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自动化与信息科学期刊

每年出版 12 

ISSN 打印: 1064-2315

ISSN 在线: 2163-9337

SJR: 0.173 SNIP: 0.588 CiteScore™:: 2

Indexed in

Satellite Correction Equations for a Strapdown Inertial System

卷 29, 册 1, 1997, pp. 91-99
DOI: 10.1615/JAutomatInfScien.v29.i1.110
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摘要

Equations for satellite correction of an aircraft strapdown inertial navigation system are given. Structure of equations that is suitable for estimating the error vector using a triangular Kalman filter (square-root filter) is specified. The possibility of providing the observability and obtaining estimation of the basic elements of the vector of state under the conditions of a horizontal linear flight is considered.

对本文的引用
  1. Miniature Inertial Measurement Unit, in Space Microsystems and Micro/nano Satellites, 2018. Crossref

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