Determining Attitude and Position in Deep Space Missions Using X Ray Pulsars

This paper initially reviews types of deep space navigation methods. Then, it studies the use of pulsars as one of sources emitting electromagnetic waves in navigation;hence more details regarding the pulsar physics and the history of navigation using pulsars are presented. The various methods of navigation (including radio method), their advantages and disadvantages—in comparison with navigation using pulsars in spacecraft—are discussed. Then, the equations necessary for calculating position and velocity of a spacecraft (such as the arrival time of pulse from pulsar to the receiver) are introduced, and the methods of calculating position and velocity are dealt with. Finally, two algorithms are presented for positioning, and one for velocity. Attitude determination follows the same simple methods presented in various articles.

Estimation of Quaternion Motion for GPS-Based Attitude Determination Using the Extended Kalman Filter

In this paper,the Global Positioning System(GPS)interferometer provides the preliminarily computed quaternions,which are then employed as the measurement of the extended Kalman filter(EKF)for the attitude determination system.The estimated quaternion elements from the EKF output with noticeably improved precision can be converted to the Euler angles for navigation applications.The aim of the study is twofold.Firstly,the GPS-based computed quaternion vector is utilized to avoid the singularity problem.Secondly,the quaternion estimator based on the EKF is adopted to improve the estimation accuracy.Determination of the unknown baseline vector between the antennas sits at the heart of GPS-based attitude determination.Although utilization of the carrier phase observables enables the relative positioning to achieve centimeter level accuracy,however,the quaternion elements derived from the GPS interferometer are inherently noisy.This is due to the fact that the baseline vectors estimated by the least-squares method are based on the raw double-differenced measurements.Construction of the transformation matrix is accessible according to the estimate of baseline vectors and thereafter the computed quaternion elements can be derived.Using the Euler angle method,the process becomes meaningless when the angles are at 90where the singularity problem occurs.A good alternative is the quaternion approach,which possesses advantages over the equivalent Euler angle based transformation since they apply to all attitudes.Simulation results on the attitude estimation performance based on the proposed method will be presented and compared to the conventional method.The results presented in this paper elucidate the superiority of proposed algorithm.

Complementary Kalman Filter as a Baseline Vector Estimator for GPS-Based Attitude Determination

The Global Positioning System(GPS)offers the interferometer for attitude determination by processing the carrier phase observables.By using carrier phase observables,the relative positioning is obtained in centimeter level.GPS interferometry has been firstly used in precise static relative positioning,and thereafter in kinematic positioning.The carrier phase differential GPS based on interferometer principles can solve for the antenna baseline vector,defined as the vector between the antenna designated master and one of the slave antennas,connected to a rigid body.Determining the unknown baseline vectors between the antennas sits at the heart of GPS-based attitude determination.The conventional solution of the baseline vectors based on least-squares approach is inherently noisy,which results in the noisy attitude solutions.In this article,the complementary Kalman filter(CKF)is employed for solving the baseline vector in the attitude determination mechanism to improve the performance,where the receiver-satellite double differenced observable was utilized as the measurement.By using the carrier phase observables,the relative positioning is obtained in centimeter level.Employing the CKF provides several advantages,such as accuracy improvement,reliability enhancement,and real-time assurance.Simulation results based on the conventional method where the least-squares approach is involved,and the proposed method where the CKF is involved are compared and discussed.

Design on a Multi-Sensor Integrated Attitude Determination System for Small UAVs

This paper discusses the design and implementation of a low cost multi-sensor integrated attitude determination system for small unmanned aerial vehicles( UAVs),which uses strapdown inertial navigation system( SINS) based on micro electromechanical system( MEMS) inertial sensors,commercial GPS receiver,and 3-axis magnetometer.MEMS-SINS initial attitude determination cannot be well performed for the reason that the MEMS inertial sensors biases are time-varying and poor repeatability,therefore in this paper the magnetometer and inclinometer are used to assist the MEMS-SINS initial attitude determination and MEMS inertial sensors field calibration.Furthermore,the attitude determination algorithms are presented to estimate the full attitude during GPS signal outage and non-accelerating situation.Additionally,the attitude information estimation results are compared with the reference of the non-magnetic marble platform and 3-axis turntable.Then the attitude estimation precision satisfies the requirement of attitude measurement for small UAVs during GPS signal outage and availability.Finally,the small UAV autonomous flight test results show that the low cost and real-time attitude determination system can yield continuous,reliable and effective attitude information for small UAVs.

Estimator-Based GPS Attitude and Angular Velocity Determination

In this paper,the estimator-based Global Positioning System(GPS)attitude and angular velocity determination is presented.Outputs of the attitude estimator include the attitude angles and attitude rates or body angular velocities,depending on the design of estimator.Traditionally as a position,velocity and time sensor,the GPS also offers a free attitude-determination interferometer.GPS research and applications to the field of attitude determination using carrier phase or Doppler measurement has been extensively conducted.The rawattitude solution using the interferometry technique based on the least-squares approach is inherently noisy.The estimator such as the Kalman filter(KF)or extended Kalman filter(EKF)can be incorporated into the GPS interferometer,potentially providing several advantages,such as accuracy improvement,reliability enhancement,and real-time characteristics.Three estimator-based approaches are investigated for performance comparison,including(1)KF with measurement involving attitude angles only;(2)EKF with measurements based on attitude angles only;(3)EKF with measurements involving both attitude angles and body angular rates.The assistance from body mounted gyroscopes,if available,can be utilized as the measurements for further performance improvement,especially useful for the case of signal-challenged environment,such as the GPS outages.Modeling of the dynamic process involving the body angular rates and derivation of the related algorithm will be presented.Simulation results for various estimator-based approaches are conducted;performance comparison is presented for the case of GPS outages.

ATTITUDE RATE ESTIMATION BY GPS DOPPLER SIGNAL PROCESSING

A method is presented for near-Earth spacecraft or aviation vehicle's attitude rate estimation 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 relatively simple, the cost and weight, as well as power consumption, are very low.

低成本惯性多冗余导航控制一体机设计

为了智能体的精确定位和定姿,实现其稳定运动控制,设计了一种低成本多惯性冗余导航控制一体机,给出了设计方法。稳压电路的开关电源MP2482DN和线性电源JW29300U-3.3V为一体机提供稳定5 V和3.3 V的较大功率电源;控制器STM32H7的SPI采用星形拓扑总线与3片六轴惯性芯片BMI088通信,2路TTL串口与差分卫星定位板双向通信,实现智能体定位和定姿;控制器STM32F4的CAN总线接口与智能体底盘双向通信,实现其运动控制,1路TTL串口实现与控制器STM32H7的双向通信;两控制器的网络接口与上位机组成无线局域网,实现数据交换和状态监控。整个系统具有功耗低、体积小、成本低、接口丰富的特点。

复杂环境下GPS+BDS-3 PPP/INS紧组合算法性能分析

针对城市复杂环境下精密单点定位(PPP)连续高精度定位受限的问题,本文基于北斗三号全球卫星导航系统(BDS-3)与全球定位系统(GPS)双系统,利用PPP与惯性导航系统(INS)紧组合算法来改善城市复杂环境下定位性能。通过构建GPS+BDS-3双系统PPP/INS紧组合滤波模型,分别对GPS PPP、GPS+BDS-3 PPP、GPS PPP/INS紧组合、GPS+BDS-3PPP/INS紧组合4种方案在城区开阔、复杂环境下的定位、测速、定姿性能进行了分析和评估。实验结果表明,开阔环境下PPP/INS紧组合相比PPP定位精度略有提升;而在复杂环境下PPP/INS紧组合可显著解决PPP定位结果连续性和有效性较差的问题;引入BDS-3后,PPP/INS紧组合导航性能进一步提升,GPS+BDS-3 PPP/INS紧组合相比GPS PPP/INS紧组合,在东、北、天方向上,开阔环境下定位精度分别提升18.5%、32.7%、43.2%,复杂环境下定位精度分别提升35.9%、49.1%、56.5%。

基于多传感器融合的工作面设备定位定姿技术研究

随着科技的发展与进步,煤矿智能化已经成为目前矿业生产中的重点研究方向。但是在薄煤层工作面中由于顶板条件的复杂性以及作业环境的多变性,导致目前的井下自动化控制技术中存在液压支架自动跟机不能完美适应井下顶底板环境且采煤机难以精准定位的问题。以薄煤层工作面自动化控制系统为基础,结合图像识别以及多传感器融合的方法研究采煤机的定位技术,并对液压支架定姿的关键技术进行了分析,期望提高薄煤层自动化系统在煤矿井下的适应性,减少工作面的操作人员,提高煤矿生产的效率。

Hybrid analytical resolution approach based on ambiguity function for attitude determination

When satellite navigation receivers are equipped with multiple antennas, they can deliver attitude information. In previous researches, carrier phase differencing measurement equations were built in the earth-centered, earth-fixed (ECEF) co- ordinate, and attitude angles could be obtained through the rotation matrix between the body frame (BF) and the local level frame (LLF). Different from the conventional methods, a hybrid algorithm is presented to resolve attitude parameters utilizing the single differencing (SD) carrier phase equations established in LLF. Assuming that the cycle integer ambiguity is known, the measure- ment equations have attitude analytical resolutions by using simultaneous single difference equations for two in-view satellites. In addition, the algorithm is capable of reducing the search integer space into countable 2D discrete points and the ambiguity function method (AFM) resolves the ambiguity function within the analytical solutions space. In the case of frequency division multiple access (FDMA) for the Russian Global Orbiting Navigation Satellite System (GLONASS), a receiver clock bias estimation is employed to evaluate its carrier phase. An evaluating variable and a weighted factor are introduced to assess the integer ambiguity initialization. By static and dynamic ground experiments, the results show that the proposed approach is effective, with enough accuracy and low computation. It can satisfy attitude determination in cases of GPS alone and combined with GLONASS.

Data-driven real-time prediction for attitude and position of super-large diameter shield using a hybrid deep learning approach

The presented research introduces a novel hybrid deep learning approach for the dynamic prediction of the attitude and position of super-large diameter shields-a critical consideration for construction safety and tunnel lining quality.This study proposes a hybrid deep learning approach for predicting dynamic attitude and position prediction of super-large diameter shield.The approach consists of principal component analysis(PCA)and temporal convolutional network(TCN).The former is used for employing feature level fusion based on features of the shield data to reduce uncertainty,improve accuracy and the data effect,and 9 sets of required principal component characteristic data are obtained.The latter is adopted to process sequence data in predicting the dynamic attitude and position for the advantages and potential of convolution network.The approach’s effectiveness is exemplified using data from a tunnel construction project in China.The obtained results show remarkable accuracy in predicting the global attitude and position,with an average error ratio of less than 2 mm on four shield outputs in 97.30%of cases.Moreover,the approach displays strong performance in accurately predicting sudden fluctuations in shield attitude and position,with an average prediction accuracy of 89.68%.The proposed hybrid model demonstrates superiority over TCN,long short-term memory(LSTM),and recurrent neural network(RNN)in multiple indexes.Shapley additive exPlanations(SHAP)analysis is also performed to investigate the significance of different data features in the prediction process.This study provides a real-time warning for the shield driver to adjust the attitude and position of super-large diameter shields.

基于三维激光扫描仪的无序工件精准定位

为了获取生产线上无序且被遮挡的工件的准确位姿,为后续机械臂对工件特定部位的抓取提供支持,本文使用高精度三维激光扫描仪扫描生产线上无序摆放的工件,然后对原始点云先后采用Voxel-Grid降采样、平面分割和DBSCAN聚类,分割出单个工件点云,再用K-4PCS粗配准和kd-tree加速的GICP精配准方法,将工件实际点云与标准的点云模板(由工件的机械设计图转化而来)进行配准,最终得到了两者之间精确的位姿变换矩阵,进而获得工件摆放的准确位姿。为了验证论文提出方法的有效性,对生产线上3组形状不同工件的摆放位姿进行了测试。结果表明,该方法对于不同形状的工件摆放位姿都有很好的求解精度(误差≤3 mm)。

单目视觉空间移动靶位姿测量方法研究

为向室内定位技术定位精度及抗干扰能力提供高精度数据对比标准,提出单目视觉空间移动靶位姿测量方法。结合机器视觉投影矩阵求解与摄影测量后方交会技术,实现任意靶位姿下的相机外参数求解。首先,通过世界坐标系下地面控制点坐标及其像面坐标,计算真实相机站位;随后,根据靶点初始世界坐标及其实时像面坐标,求解虚拟相机站位;最后,根据虚拟及真实相机站位外参数,将靶点初始世界坐标变换至靶点实时世界坐标。实验结果表明,在10 m×4.5 m×3.8 m测量空间中,靶位移距离测量误差X方向均方根误差(RMSE)为0.3583 mm,Y方向RMSE为0.3509 mm,Z方向RMSE为1.4752 mm。靶姿态角φ测量RMSE为0.0940°,ω测量RMSE为0.0893°,κ测量RMSE为0.0254°。满足大范围移动载体的高精度实时定位定姿需求。

带约束条件的自适应滤波及其在GPS定位中的应用

推导了约束状态下的卡尔曼滤波递推方程 ,采用不消去状态参数的方法 ,在卡尔曼滤波的数学模型中增加约束状态方程推导出约束状态下的卡尔曼滤波递推方程。表明采用带约束条件的滤波递推过程与一般卡尔曼滤波递推方程相似 ,只要对预报值及其协方差增加一项约束条件改正项即可 ,因此 ,在滤波计算上不需要做大的修改。还讨论了带约束条件的卡尔曼滤波的自适应算法 ,说明一般自适应滤波算法同样适用于带约束条件的滤波 ,因此在应用上非常便利。利用一组GPS动态定位数据中的伪距观测值进行计算分析 ,并以距离作为一个约束条件 ,结果显示约束条件对滤波结果的改善程度与约束条件和动态系统本身有关。对于一般卡尔曼滤波中因模型确定误差和动态目标突然加速而导致的滤波发散现象 ,如果增加约束条件的约束力较小时 ,同样会出现滤波结果偏离 ,因此 ,带约束条件的滤波同样需要考虑滤波的自适应性。

长壁综采工作面采煤机定位定姿技术研究

分析了现有的采煤机支架传感定位技术、轨道里程计定位技术、自主定位技术的研究现状及其存在的问题;提出了以采区绝对坐标为参考坐标,采煤机在开采煤层内绝对定位的研究内容;探讨了采煤机定位技术在长壁综采工作面自动化中的作用。

UWB/INS紧组合的室内定位定姿方法

针对室内环境下UWB定位精度受NLOS误差影响明显,且不能提供载体姿态信息的问题,提出UWB/INS紧组合的室内定位定姿方法:利用经过标准时间偏差改正后的RTT测距信息与INS推算的距离信息之差作为量测信息,按设定的阈值剔除NLOS误差,通过扩展卡尔曼滤波进行室内定位定姿。实验结果表明,该方法能有效抑制NLOS误差的影响,较好提升在NLOS环境下的定位定姿精度,适用于高精度的室内移动测量。

基于解析法的全球定位系统姿态测量技术

提出了一种新的实时全球定位系统(GPS)姿态测量初始化方法,将超越方程的求解与模糊度函数法相结合,有效地提高了初始化计算速度.讨论了模糊度函数法,从几何角度描述了观测方程,给出了二元非线性观测方程组的解,并对实测数据进行了处理.结果表明,该方法与一般的方法相比,初始化的计算更有效,更经济.

非合作航天器对接环识别算法研究

针对非合作航天器的对接环识别问题,研究基于单目视觉和激光测距仪的识别算法。首先给出一种简单的非合作航天器相对姿态单目视觉确定算法,得到通用的坐标转换矩阵表示的相对姿态,并由激光测距仪的信息得到相对位置。然后采用最小二乘法,得到对接环外端框所成图像的椭圆参数。根据相对位姿和椭圆参数,提出对接环识别算法。仿真结果表明,提出的识别算法能够准确地确定对接环外端框的相关尺寸。

基于样条模型的高精度星间相对定位与定姿

针对分布式小卫星编队的星间相对定位与定姿的高精度要求,提出了基于样条模型的星间相对定位与定姿的新方法。新方法将一段连续时间内的卫星状态参数用样条参数模型表示,将直接估计状态参数转化为样条参数,减少了待估参数的个数,实现了多时刻状态联解,提高了姿态参数对距离变化的敏感性,结构更加稳定。仿真结果表明,相对定位精度由5mm提高到2mm,相对定姿精度由0.0004弧度提高到0.00003弧度,并解决了估计不稳定现象。

基于三目视觉测量的航天器交会对接相对位姿确定算法

针对航天器交会对接过程中位姿参数的测量问题,提出了三目视觉的测量方法。本文阐述了三目视觉的测量原理,建立了数学模型,分析了测量系统的误差。仿真结果表明该方法有效。与双目视觉相比,它能降低图像匹配误差的影响,提高特征点的定位精度,增加测量系统的可靠性,因此能够满足航天器位姿参数的测量要求,对航天器在轨实时应用具有重要参考价值。