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| 02023nam 2200301za 4500 |
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| 001 | 9.856207 |
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| 003 | CaOODSP |
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| 005 | 20240221113057 |
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| 007 | cr ||||||||||| |
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| 008 | 180507s2017 quc |o f|0| 0 eng d |
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| 040 | |aCaOODSP|beng |
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| 043 | |an-cn--- |
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| 086 | 1 |aD68-10/110-2017E-PDF |
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| 245 | 00|aObservability of satellite launcher navigation with INS, GPS, attitude sensors and reference trajectory |h[electronic resource] / |cYanick Beaudoin ... [et al.] |
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| 260 | |a[Valcartier, QC] : |bDefence Research and Development Canada, |c2017. |
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| 300 | |a[16] p. |
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| 490 | 1 |aExternal literature (P) ; |vDRDC-RDDC-2017-P110 |
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| 500 | |aCover title. |
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| 500 | |a"Can unclassified." |
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| 500 | |a"November 2017." |
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| 504 | |aIncludes bibliographic references. |
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| 520 | 3 |a"The navigation system of a satellite launcher is of paramount importance. In order to correct the trajectory of the launcher, the position, velocity and attitude must be known with the best possible precision. In this paper, the observability of four navigation solutions is investigated. The first one is the INS/GPS couple. Then, attitude reference sensors, such as magnetometers, are added to the INS/GPS solution. The authors have already demonstrated that the reference trajectory could be used to improve the navigation performance. This approach is added to the two previously mentioned navigation systems. For each navigation solution, the observability is analyzed with different sensor error models. First, sensor biases are neglected. Then, sensor biases are modelled as random walks and as first order Markov processes"--Abstract. |
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| 692 | 07|2gccst|aSatellites |
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| 692 | 07|2gccst|aNavigation systems |
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| 700 | 1 |aBeaudoin, Yanick, |d1974- |
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| 710 | 1 |aDefence R&D Canada. |bValcartier Research Centre. |
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| 830 | #0|aExternal literature (P) (Defence R&D Canada)|vDRDC-RDDC-2017-P110|w(CaOODSP)9.854437 |
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| 856 | 40|qPDF|s465 KB|uhttps://publications.gc.ca/collections/collection_2018/rddc-drdc/D69-53-2017-eng.pdf |
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