GPS/BDS组合姿态测量及精度分析

给出了GPS/BDS组合双差观测模型和姿态测量解算算法,采用Kalman滤波进行动态基线解算的参数估计,利用LAMBDA方法固定双系统模糊度,获得动态基线固定解,最后通过基线的坐标系转换获得姿态角。比较了单系统和GPS/BDS双系统静态姿态角与动态短基线解算结果。试验结果表明,GPS/BDS组合姿态测量的精度和可靠性较GPS单系统都有显著提高。     

基于多导航系统的姿态测量及精度评估

基于卫星导航系统的姿态测量可作为一个新型姿态测量系统,代替传统昂贵的姿态测量设备,具有极大的应用潜力.本文首先介绍了利用卫星进行姿态测量的基本原理,在此基础上采用上海司南卫星导航技术股份有限公司的一块K728 GNSS OEM开发板和一块PCB板,设计了一个基于双天线的姿态测量系统,进行载体姿态测量的实验,并实现了PC机直接获取K728板卡实时解算的数据.最后,利用Matlab对测得的数据进行处理,评估了该开发板在测姿应用中的精度.实验结果表明,在系统正常工作的情况下,解算出的方位角精度高于0.2°/R(R为双天线基线长),俯仰角的精度高于0.4°/R.初步实验表明,该姿态测量系统可以应用在车辆自主驾驶控制以及飞行器、轮船的常规姿态测量.     

机载GPS自适应天线阵的测量结果

共形安装的机载GPS自适应天线阵的性能会受到阵列单元和飞机机身之间相互作用的影响。本文将介绍安装在比例为1：8的F－16飞机模型机身上的7单元微带贴片天线自适应阵列的设计和测量结果，以便评估这种天线阵与飞机间的相互作用及其在将多部宽带干扰机调零时对阵列性能的影响。自适应天线阵工作在12.6GHz的频率上，带宽为160MHz，分别是GPS L1频率和带宽的8倍。所有7个单元的远场天线方向图均在近场天线范围内的成比例频段上作了测量。为了更好地了解机体对天线方向图的影响，我们还将对隔离微带贴片单元测出的方向图与根据OSU－NEWAIR程序（code)计算出的天线方向图作了比较，OSU－NEWAIR程序使用均匀衍射理论来分析天线与机身间的相互作用。比较的结果表明，测量得的方向图和计算出的方向图之间具有良好的一致性。从这些缩比模型测量中收集的数据正在用来测试MITRE（麻省理工学院研究小组）开发的时空自适应调零算法在多部宽带干扰机相对飞机不同取向时的有效性。为了证明这种阵列在有两部窄带干扰机时使用简化直接矩阵求逆算法的调零能力，我们还进行了一些测量。测出的自适应阵列方向性图与理论上的预测十分吻合。文章还阐明了缩比模型测试的优点，以验证机载自适应阵列的调零性能。     

载波相位差分相对定位的模糊度求解

鉴于整周模糊度的求解是载波相位差分相对定位中的技术难点。详细介绍了载波相位差分相对定位的原理和整周模糊度的求解步骤,采用LAMBDA方法对一组静态短基线进行求解,并比较了模糊度浮点解和固定解以及基线的浮点解和固定解。实例证明,载波相位差分定位能够达到厘米级的定位精度。     

双星姿态测量中确定整周模糊度的新方法

针对双星姿态测量中整周模糊度解算这一关键问题,提出了一种新的双星整周模糊度解算方法--天线反转法.其基本思想是,在静态初始化过程中将副天线绕主天线反转了180°.模拟算例表明,该方法能够快速可靠地解算出双星整周模糊度.     

双星姿态测量中确定整周模糊度的新方法

针对双星姿态测量中整周模糊度解算这一关键问题,提出了一种新的双星整周模糊度解算方法——天线反转法。其基本思想是,在静态初始化过程中将副天线绕主天线反转了180°。模拟算例表明,该方法能够快速可靠地解算出双星整周模糊度。     

一种改进的加权整体最小二乘GNSS船姿估计方法

为提高GNSS船姿测量精度,该文构建了基于先验模糊度信息的乘性欧拉角GNSS载波观测方程,提出了一种基于部分变量误差模型(Partial-EIV)的加权整体最小二乘(WTLS)动态船姿估计方法。首先利用GNSS动对动加以基线长约束快速精确固定模糊度,然后将整周模糊度固定解作为已知值代入乘性姿态角载波观测误差方程,并将观测方程进行向量化;针对状态方程以及观测方程系数矩阵包含随机元素和固定元素的结构特征,引入Partial-EIV模型,采用一种改进目标函数的WTLS方法估计乘性欧拉角,该方法可以同时顾及状态方程以及观测方程误差,充分利用观测值以及姿态约束信息,减小误差累积。通过实测GNSS三天线匀速测姿算例对本文方法进行验证,结果表明,该文方法优于动态参考站差分(MBD)基线姿态直接解法,对于复杂海洋环境船姿测量具有一定的参考价值。     

北斗系统姿态测量中周跳探测与修复方法

针对姿态测量基于短基线精密相对定位,而观测值的周跳直接影响基线解算精度,将导致姿态解算结果数据质量下降的问题,提出了姿态测量应用中的周跳组合探测修复方法。文章在分析姿态解算原理及误差影响程度的基础上,结合经典电离层残差法和多项式拟合法,探讨其在北斗卫星导航系统中周跳探测修复的方法原理、缺陷及对北斗数据探测修复效果,结合实际情况提出了姿态测量应用中的组合探测修复方法。采集真实数据实时解算,定量计算了修复后的基线解算精度和姿态测量效果,验证了所提出的方法可用于实际测量解算,处理后的姿态测量精度满足使用需求,研究结果对北斗姿态解算有参考价值。     

陆地导航中GNSS/陀螺仪组合实时测姿方法

在陆地导航系统中使用GNSS/INS组合导航会增加系统成本,多天线GNSS测姿精度受基线长度影响,且存在的模糊度固定问题。本文提出仅利用一个陀螺仪和单天线GNSS组合来进行实时测姿。先由单天线GNSS计算姿态角3参数,航向角为陆地导航的关键参数,为此将陀螺信息与GNSS导出的航向角进行融合。分析了单天线测姿在载体静止或低速运动时精度很差的原因,提出了在组合滤波中进行解决的方案。推导了GNSS和陀螺信息融合的滤波模型,将陀螺仪信息作为状态模型的控制输入,以GNSS航向为滤波观测值。实验结果表明,GNSS/陀螺仪组合计算的航向角精度和可靠性相对GNSS测姿结果均有很大提升。     

一种实时GPS姿态测量中的整周模糊度的解算方法

GPS实时姿态测量的核心问题是整周模糊度的解算.提出一种适合实时姿态测量的模糊度解算方法,它利用单差平滑伪距进行解算,与传统的模糊度解算方法相比具有许多优点.通过仿真试验对该方法的有效性和实用性进行了验证.     

GNSS调零抗干扰天线的反欺骗性能分析

为分析全球卫星导航系统(GNSS)中存在欺骗干扰的场景下调零抗干扰天线的反欺骗性能,推导出在快拍数有限的情况下,功率倒置(PI)算法利用调零天线处理后输出真实信号和欺骗信号功率的理论公式. 详细分析了欺骗信号到达天线阵口面的功率对真实信号和欺骗信号输出功率的影响,通过欺骗抑制比这一指标来衡量PI自适应调零天线的反欺骗性能. 分析得出:即使欺骗信号功率在噪声水平之下,使用PI算法的自适应调零抗干扰接收机依然能对欺骗干扰进行抑制,在欺骗信噪比高时,抑制效果更加明显. 最后通过仿真和硬件平台实测验证了结论的正确性.      

The affine constrained GNSS attitude model and its multivariate integer least-squares solution

A new global navigation satellite system (GNSS) carrier-phase attitude model and its solution are introduced in this contribution. This affine-constrained GNSS attitude model has the advantage that it avoids the computational complexity of the orthonormality-constrained GNSS attitude model, while it still has a significantly improved ambiguity resolution performance over its unconstrained counterpart. The functional and stochastic model is formulated in multivariate form, for one-, two- and three-dimensional antenna arrays, tracking GNSS signals on an arbitrary number of frequencies with two or more antennas. The stochastic model includes the capability to capture variations in the antenna-quality within the array. The multivariate integer least-squares solution of the model parameters is given and the model’s ambiguity success-rate is analysed by means of the ambiguity dilution of precision (ADOP). A general closed-form expression for the affine-constrained ADOP is derived, thus providing an easy-to-use and insightful rule-of-thumb for the ambiguity resolution capabilities of the affine constrained GNSS attitude model.     

Integer least-squares theory for the GNSS compass

Global navigation satellite system (GNSS) carrier phase integer ambiguity resolution is the key to high-precision positioning and attitude determination. In this contribution, we develop new integer least-squares (ILS) theory for the GNSS compass model, together with efficient integer search strategies. It extends current unconstrained ILS theory to the nonlinearly constrained case, an extension that is particularly suited for precise attitude determination. As opposed to current practice, our method does proper justice to the a priori given information. The nonlinear baseline constraint is fully integrated into the ambiguity objective function, thereby receiving a proper weighting in its minimization and providing guidance for the integer search. Different search strategies are developed to compute exact and approximate solutions of the nonlinear constrained ILS problem. Their applicability depends on the strength of the GNSS model and on the length of the baseline. Two of the presented search strategies, a global and a local one, are based on the use of an ellipsoidal search space. This has the advantage that standard methods can be applied. The global ellipsoidal search strategy is applicable to GNSS models of sufficient strength, while the local ellipsoidal search strategy is applicable to models for which the baseline lengths are not too small. We also develop search strategies for the most challenging case, namely when the curvature of the non-ellipsoidal ambiguity search space needs to be taken into account. Two such strategies are presented, an approximate one and a rigorous, somewhat more complex, one. The approximate one is applicable when the fixed baseline variance matrix is close to diagonal. Both methods make use of a search and shrink strategy. The rigorous solution is efficiently obtained by means of a search and shrink strategy that uses non-quadratic, but easy-to-evaluate, bounding functions of the ambiguity objective function. The theory presented is generally valid and it is not restricted to any particular GNSS or combination of GNSSs. Its general applicability also applies to the measurement scenarios (e.g. single-epoch vs. multi-epoch, or single-frequency vs. multi-frequency). In particular it is applicable to the most challenging case of unaided, single frequency, single epoch GNSS attitude determination. The success rate performance of the different methods is also illustrated.     

基于GNSS天线阵列的定姿方法研究

针对车载移动测量系统对运动载体姿态的确定,研究车载全球卫星导航系统(GNSS)天线阵列定姿方法,分析直接法和最小二乘法定姿的姿态解算公式,并进行GNSS天线阵列车载实验. 为得到两种定姿方法的精度,在不同软件定位模式解算的基础上,利用直接法和最小二乘法进行了姿态解算. 实验和分析结果表明:四天线阵列最小二乘法定姿精度优于三天线阵列直接法,可靠性更高;在所有组合中,基于Moving-base定位模式的四天线阵列最小二乘法定姿精度最高,其航向角、俯仰角和横滚角精度分别可达0.066 0°、0.168 4°和0.267 8°.      

New method for single epoch, single frequency land vehicle attitude determination using low-end GPS receiver

Stand-alone, unaided, single frequency, single epoch attitude determination is the most challenging case of GNSS compass processing. For land vehicle applications, the baseline approximately lies in the plane of the local geodetic horizon. This provides an important constraint that can be exploited to directly aid the ambiguity resolution process. We fully integrate the constraint into the observation equations, which are transformed orthogonally. Our method can acquire the high-quality float solution by means of a heading search strategy. The fixed solution is obtained by weighted constrained integer least squares for each possible heading. The correct solution is identified by three consecutive steps: Kolmogorov?CSmirnov test, heading verification, and global minimizer of the fixed ambiguity objective function. The analysis focuses on single frequency, single epoch land vehicle attitude determination using low-end GPS receivers with very low precision of carrier phase and code measurements. The error analysis is given for choosing a proper baseline length in practical application. Experimental results demonstrate that this scheme can improve the ambiguity success rate for very short baseline.     

Single-frequency L5 attitude determination from IRNSS/NavIC and GPS: a single- and dual-system analysis

The Indian Regional Navigation Satellite System (IRNSS) has recently (May 2016) reached its full operational capability. In this contribution, we provide the very first L5 attitude determination analyses of the fully operational IRNSS as a standalone system and also in combination with the fully operational GPS Block IIF along with the corresponding ambiguity resolution results. Our analyses are carried out for both a linear array of two antennas and a planar array of three antennas at Curtin University, Perth, Australia. We study the noise characteristics (carrier-to-noise density, measurement precision, time correlation), the integer ambiguity resolution performance (LAMBDA, MC-LAMBDA) and the attitude determination performance (ambiguity float and ambiguity fixed). A prerequisite for precise and fast IRNSS attitude determination is the successful resolution of the double-differenced integer carrier-phase ambiguities. In this contribution, we will compare the performance of the unconstrained and the multivariate-constrained LAMBDA method. It is therefore also shown what improvements are achieved when the known body geometry of the antenna array is rigorously incorporated into the ambiguity objective function. As our ambiguity-fixed outcomes show consistency between empirical and formal results, we also formally assess the precise attitude determination performance for several locations within the IRNSS service area.     

Testing of a new single-frequency GNSS carrier phase attitude determination method: land,ship and aircraft experiments

Global navigation satellite system (GNSS) ambiguity resolution is the process of resolving the unknown cycle ambiguities of the carrier phase data as integers. The sole purpose of ambiguity resolution is to use the integer ambiguity constraints as a means of improving significantly on the precision of the remaining GNSS model parameters. In this contribution, we consider the problem of ambiguity resolution for GNSS attitude determination. We analyse the performance of a new ambiguity resolution method for GNSS attitude determination. As it will be shown, this method provides a numerically efficient, highly reliable and robust solution of the nonlinearly constrained integer least-squares GNSS compass estimators. The analyses have been done by means of a unique set of extensive experimental tests, using simulated as well as actual GNSS data and using receivers of different manufacturers and type as well as different platforms. The executed field tests cover two static land experiments, one in the Netherlands and one in Australia, and two dynamic experiments, a low-dynamics vessel experiment and high-dynamics aircraft experiment. In our analyses, we focus on stand-alone, unaided, single-frequency, single-epoch attitude determination, as this is the most challenging case of GNSS compass processing.     

零基线约束的参考站间模糊度固定方法研究

论文提出一种GNSS零基线约束的参考站间模糊度快速固定方法,该方法基于“一天线+双接收机”设计进行参考站间模糊度固定。首先,利用两个参考站四台接收机观测值形成四对参考站间无电离层组合双差观测值。其次,结合无电离层组合观测值模糊度和宽巷整周模糊度进行卡尔曼滤波和N1模糊度实数解计算。然后在模糊度域内进行线性变换,单历元固定零基线模糊度;利用零基线模糊度约束解算四组参考站间模糊度中的一组模糊度。最后,利用固定的模糊度还原所有原始双差整周模糊度。实验证明:与传统参考站间模糊度固定方法比,充分利用了零基线模糊度固定的约束条件进行参考站间模糊度固定,加快了模糊度收敛速度,极大地提高了模糊度固定的速度和成功率。      

热膨胀效应对GNSS短基线坐标时间序列影响研究

天线观测墩及基岩的热膨胀效应会造成全球卫星导航系统(GNSS)基准站坐标时间序列非线性变化,本文利用长期观测数据评估了热膨胀效应对GNSS短基线时间序列周期特性的影响. 结果表明:热膨胀效应在高程上可以引起约1 mm的季节性周年信号,可以很好地解释GNSS短基线时间序列中的周期信号,而对平面方向的贡献不大,但是观测墩因日光照射受热不均产生的热弯曲对平面方向上的影响应予以考虑.