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首页> 外文会议>Proceedings of the 54th annual meeting : Taking navigation to new heights >A Batch Filter for Baseline Estimation Using On-Orbit GPS and Gyro Data
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A Batch Filter for Baseline Estimation Using On-Orbit GPS and Gyro Data

机译：使用在轨GPS和陀螺仪数据进行基线估计的批处理过滤器

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The GPS Attitude and Navigation Experiment (GANE) flown on STS-77 simulated the environment of the GPS antenna array and inertial instrument suite planned for the International Space Station (ISS). This paper describes a methodology for batch estimation of initial attitude and GPS baselines intended for use with the ISS and presents results for the GANE. The results are compared to reference data from ground tests and on-orbit from the Orbiter high-accuracy inertial navigation system (HAINS).rnInitial attitude errors for the GPS/IRU solution as compared to the Orbiter reference are within 0.14 deg for one data set, and 1.5 deg for a second data set, with the largest errors occurring in the pitch axis. Baseline vector estimates differ from pre-flight values by as much as 5 cm, with the magnitudes of the baseline vectors differing by as much as 6 mm. However, the baseline vector estimates agree with the Orbiter-derived reference to within 4 mm; with the maximum difference in magnitudes being less than 1 mm. Linernbias estimates differ from pre-flight values by as much as 0.05 cycles for one data set, and 0.03 cy for another data set. For both data sets, the difference is less than 0.006 cycles when compared to the line biases derived from the Orbiter reference data.rnThe results illustrate the importance of baseline calibration on-orbit due to changes in the antennas and baselines between ground and flight operations. Furthermore, consistency between the operational IRU and the reference Orbiter INS provides confidence in the accuracy of the batch estimation procedure and results.
机译：在STS-77上进行的GPS姿态和导航实验（GANE）模拟了计划用于国际空间站（ISS）的GPS天线阵列和惯性仪器套件的环境。本文介绍了一种用于与ISS配合使用的初始姿态和GPS基线的批估计方法，并介绍了GANE的结果。将结果与地面测试的参考数据以及Orbiter高精度惯性导航系统（HAINS）的在轨数据进行比较。rn对于一个数据集，与Orbiter参考相比，GPS / IRU解决方案的初始姿态误差在0.14度以内对于第二个数据集为1.5度，最大误差发生在俯仰轴上。基线矢量估计值与飞行前值相差最多5厘米，基线矢量的大小相差最多6毫米。但是，基线矢量估计值与Orbiter得出的参考值一致，在4 mm以内。最大幅度差小于1毫米。对于一个数据集，Linernbias估计值与飞行前值相差多达0.05个周期，而对于另一个数据集，其偏差为0.03 cy。对于这两个数据集，与从轨道飞行器参考数据得出的线路偏置相比，差异小于0.006个周期。结果表明，由于地面和飞行操作之间的天线和基线发生变化，基线校准在轨的重要性。此外，操作性IRU和参考Orbiter INS之间的一致性为批量估算程序和结果的准确性提供了信心。

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