| 1. Identity statement | |
| Reference Type | Book Section |
| Site | marte3.sid.inpe.br |
| Holder Code | isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S |
| Identifier | 6qtX3pFwXQZ3r59YCT/GUKzo |
| Repository | sid.inpe.br/iris@1905/2005/07.29.22.33.01 (restricted access) |
| Last Update | 2015:11.18.11.47.46 (UTC) marciana |
| Metadata Repository | sid.inpe.br/iris@1905/2005/07.29.22.33.08 |
| Metadata Last Update | 2021:02.11.18.09.43 (UTC) administrator |
| Secondary Key | INPE-8044-PRE/3860 |
| Label | 8990 |
| Citation Key | FelipePrad:2000:OpMaTh |
| Title | Optimal maneuvers in three-dimensional swing by trajectories  |
| Format | ISBN:85-901487-1-8 |
| Year | 2000 |
| Secondary Date | 20010416 |
| Access Date | 2024, May 05 |
| Secondary Type | PRE LN |
| Number of Files | 1 |
| Size | 367 KiB |
| 2. Context | |
| Author | 1 Felipe, Gislaine de 2 Prado, Antonio Fernando Bertachini de Almeida |
| Group | 1 DMC-INPE-MCT-BR |
| Editor | Prado, Antonio Fernando Bertachini de Almeida. |
| Book Title | Colóquio Brasileiro de Dinâmica Orbital, 9 Advances in Space Dynamics |
| Pages | 84-98 |
| Series Title | Advances in Space Dynamics |
| History (UTC) | 2014-09-29 15:08:58 :: administrator -> marciana :: 2000 2015-11-18 11:47:46 :: marciana -> administrator :: 2000 2021-02-11 18:09:43 :: administrator -> :: 2000 |
| 3. Content and structure | |
| Is the master or a copy? | is the master |
| Content Stage | completed |
| Transferable | 1 |
| Content Type | External Contribution |
| Keywords | ENGENHARIA E TECNOLOGIA ESPACIAL astrodinâmica trajetorias espaciais mecanica celeste manobras de orbitas astrodynamics spacecraft trajectories celestial mechanics orbital maneuvers |
| Abstract | The swing-by maneuver uses a close approach with a celestial body to modify the velocity, energy and angular momentum of a spacecraft. The literature has several papers studying this problem, usually using a patched-conic approximation. In the present paper the swing-by maneuvers are studied and classified under the model given by the three-dimensional restricted three-body problem. To show the results, the orbits of the spacecraft are classified in four groups: elliptic direct, elliptic retrograde, hyperbolic direct and hyperbolic retrograde. Then, the modification in the orbit of the spacecraft due to the close approach is shown in plots that specify from which group of orbits the spacecraft is coming and to which group it is going. The results generated here are used to solve optimal problems, such as finding trajectories that satisfy some given constraints (such as achieving an escape or a capture) with some parameters being extremized (position, velocity, etc ...). Three optimal problems are solved in this paper to show this application. |
| Area | ETES |
| Arrangement | urlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Optimal maneuvers in... |
| doc Directory Content | access |
| source Directory Content | there are no files |
| agreement Directory Content | there are no files |
| 4. Conditions of access and use | |
| Target File | 2000_felipe3.pdf |
| User Group | administrator |
| Visibility | shown |
| Read Permission | deny from all and allow from 150.163 |
| Update Permission | not transferred |
| 5. Allied materials | |
| Next Higher Units | 8JMKD3MGPCW/446AF4B |
| Host Collection | sid.inpe.br/banon/2001/04.03.15.36 |
| 6. Notes | |
| Empty Fields | affiliation archivingpolicy archivist callnumber city copyholder copyright creatorhistory descriptionlevel dissemination doi e-mailaddress edition electronicmailaddress isbn issn language lineage mark mirrorrepository nextedition notes numberofvolumes orcid parameterlist parentrepositories previousedition previouslowerunit progress project publisher readergroup resumeid rightsholder schedulinginformation secondarymark serieseditor session shorttitle sponsor subject tertiarymark tertiarytype translator url versiontype volume |