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Robust relative navigation for spacecraft rendezvous using differential drag

机译：使用差示拖动的航天器对宇宙飞船的强大的相对导航

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摘要

This work is concerned with the development of relative navigation filters processing relative position measurements of two satellites that perform rendezvous via differential drag only along low Earth orbits. The filters are developed in the Leader Hill frame with an emphasis on differential drag uncertainty modeling. Embedding the atmosphere density daily high variability in a bitopic uncertainty yields a novel robust H-infinity, filter of the six relative motion states. For comparison two Kalman filters matched to other atmosphere density models are developed. Furthermore the navigation are embedded in a realistic guidance navigation and attitude control and determination architecture (GNC/ADC) for nanosatellites. The proposed test case features two nanosatellites at 300 km altitude switching from positive to negative differential drag modes via 3D rigid body rotation. The 3D attitude control system involves three reactions wheels and three magnetorquers. The satellites inertial attitudes are estimated using three rate gyroscopes and coarse vector measurements. The proposed GNC/ADC scheme is tested in a high fidelity simulation environment. With 1 m relative position measurement accuracy and 10 degrees attitude pointing accuracy the steady-state along track navigation errors are 4 m, 7 m, and 8 m (RMS) for the H-infinity filter and the Kalman filters, respectively. The H-infinity filter also shows quicker convergence and lesser sensitivity to the atmosphere density high variability. The two satellites succeed in closing an initial along track separation distance from 7500 m down to 250 m within 10 orbits, while the final radial deviation is about 10 m.
机译：这项工作涉及相对导航滤波器的开发处理的两个卫星的相对位置测量，其通过沿低地球轨道仅通过差分拖动来执行Rendezvous。滤波器是在领导者山框架中开发的，重点是差分阻力不确定性建模。在比特缺陷不确定性中嵌入大气密度的日常变异性产生了一种新颖的鲁棒H-Infinity，六个相对运动状态的过滤器。为了比较，开发了与其他气氛密度模型相匹配的两个卡尔曼滤波器。此外，导航嵌入纳米替肽的现实引导导航和姿态控制和确定架构（GNC / ADC）中。所提出的测试用例具有两个纳米卫星，在300公里的高度从正到负差分拖动模式通过3D刚体旋转切换。 3D姿态控制系统涉及三个反应车轮和三个磁力。使用三个速率陀螺仪和粗载量测量估计卫星惯性态度。在高保真仿真环境中测试了所提出的GNC / ADC方案。具有1米的相对位置测量精度和10度姿态指向精度，沿着轨道导航误差的稳态分别为H-Infinity过滤器和卡尔曼滤波器的4米，7米和8米（RMS）。 H-Infinity过滤器还显示出更快的收敛性和对大气密度高变异性的敏感性。两颗卫星成功地沿着轨道分离距离在10个轨道内的7500米下降到250米，而最终的径向偏差约为10米。

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  • 来源
    《Acta astronautica》 |2019年第5期|32-43|共12页
  • 作者

    Chocron S.; Choukroun D.;

  • 作者单位

    Ben Gurion Univ Negev Fac Engn Sci Dept Mech Engn Pearlstone Ctr Aeronaut Engn Studies IL-84105 Beer Sheva Israel|Fac Engn Sci Dept Mech Engn Beer Sheva Israel;

    Ben Gurion Univ Negev Fac Engn Sci Dept Mech Engn Pearlstone Ctr Aeronaut Engn Studies IL-84105 Beer Sheva Israel|Fac Engn Sci Dept Mech Engn Beer Sheva Israel;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Robust relative navigation; Spacecraft rendezvous; Differential drag;

    机译：强大的相对导航;航天器会合;差分阻力;

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