and accuracy of the heading estimation, using raw measurements from two GPS single-frequency L1 receivers. Conclusions are presented based on the results from field trials for baselines up to 8 m.     

基于载体姿态的GPS信号模拟器

GPS姿态测量技术是根据安装在载体上的多天线阵所确定的基线平面来推算出载体的航向及姿态原理。通过将载体姿态信息反映在其多天线阵接收信号状态上,并形成测姿所用的观测文件,以实现对测姿接收机在各种环境条件下的灵活测试。提出了GPS姿态信号模拟的原理设计方案,同时进行了建模与仿真分析,包括从姿态信号生成模拟、多天线阵定位解算到载体姿态解算的一系列完整过程。仿真结果表明,三维姿态角标准差都在0.2°以下,符合实际情况。     

一种基于载波相位时间差分的惯性/卫星组合方法

传统的惯性/卫星紧耦合组合导航系统使用卫星伪距/伪距率作为量测，卫星伪距率一般可以提供厘米/秒级精度的速度信息；而载波相位时间差分观测量可以达到毫米级精度且无需参考接收机。本文分析了载波相位时间差分的原理，并将其应用到惯性/卫星组合导航系统中；在滤波器的设计中使用状态延迟滤波法处理载波相位时间差分观测量，使惯性/卫星组合导航系统达到了较高的速度精度。     

INS辅助GPS载波跟踪环分析

高动态环境会造成较大的多普勒频移,这使得一般的GPS接收机在没有外界辅助的情况下难以可靠工作.为了同时满足高动态GPS接收机动态性能和噪声抑制两方面的需要,GPS/INS紧耦合系统利用INS的信息辅助GPS接收机的载波跟踪回路.对紧耦合系统的关键技术--INS辅助GPS载波跟踪回路进行了系统分析,阐述了INS信息辅助G...     

一种靶船航向、姿态测量与定位、授时的方法与实现

讨论了用航向、姿态测量装置实现靶船航向、姿态测量和用GPS接收机实现靶船定位、授时的方法，并互利用它们构建了硬件平台。最后，给出了系统总体设计框图，并对系统功能的实现和工作过程进行了详细介绍。     

GPS卫星导航系统多频姿态测量技术研究

GPS全球卫星导航系统现代化工作,为多频姿态测量接收机的研制提供了基础条件。针对低轨卫星、导弹、飞机和舰艇等平台对姿态测量的使用需求,给出了由天线单元、测量单元和姿态解算单元构成的多频姿态测量接收机总体方案。研究了基于GPS多频组合噪声残差法实时探测与修复周跳、基于几何约束的单历元模糊度解算等关键技术,并给出了详细的计算方程和流程。对GPS单频定姿接收机和多频定姿接收机进行静态试验,证明后者在测姿精度和解算成功率方面都优于前者。     

Smart framework for GNSS‐based navigation in urban environments

Intelligent Transport System applications require accurate and reliable positioning. When stand‐alone global positioning system (GPS) is used in urban areas, the results dramatically degrade, because of signal outages and multipath. This paper unveils new signal processing techniques for carrier phase‐based navigation in urban environments. The techniques identify multipath or weak signals using carrier phase based receiver autonomous integrity monitoring, and abnormal signals and situational measurements are eliminated or estimated. To estimate the carrier phase during a short time period when GPS signals is blocked, this paper uses carrier phase statistics. The performance of the proposed method is verified, through a car test. The test environment has many signal outages and multipath because of high buildings. Many abnormal signal conditions occurred during the test, and the results confirmed that the proposed method performed better than the basic stand‐alone GPS approach when compared with GPS/inertial navigation system (INS) integrated navigation results. Copyright © 2015 John Wiley & Sons, Ltd.     

Range errors in global positioning system during ice cloud andsnowfall periods

Results from a global positioning system (GPS) measurement campaign conducted during March 1989 on a baseline of 13.1415 km length show a relatively large discrepancy in the adjusted baseline height component during ice cloud and snowfall periods. These experimental observations have stimulated the development of a propagation-prediction model to investigate the performance of GPS carrier beat phase measurements during ice cloud (predominantly present above the freezing level) and snowfall precipitation periods. Theoretical results revealed that even for extremely high ice cloud volume concentrations and for snowfall rates up to 20 mm/h the estimated phase delay, if identical at the two receiver sites, has negligible effect on the recovery of the vector baseline components. However, due to the localized nature of many snow storms and the nonuniform spatial cover of ice clouds, the differential effects between two distant receiver sites can become important for precise relative GPS applications. Finally, the model demonstrates that a differential phase delay of about 4.6° at zenith which is to be expected under adverse storm conditions may explain the range of experimentally observed discrepancies in the relative baseline height component     

Mobile GPS carrier phase tracking using a novel intelligent dual‐loop receiver

Carrier phase information is necessary for accurate measurements in global positioning system (GPS) applications. This paper presents a novel intelligent GPS carrier tracking loop with variable‐bandwidth characteristics for fast acquisition and better tracking capability in the presence of dynamic environments. Our dual‐loop receiver is composed of a frequency‐locked loop‐assisted phase‐locked loop structure, the fuzzy controllers (FCs), and the ATAN discriminator functions. The soft‐computing FCs provide the time‐varying loop gains to perform accurate and reliable control of the dual‐loop paradigm. Once the phase dynamic errors become large under kinematic conditions, the fuzzy loop gains increase adaptively and achieve rapid acquisition. On the other hand, when the tracking errors approach zero in the steady state, the loop gains decrease and the corresponding dual‐loop receiver returns to a narrowband system. Four types of carrier phase signals, i.e. phase offset, decaying sinusoidal phase jitter, frequency offset, and frequency ramp offset, are considered to emulate realistic mobile circumstances. Simulation results show that our proposed receiver does achieve a superior performance over conventional tracking loops in terms of faster settling time and wider acquisition range while preventing the occurrence of cycle slips. Copyright © 2008 John Wiley & Sons, Ltd.     

基于DSP的GPS双天线实时姿态测量系统实现

实现了基于DSP的GPS双天线实时姿态测量系统，采用Kalman滤波估计载体的位置，速度和初始模糊值搜索距离，然后采用FASF和LAMBDA解算整周模糊度和直接法计算载体的姿态。给出了基于DSP的硬件实现，相对于传统的模糊度解算方法，所采用的整周模糊度解算方法具有效率更高，更便于实时和动态应用的特点，实现了与多天线GPS姿态测量系统相当的精度。对GPS姿态测量技术的工程应用和理论研究具有一定的参考价值。     

GPS接收机载波跟踪环设计与分析

针对GPS接收机载波跟踪环环宽与跟踪的动态性能问题,在分析影响GPS信号动态性能的主要参数热噪声、晶振Allan相位噪声、晶振振动相位噪声和动态应力的基础上,通过对不同阶数的锁相环、锁频环跟踪门限分析与仿真,主要解决了如何设计GPS接收机的载波跟踪环路的带宽,并使系统性能达到最佳的问题,即使用环宽为18 Hz的二阶锁相环辅助环宽为10 Hz的三阶锁频环可以跟踪动态范围小于10 g、100 g/s的高动态信号。     

GNSS/INS组合导航在飞行校验系统中的应用

目前的飞行校验系统以 GPS 作为空间基准,这种定位方式在精度、性能、可靠性方面都存在着固有缺陷。本文介绍的同步定位-姿态-导航(SPAN,Synchronous Position,Attitude and Navigation)技术集合了两种不同但互补的技术：全球导航卫星系统(GNSS,Global Navigation Satellite System)定位技术和惯性导航技术。通过二者的结合,SPAN 技术可以达到取长补短的目的,组合后的导航系统无论在精度、性能、可靠性方面都优于单独的子系统。将这项技术应用于飞行校验系统,利用 GNSS 定位的绝对精度加上惯性测量单元(IMU)陀螺和加速计测量的稳定性,就可以在卫星信号丢失或者高动态应用环境下仍然提供持续、稳定、可靠的位置及姿态数据。     

Comparison of wide-laning and tone-ranging

Satellite navigation today is based on range determination. Accurate range measurements require the use of carrier phase measurements which are ambiguous. Numerous ingenious methods have been developed to resolve GPS ambiguities. A comparison is made of two different principles for obtaining robust ambiguity resolution in real time in a future system     

基于软件GPS接收机的最小二乘定向技术研究

利用GPS进行载体航向的确定,需要从整周模糊度解算和航向解算两个方面进行处理。采用改进的最小二乘解算整周法,并利用在GPS软件接收机,对真实卫星数据进行了处理,通过对航向角精度进行分析,对比不同基线长度时的定向结果,证明了该方法的有效性。