Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile
Autor(a) principal: | |
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Data de Publicação: | 2019 |
Outros Autores: | , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Journal of Aerospace Technology and Management (Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100306 |
Resumo: | ABSTRACT Based on adaptive sliding mode-control and back-stepping design method, an integrated guidance and control method with less calculation is proposed, which is designed for air-to-ground missile during the terminal course in three-dimensional space. The model of the control system with nonlinear and coupling is simplified, then the integrated guidance and control model in pitch and yaw channel is established. The coupling terms and modeling error between channels is considered as unknown bounded disturbance. An extended state observer is developed to estimate and compensate the unknown disturbance. In the design process, the block dynamic surface method is adopted, and the first order low pass filter is introduced to avoid the problem of differential explosion present in the traditional back-stepping design method during the process of differentiating virtual control variable. The Lyapunov stability theory is used to prove the stability of the system. Finally, in the case of nominal and positive and negative perturbations of model parameters, the simulation experiments are carried outto verify the effectiveness of the proposed IGC algorithm. |
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Journal of Aerospace Technology and Management (Online) |
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Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground MissileIntegrated guidance and controlAdaptive back-stepping sliding modeDynamic surfaceAir-to-ground missileExtended state observerABSTRACT Based on adaptive sliding mode-control and back-stepping design method, an integrated guidance and control method with less calculation is proposed, which is designed for air-to-ground missile during the terminal course in three-dimensional space. The model of the control system with nonlinear and coupling is simplified, then the integrated guidance and control model in pitch and yaw channel is established. The coupling terms and modeling error between channels is considered as unknown bounded disturbance. An extended state observer is developed to estimate and compensate the unknown disturbance. In the design process, the block dynamic surface method is adopted, and the first order low pass filter is introduced to avoid the problem of differential explosion present in the traditional back-stepping design method during the process of differentiating virtual control variable. The Lyapunov stability theory is used to prove the stability of the system. Finally, in the case of nominal and positive and negative perturbations of model parameters, the simulation experiments are carried outto verify the effectiveness of the proposed IGC algorithm.Departamento de Ciência e Tecnologia Aeroespacial2019-01-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100306Journal of Aerospace Technology and Management v.11 2019reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v11.982info:eu-repo/semantics/openAccessWang,ZhikaiMa,JianweiFu,Jiangtaoeng2019-01-11T00:00:00Zoai:scielo:S2175-91462019000100306Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2019-01-11T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
title |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
spellingShingle |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile Wang,Zhikai Integrated guidance and control Adaptive back-stepping sliding mode Dynamic surface Air-to-ground missile Extended state observer |
title_short |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
title_full |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
title_fullStr |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
title_full_unstemmed |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
title_sort |
Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile |
author |
Wang,Zhikai |
author_facet |
Wang,Zhikai Ma,Jianwei Fu,Jiangtao |
author_role |
author |
author2 |
Ma,Jianwei Fu,Jiangtao |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Wang,Zhikai Ma,Jianwei Fu,Jiangtao |
dc.subject.por.fl_str_mv |
Integrated guidance and control Adaptive back-stepping sliding mode Dynamic surface Air-to-ground missile Extended state observer |
topic |
Integrated guidance and control Adaptive back-stepping sliding mode Dynamic surface Air-to-ground missile Extended state observer |
description |
ABSTRACT Based on adaptive sliding mode-control and back-stepping design method, an integrated guidance and control method with less calculation is proposed, which is designed for air-to-ground missile during the terminal course in three-dimensional space. The model of the control system with nonlinear and coupling is simplified, then the integrated guidance and control model in pitch and yaw channel is established. The coupling terms and modeling error between channels is considered as unknown bounded disturbance. An extended state observer is developed to estimate and compensate the unknown disturbance. In the design process, the block dynamic surface method is adopted, and the first order low pass filter is introduced to avoid the problem of differential explosion present in the traditional back-stepping design method during the process of differentiating virtual control variable. The Lyapunov stability theory is used to prove the stability of the system. Finally, in the case of nominal and positive and negative perturbations of model parameters, the simulation experiments are carried outto verify the effectiveness of the proposed IGC algorithm. |
publishDate |
2019 |
dc.date.none.fl_str_mv |
2019-01-01 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100306 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100306 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v11.982 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
text/html |
dc.publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
dc.source.none.fl_str_mv |
Journal of Aerospace Technology and Management v.11 2019 reponame:Journal of Aerospace Technology and Management (Online) instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA) instacron:DCTA |
instname_str |
Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
instacron_str |
DCTA |
institution |
DCTA |
reponame_str |
Journal of Aerospace Technology and Management (Online) |
collection |
Journal of Aerospace Technology and Management (Online) |
repository.name.fl_str_mv |
Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
repository.mail.fl_str_mv |
||secretary@jatm.com.br |
_version_ |
1754732532014776320 |