Relative navigation algorithm research of chaser spacecraft

Hong Deng; Weichao Zhong; Zhaowei Sun; Shunan Wu

doi:10.1109/AERO.2011.5747614

Relative navigation algorithm research of chaser spacecraft

Hong Deng^*
, Weichao Zhong
, Zhaowei Sun
, Shunan Wu

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

1 Scopus citations

Abstract

In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H_∞ filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H_∞ filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.

Original language	English
Title of host publication	2011 Aerospace Conference, AERO 2011
DOIs	https://doi.org/10.1109/AERO.2011.5747614
State	Published - 2011
Event	2011 IEEE Aerospace Conference, AERO 2011 - Big Sky, MT, United States Duration: 5 Mar 2011 → 12 Mar 2011

Publication series

Name	IEEE Aerospace Conference Proceedings
ISSN (Print)	1095-323X

Conference

Conference	2011 IEEE Aerospace Conference, AERO 2011
Country/Territory	United States
City	Big Sky, MT
Period	5/03/11 → 12/03/11

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10.1109/AERO.2011.5747614

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@inproceedings{21387e125b8a44f5862d5042f907d8b4,

title = "Relative navigation algorithm research of chaser spacecraft",

abstract = "In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H∞ filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H∞ filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.",

author = "Hong Deng and Weichao Zhong and Zhaowei Sun and Shunan Wu",

year = "2011",

doi = "10.1109/AERO.2011.5747614",

language = "英语",

isbn = "9781424473502",

series = "IEEE Aerospace Conference Proceedings",

booktitle = "2011 Aerospace Conference, AERO 2011",

note = "2011 IEEE Aerospace Conference, AERO 2011 ; Conference date: 05-03-2011 Through 12-03-2011",

}

TY - GEN

T1 - Relative navigation algorithm research of chaser spacecraft

AU - Deng, Hong

AU - Zhong, Weichao

AU - Sun, Zhaowei

AU - Wu, Shunan

PY - 2011

Y1 - 2011

N2 - In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H∞ filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H∞ filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.

AB - In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H∞ filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H∞ filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.

UR - https://www.scopus.com/pages/publications/79955770025

U2 - 10.1109/AERO.2011.5747614

DO - 10.1109/AERO.2011.5747614

M3 - 会议稿件

AN - SCOPUS:79955770025

SN - 9781424473502

T3 - IEEE Aerospace Conference Proceedings

BT - 2011 Aerospace Conference, AERO 2011

T2 - 2011 IEEE Aerospace Conference, AERO 2011

Y2 - 5 March 2011 through 12 March 2011

ER -

Relative navigation algorithm research of chaser spacecraft

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