Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory
Autor(a) principal: | |
---|---|
Data de Publicação: | 2016 |
Outros Autores: | , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Latin American journal of solids and structures (Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1679-78252016000200296 |
Resumo: | Abstract This paper is devoted to the vibration of rotating flexible spacecraft. The maneuver of the spacecraft is modeled by a constant torque input acting on the hub. For the first time in this paper the equations of motion of flexible spacecraft are derived based on higher order sandwich panel theory (HSAPT). Hamilton's principle is used for driving the governing partial differential equations of motion. The generalized differential quadrature method (GDQ) is utilized to solve the partial differential equations of motion. The effect of different parameters on vibration of rotating flexible spacecraft appendage is investigated. It is also investigated the effect of these parameters on natural frequencies. The result of HSAPT and Euler Bernoulli theory is compared with each other. To show the accuracy the natural frequencies of recent paper are compared with the literature. |
id |
ABCM-1_78d5960dc99f01b109f9a2c023f5c372 |
---|---|
oai_identifier_str |
oai:scielo:S1679-78252016000200296 |
network_acronym_str |
ABCM-1 |
network_name_str |
Latin American journal of solids and structures (Online) |
repository_id_str |
|
spelling |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel TheoryFlexible SpacecraftConstant torqueHamilton's principleGDQHSAPTAbstract This paper is devoted to the vibration of rotating flexible spacecraft. The maneuver of the spacecraft is modeled by a constant torque input acting on the hub. For the first time in this paper the equations of motion of flexible spacecraft are derived based on higher order sandwich panel theory (HSAPT). Hamilton's principle is used for driving the governing partial differential equations of motion. The generalized differential quadrature method (GDQ) is utilized to solve the partial differential equations of motion. The effect of different parameters on vibration of rotating flexible spacecraft appendage is investigated. It is also investigated the effect of these parameters on natural frequencies. The result of HSAPT and Euler Bernoulli theory is compared with each other. To show the accuracy the natural frequencies of recent paper are compared with the literature.Associação Brasileira de Ciências Mecânicas2016-02-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S1679-78252016000200296Latin American Journal of Solids and Structures v.13 n.2 2016reponame:Latin American journal of solids and structures (Online)instname:Associação Brasileira de Engenharia e Ciências Mecânicas (ABCM)instacron:ABCM10.1590/1679-78252326info:eu-repo/semantics/openAccessAzimi,MiladShahravi,MortezaJoubaneh,Eshagh Farzaneheng2016-09-06T00:00:00Zoai:scielo:S1679-78252016000200296Revistahttp://www.scielo.br/scielo.php?script=sci_serial&pid=1679-7825&lng=pt&nrm=isohttps://old.scielo.br/oai/scielo-oai.phpabcm@abcm.org.br||maralves@usp.br1679-78251679-7817opendoar:2016-09-06T00:00Latin American journal of solids and structures (Online) - Associação Brasileira de Engenharia e Ciências Mecânicas (ABCM)false |
dc.title.none.fl_str_mv |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
title |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
spellingShingle |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory Azimi,Milad Flexible Spacecraft Constant torque Hamilton's principle GDQ HSAPT |
title_short |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
title_full |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
title_fullStr |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
title_full_unstemmed |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
title_sort |
Dynamic Analysis of Maneuvering Flexible Spacecraft Appendage Using Higher Order Sandwich Panel Theory |
author |
Azimi,Milad |
author_facet |
Azimi,Milad Shahravi,Morteza Joubaneh,Eshagh Farzaneh |
author_role |
author |
author2 |
Shahravi,Morteza Joubaneh,Eshagh Farzaneh |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Azimi,Milad Shahravi,Morteza Joubaneh,Eshagh Farzaneh |
dc.subject.por.fl_str_mv |
Flexible Spacecraft Constant torque Hamilton's principle GDQ HSAPT |
topic |
Flexible Spacecraft Constant torque Hamilton's principle GDQ HSAPT |
description |
Abstract This paper is devoted to the vibration of rotating flexible spacecraft. The maneuver of the spacecraft is modeled by a constant torque input acting on the hub. For the first time in this paper the equations of motion of flexible spacecraft are derived based on higher order sandwich panel theory (HSAPT). Hamilton's principle is used for driving the governing partial differential equations of motion. The generalized differential quadrature method (GDQ) is utilized to solve the partial differential equations of motion. The effect of different parameters on vibration of rotating flexible spacecraft appendage is investigated. It is also investigated the effect of these parameters on natural frequencies. The result of HSAPT and Euler Bernoulli theory is compared with each other. To show the accuracy the natural frequencies of recent paper are compared with the literature. |
publishDate |
2016 |
dc.date.none.fl_str_mv |
2016-02-01 |
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=S1679-78252016000200296 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1679-78252016000200296 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.1590/1679-78252326 |
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 |
Associação Brasileira de Ciências Mecânicas |
publisher.none.fl_str_mv |
Associação Brasileira de Ciências Mecânicas |
dc.source.none.fl_str_mv |
Latin American Journal of Solids and Structures v.13 n.2 2016 reponame:Latin American journal of solids and structures (Online) instname:Associação Brasileira de Engenharia e Ciências Mecânicas (ABCM) instacron:ABCM |
instname_str |
Associação Brasileira de Engenharia e Ciências Mecânicas (ABCM) |
instacron_str |
ABCM |
institution |
ABCM |
reponame_str |
Latin American journal of solids and structures (Online) |
collection |
Latin American journal of solids and structures (Online) |
repository.name.fl_str_mv |
Latin American journal of solids and structures (Online) - Associação Brasileira de Engenharia e Ciências Mecânicas (ABCM) |
repository.mail.fl_str_mv |
abcm@abcm.org.br||maralves@usp.br |
_version_ |
1754302888378630144 |