Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method
A finite time attitude controller is designed for a flexible spacecraft based on a novel output redefinition method, in this paper. To make the flexible appendages vibration suppression effective, the appendage tip-point is selected as the output. First, a novel output redefinition method is propose...
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| Veröffentlicht in: | Chinese journal of aeronautics 2023-11, Vol.36 (11), p.373-385 |
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| container_title | Chinese journal of aeronautics |
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| creator | ESMAEILZADEH, Seyed Majid ZEYGHAMI, Mohammad Sadegh |
| description | A finite time attitude controller is designed for a flexible spacecraft based on a novel output redefinition method, in this paper. To make the flexible appendages vibration suppression effective, the appendage tip-point is selected as the output. First, a novel output redefinition method is proposed to overcome the non-minimum phase property of the dynamic model. The proposed method not only makes the system model minimum phase but also improves the attitude control system performance. Consequently, the precise attitude pointing and stabilization are achieved. Then, a nonlinear finite time H∞ controller is designed based on the backstepping approach. For the situation where the modal variables measurements are not available, a modal observer is also designed. The simulation results show the effectiveness of the proposed method in the presence of the model uncertainties and environmental disturbances. |
| doi_str_mv | 10.1016/j.cja.2023.08.001 |
| format | Article |
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To make the flexible appendages vibration suppression effective, the appendage tip-point is selected as the output. First, a novel output redefinition method is proposed to overcome the non-minimum phase property of the dynamic model. The proposed method not only makes the system model minimum phase but also improves the attitude control system performance. Consequently, the precise attitude pointing and stabilization are achieved. Then, a nonlinear finite time H∞ controller is designed based on the backstepping approach. For the situation where the modal variables measurements are not available, a modal observer is also designed. 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The simulation results show the effectiveness of the proposed method in the presence of the model uncertainties and environmental disturbances.</description><subject>Attitude control</subject><subject>Backstepping</subject><subject>Finite time</subject><subject>Flexible spacecraft</subject><subject>H∞ control</subject><subject>Output redefinition</subject><subject>Robust</subject><issn>1000-9361</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2023</creationdate><recordtype>article</recordtype><recordid>eNp9kLtOAzEQRV2ARAh8AJ07qizj9T5FhSJeUgQN1JbXHhMvGzvyekP4exxCTTXF3HNHcwi5YpAxYNVNn6leZjnkPIMmA2AnZMYAYNHyip2R83HsAXhbM5gR--LdYB3KQI11NiKNdoNUxmjjpJEq72LwA_WGmgH3thuQjlupUAVpIu3kiJp6RyV1focpN8XtFGlAjb99Nu02GNdeX5BTI4cRL__mnLw_3L8tnxar18fn5d1qoXhexAXL605Xpuk45G0JHWtK1hpuykqbqgZWsAqVltzootYFyLIxDRhjCik1bxH4nFwfe7-kM9J9iN5PwaWLYv257wQevDAGeZGS7JhUwY9jQCO2wW5k-BYMxMGk6EUyKQ6EgEYkk4m5PTKYXthZDGJUFp1CbQOqKLS3_9A_qXJ_WA</recordid><startdate>20231101</startdate><enddate>20231101</enddate><creator>ESMAEILZADEH, Seyed Majid</creator><creator>ZEYGHAMI, Mohammad Sadegh</creator><general>Elsevier Ltd</general><general>Department of Electrical Engineering,Iran University of Science and Technology,Narmak,Tehran 16846-13114,Iran</general><scope>6I.</scope><scope>AAFTH</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>2B.</scope><scope>4A8</scope><scope>92I</scope><scope>93N</scope><scope>PSX</scope><scope>TCJ</scope></search><sort><creationdate>20231101</creationdate><title>Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method</title><author>ESMAEILZADEH, Seyed Majid ; ZEYGHAMI, Mohammad Sadegh</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c324t-127bd6f8b302950b18519f3f56df6701416ecda3fd47d40a58f80fff4aad39e03</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2023</creationdate><topic>Attitude control</topic><topic>Backstepping</topic><topic>Finite time</topic><topic>Flexible spacecraft</topic><topic>H∞ control</topic><topic>Output redefinition</topic><topic>Robust</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>ESMAEILZADEH, Seyed Majid</creatorcontrib><creatorcontrib>ZEYGHAMI, Mohammad Sadegh</creatorcontrib><collection>ScienceDirect Open Access Titles</collection><collection>Elsevier:ScienceDirect:Open Access</collection><collection>CrossRef</collection><collection>Wanfang Data Journals - Hong Kong</collection><collection>WANFANG Data Centre</collection><collection>Wanfang Data Journals</collection><collection>万方数据期刊 - 香港版</collection><collection>China Online Journals (COJ)</collection><collection>China Online Journals (COJ)</collection><jtitle>Chinese journal of aeronautics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>ESMAEILZADEH, Seyed Majid</au><au>ZEYGHAMI, Mohammad Sadegh</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method</atitle><jtitle>Chinese journal of aeronautics</jtitle><date>2023-11-01</date><risdate>2023</risdate><volume>36</volume><issue>11</issue><spage>373</spage><epage>385</epage><pages>373-385</pages><issn>1000-9361</issn><abstract>A finite time attitude controller is designed for a flexible spacecraft based on a novel output redefinition method, in this paper. To make the flexible appendages vibration suppression effective, the appendage tip-point is selected as the output. First, a novel output redefinition method is proposed to overcome the non-minimum phase property of the dynamic model. The proposed method not only makes the system model minimum phase but also improves the attitude control system performance. Consequently, the precise attitude pointing and stabilization are achieved. Then, a nonlinear finite time H∞ controller is designed based on the backstepping approach. For the situation where the modal variables measurements are not available, a modal observer is also designed. The simulation results show the effectiveness of the proposed method in the presence of the model uncertainties and environmental disturbances.</abstract><pub>Elsevier Ltd</pub><doi>10.1016/j.cja.2023.08.001</doi><tpages>13</tpages><oa>free_for_read</oa></addata></record> |
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| identifier | ISSN: 1000-9361 |
| ispartof | Chinese journal of aeronautics, 2023-11, Vol.36 (11), p.373-385 |
| issn | 1000-9361 |
| language | eng |
| recordid | cdi_wanfang_journals_hkxb_e202311024 |
| source | Elsevier ScienceDirect Journals; Elektronische Zeitschriftenbibliothek - Frei zugängliche E-Journals |
| subjects | Attitude control Backstepping Finite time Flexible spacecraft H∞ control Output redefinition Robust |
| title | Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method |
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