Triple difference-based spacecraft GPS/INS attitude determination

Xiaokui Yue; Jianping Yuan

Triple difference-based spacecraft GPS/INS attitude determination

Xiaokui Yue, Jianping Yuan

航天学院

Northwestern Polytechnical University Xian

科研成果: 期刊稿件 › 文章 › 同行评审

1 引用（Scopus）

摘要

Based on the triple difference carrier phase observables, a GPS/INS integration algorithm for attitude determination is studied. The proposed integration system also contains a cycle slip detection algorithm, in which inertial information is utilized to detect cycle slip. Some computer simulations are performed to verify the proposed integration system. The results show that accurate and reliable navigation solution can be gained.

源语言	英语
页（从-至）	1-5+10
期刊	Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology
卷	26
期	4
出版状态	已出版 - 8月 2006

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引用此

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title = "Triple difference-based spacecraft GPS/INS attitude determination",

abstract = "Based on the triple difference carrier phase observables, a GPS/INS integration algorithm for attitude determination is studied. The proposed integration system also contains a cycle slip detection algorithm, in which inertial information is utilized to detect cycle slip. Some computer simulations are performed to verify the proposed integration system. The results show that accurate and reliable navigation solution can be gained.",

keywords = "Carrier phase, Combinatorial algorithm, Global positioning system, Inertial measurement, Simulation, Spacecraft",

author = "Xiaokui Yue and Jianping Yuan",

year = "2006",

month = aug,

language = "英语",

volume = "26",

pages = "1--5+10",

journal = "Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology",

issn = "1000-758X",

publisher = "Chinese Academy of Space Technology",

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TY - JOUR

T1 - Triple difference-based spacecraft GPS/INS attitude determination

AU - Yue, Xiaokui

AU - Yuan, Jianping

PY - 2006/8

Y1 - 2006/8

N2 - Based on the triple difference carrier phase observables, a GPS/INS integration algorithm for attitude determination is studied. The proposed integration system also contains a cycle slip detection algorithm, in which inertial information is utilized to detect cycle slip. Some computer simulations are performed to verify the proposed integration system. The results show that accurate and reliable navigation solution can be gained.

AB - Based on the triple difference carrier phase observables, a GPS/INS integration algorithm for attitude determination is studied. The proposed integration system also contains a cycle slip detection algorithm, in which inertial information is utilized to detect cycle slip. Some computer simulations are performed to verify the proposed integration system. The results show that accurate and reliable navigation solution can be gained.

KW - Carrier phase

KW - Combinatorial algorithm

KW - Global positioning system

KW - Inertial measurement

KW - Simulation

KW - Spacecraft

UR - http://www.scopus.com/inward/record.url?scp=33750323526&partnerID=8YFLogxK

M3 - 文章

AN - SCOPUS:33750323526

SN - 1000-758X

VL - 26

SP - 1-5+10

JO - Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology

JF - Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology

IS - 4

ER -

Triple difference-based spacecraft GPS/INS attitude determination

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