Relative Navigation Between Two Spacecraft Using X-ray Pulsars
Relative Navigation Between Two Spacecraft Using X-ray Pulsars
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DOI：
10.1109/tcst.2010.2068049
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发表时间：
2011-09
影响因子：
4.8
通讯作者：
A. A. Emadzadeh-A.;J. Speyer
中科院分区：
文献类型：
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作者：
A. A. Emadzadeh-A.;J. Speyer
本文建议利用x射线脉冲星进行深空航天器间的相对导航。提出了描述x射线脉冲星信号的数学模型。建立了脉冲时延估计问题，给出了估计脉冲时延的cram<s:1> r- rao下界。介绍了两种不同的脉冲时延估计器，并研究了它们的渐近性能。研究了每个时延估计器的数值复杂度，以及绝对速度误差对其性能的影响。利用脉冲星测量数据，提出了一种航天器间相对导航的递归算法。航天器加速度数据由惯性测量单元（imu）提供。利用脉冲延迟估计作为测量，基于航天器和IMU动力学模型，采用卡尔曼滤波获得三维相对位置和速度。此外，还可以估计加速度计的相对偏差以及时钟之间的时间差。通过数值仿真验证了所提出的导航算法。
This paper suggests utilizing X-ray pulsars for relative navigation between two spacecraft in deep space. Mathematical models describing X-ray pulsar signals are presented. The pulse delay estimation problem is formulated, and the Cramér-Rao lower bound (CRLB) for estimation of the pulse delay is given. Two different pulse delay estimators are introduced, and their asymptotic performance is studied. Numerical complexity of each delay estimator, and the effect of absolute velocity errors on its performance is investigated. Using the pulsar measurements, a recursive algorithm is proposed for relative navigation between two spacecraft. The spacecraft acceleration data are provided by the inertial measurement units (IMUs). The pulse delay estimates are used as measurements, and based on models of the spacecraft and IMU dynamics, a Kalman filter is employed to obtain the 3-D relative position and velocity. Furthermore, it is shown that the relative accelerometer biases as well as the differential time between clocks can be estimated. Numerical simulations are also performed to assess the proposed navigation algorithm.