Aircraft navigation based on differentiation-integration observer
In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Wang, Xinhua [verfasserIn] |
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| Format: |
Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2015 |
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| Schlagwörter: |
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| Übergeordnetes Werk: |
Enthalten in: Aerospace science and technology - Paris : Elsevier, 1997, (2015) |
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| Übergeordnetes Werk: |
year:2015 |
| Links: |
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| DOI / URN: |
10.1016/j.ast.2017.05.007 |
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| Katalog-ID: |
OLC1998421686 |
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| 520 | |a In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. | ||
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10.1016/j.ast.2017.05.007 doi PQ20171125 (DE-627)OLC1998421686 (DE-599)GBVOLC1998421686 (PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720 (KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio DE-627 ger DE-627 rakwb eng 620 DNB Wang, Xinhua verfasserin aut Aircraft navigation based on differentiation-integration observer 2015 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. Computer Science Systems and Control Cai, Lilong oth Enthalten in Aerospace science and technology Paris : Elsevier, 1997 (2015) (DE-627)226623149 (DE-600)1378482-1 (DE-576)058656634 1270-9638 nnns year:2015 http://dx.doi.org/10.1016/j.ast.2017.05.007 Volltext http://arxiv.org/abs/1506.02762 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-FRK SSG-OLC-AST SSG-OLC-ROK SSG-OPC-AST GBV_ILN_70 AR 2015 |
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10.1016/j.ast.2017.05.007 doi PQ20171125 (DE-627)OLC1998421686 (DE-599)GBVOLC1998421686 (PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720 (KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio DE-627 ger DE-627 rakwb eng 620 DNB Wang, Xinhua verfasserin aut Aircraft navigation based on differentiation-integration observer 2015 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. Computer Science Systems and Control Cai, Lilong oth Enthalten in Aerospace science and technology Paris : Elsevier, 1997 (2015) (DE-627)226623149 (DE-600)1378482-1 (DE-576)058656634 1270-9638 nnns year:2015 http://dx.doi.org/10.1016/j.ast.2017.05.007 Volltext http://arxiv.org/abs/1506.02762 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-FRK SSG-OLC-AST SSG-OLC-ROK SSG-OPC-AST GBV_ILN_70 AR 2015 |
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10.1016/j.ast.2017.05.007 doi PQ20171125 (DE-627)OLC1998421686 (DE-599)GBVOLC1998421686 (PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720 (KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio DE-627 ger DE-627 rakwb eng 620 DNB Wang, Xinhua verfasserin aut Aircraft navigation based on differentiation-integration observer 2015 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. Computer Science Systems and Control Cai, Lilong oth Enthalten in Aerospace science and technology Paris : Elsevier, 1997 (2015) (DE-627)226623149 (DE-600)1378482-1 (DE-576)058656634 1270-9638 nnns year:2015 http://dx.doi.org/10.1016/j.ast.2017.05.007 Volltext http://arxiv.org/abs/1506.02762 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-FRK SSG-OLC-AST SSG-OLC-ROK SSG-OPC-AST GBV_ILN_70 AR 2015 |
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10.1016/j.ast.2017.05.007 doi PQ20171125 (DE-627)OLC1998421686 (DE-599)GBVOLC1998421686 (PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720 (KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio DE-627 ger DE-627 rakwb eng 620 DNB Wang, Xinhua verfasserin aut Aircraft navigation based on differentiation-integration observer 2015 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. Computer Science Systems and Control Cai, Lilong oth Enthalten in Aerospace science and technology Paris : Elsevier, 1997 (2015) (DE-627)226623149 (DE-600)1378482-1 (DE-576)058656634 1270-9638 nnns year:2015 http://dx.doi.org/10.1016/j.ast.2017.05.007 Volltext http://arxiv.org/abs/1506.02762 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-FRK SSG-OLC-AST SSG-OLC-ROK SSG-OPC-AST GBV_ILN_70 AR 2015 |
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10.1016/j.ast.2017.05.007 doi PQ20171125 (DE-627)OLC1998421686 (DE-599)GBVOLC1998421686 (PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720 (KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio DE-627 ger DE-627 rakwb eng 620 DNB Wang, Xinhua verfasserin aut Aircraft navigation based on differentiation-integration observer 2015 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. Computer Science Systems and Control Cai, Lilong oth Enthalten in Aerospace science and technology Paris : Elsevier, 1997 (2015) (DE-627)226623149 (DE-600)1378482-1 (DE-576)058656634 1270-9638 nnns year:2015 http://dx.doi.org/10.1016/j.ast.2017.05.007 Volltext http://arxiv.org/abs/1506.02762 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-FRK SSG-OLC-AST SSG-OLC-ROK SSG-OPC-AST GBV_ILN_70 AR 2015 |
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In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. |
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In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. |
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In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory. |
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<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a2200265 4500</leader><controlfield tag="001">OLC1998421686</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230715082025.0</controlfield><controlfield tag="007">tu</controlfield><controlfield tag="008">171125s2015 xx ||||| 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1016/j.ast.2017.05.007</subfield><subfield code="2">doi</subfield></datafield><datafield tag="028" ind1="5" ind2="2"><subfield code="a">PQ20171125</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)OLC1998421686</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-599)GBVOLC1998421686</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(PRQ)a741-cb26e4f011b059ea5315ff0393ea1b0d6b608d645ad1e1536742b4eab08f7c720</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(KEY)0324851820150000000000000000aircraftnavigationbasedondifferentiationintegratio</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">620</subfield><subfield code="q">DNB</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Wang, Xinhua</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Aircraft navigation based on differentiation-integration observer</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2015</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">ohne Hilfsmittel zu benutzen</subfield><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Band</subfield><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">In this paper, a generalized differentiation-integration observer is presented based on sensors selection. The proposed differentiation-integration observer can estimate the multiple integrals and high-order derivatives of a signal, synchronously. The parameters selection rules are presented for the differentiation-integration observer. The theoretical results are confirmed by the frequency-domain analysis. The effectiveness of the proposed observer are verified through the numerical simulations on a quadrotor aircraft: i) through the differentiation-integration observer, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity; ii) a control law is designed based on the observers to drive the aircraft to track a reference trajectory.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Computer Science</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Systems and Control</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Cai, Lilong</subfield><subfield code="4">oth</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Aerospace science and technology</subfield><subfield code="d">Paris : Elsevier, 1997</subfield><subfield code="g">(2015)</subfield><subfield code="w">(DE-627)226623149</subfield><subfield code="w">(DE-600)1378482-1</subfield><subfield code="w">(DE-576)058656634</subfield><subfield code="x">1270-9638</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">year:2015</subfield></datafield><datafield tag="856" ind1="4" ind2="1"><subfield code="u">http://dx.doi.org/10.1016/j.ast.2017.05.007</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="856" ind1="4" ind2="2"><subfield code="u">http://arxiv.org/abs/1506.02762</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_OLC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-TEC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-FRK</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-AST</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-ROK</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OPC-AST</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_70</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="j">2015</subfield></datafield></record></collection>
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7.397358 |