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SCIENTIA SINICA Physica, Mechanica & Astronomica, Volume 49, Issue 8: 084510(2019) https://doi.org/10.1360/SSPMA-2019-0103

Autonomous celestial navigation method of asteroid probe based on angle measurement and velocity measurement

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  • ReceivedApr 4, 2019
  • AcceptedMay 10, 2019
  • PublishedJun 17, 2019
PACS numbers

Abstract

Autonomous navigation is one of the key technologies to ensure the successful implementation of deep space exploration mission. Aiming at the requirement of celestial autonomous navigation ability of asteroid probe in practical engineering tasks, the integrated autonomous navigation method combined celestial spectral velocity measurement with celestial image angle measurement is proposed to realize continuous autonomous, real-time and high-precision navigation of asteroid probe. Considering the limitation of traditional radio navigation on the ground and the high requirement for autonomous survivability of asteroid probe, the task of asteroid explorer has an urgent need for real-time and autonomous navigation ability. The current autonomous navigation method mainly extracts the angle measurement information of the probe relative to the target celestial planet from the optical image information of the target celestial planet, and then calculates and determines the navigation state of the probe. However the accuracy of velocity estimation by this navigation method is limited, which still cannot fully meet the current demand of asteroid probe. In view of the shortcomings of the main existing autonomous navigation methods, this paper proposes a direct velocity measurement method based on astronomical spectrum, and combines it with the astronomical angle navigation method to form the integrated autonomous navigation method. Based on the integrated autonomous navigation method, the navigation system model and filtering algorithm are derived, and the observability and navigation accuracy performance of the integrated navigation system are analyzed. Taking the Ceres exploration mission as an engineering background, the simulation results show that the stellar velocity information measured by astronomical spectroscopy can greatly improve the integrated navigation performance. And the accuracy of position and velocity estimation results of the probe can restrain the influence of errors more effectively and enhance the reliability of navigation system. Compared with the traditional terrestrial radio navigation or angle measurement navigation methods, the integrated navigation results have higher accuracy and better real-time performance, which can provide accurate navigation information for asteroid probe orbit modification. The integrated navigation method derived in this paper is effective, reliable and easy to implement. It provides a reference for the implementation of the asteroid exploration project and the subsequent major deep space missions in China.


Funded by

科工局十三五民用航天预研(D030102)

上海市科委科研计划(18DZ2272300)


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  • Figure 1

    (Color online) Principle of angle measurement navigation.

  • Figure 2

    (Color online) Measuring relative velocity of apparent motion by Doppler principle.

  • Figure 3

    (Color online) Principle of velocity measurement navigation.

  • Figure 4

    (Color online) Navigation results of radio navigation method.

  • Figure 5

    (Color online) Navigation results of angle navigation method. (a) Position estimation; (b) velocity estimation.

  • Figure 6

    (Color online) Navigation results of integrated navigation method. (a) Position estimation; (b) velocity estimation.

  • Table 1   Observability analysis of different navigation methods

    导航系统

    量测方案

    可观测阶数

    可观测度

    测角导航

    太阳、小行星视线矢量

    2

    8.97×10−11

    测角测速

    组合导航

    太阳、小行星视线矢量

    太阳、恒星视向速度

    1

    8.24×10−10

  • Table 2   Parameters of asteroid probe

    参数名称

    参数值

    基本参数

    探测器质量2000 kg, 有效光压面积10 m2

    电推进参数

    推力大小2000 mN, 方向为背向太阳; 推力大小误差3 mN, 方向误差0.01°

    探测器初始状态

    位置r=[−232397675 234438176 29399149] km, 偏差为Δr=[1000 1000 1000] km;

    速度v=[−15.97 −13.05 0.99] km/s, 误差为Δv=[100 100 100] m/s

    小行星初始状态

    位置r=[−245859494 222859970 30210427] km

    速度v=[−15.27 −13.81 0.91] km/s

  • Table 3   Parameters of navigation method

    参数名称

    参数值

    UKF算法参数

    P=diag([106, 106, 106, 102, 102, 102]), Q=1×1020I6×6, R=0.235×1010I6×6.

    α=1, β=0, κ=3

    系统量测误差

    测角量测精度2 arcsec, 测速量测精度1 m/s

    仿真参数设置

    起始时刻2028-01-23 00:07:27.589 UTCG; 结束时刻2028-02-02 00:07:27.589 UTCG;

    仿真步长600 S

  • Table 4   Comparison of navigation accuracy of different navigation methods

    导航方法

    位置精度(3σ, km)

    速度精度(3σ, m/s)

    地面无线电导航

    278.03

    5.14

    测角导航

    254.82

    4.32

    测角测速组合导航

    114.54

    1.31

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