| 1. Identity statement | |
| Reference Type | Book Section |
| Site | marte3.sid.inpe.br |
| Holder Code | isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S |
| Identifier | 6qtX3pFwXQZ3r59YCT/H3JMK |
| Repository | sid.inpe.br/iris@1905/2005/08.04.02.01 (restricted access) |
| Last Update | 2019:01.16.16.13.09 (UTC) simone |
| Metadata Repository | sid.inpe.br/iris@1905/2005/08.04.02.01.24 |
| Metadata Last Update | 2021:02.11.18.10.08 (UTC) administrator |
| Secondary Key | INPE-9533-PRE/5186 |
| Label | 10461 |
| Citation Key | CorreaPradStuc:2002:ImTrHa |
| Title | Impulsive transfers from halo orbits in the Earth-Moon system  |
| Format | ISBN 85-17-00006-4 |
| Year | 2002 |
| Secondary Date | 20021213 |
| Access Date | 2024, May 08 |
| Secondary Type | PRE LN |
| Number of Files | 1 |
| Size | 5728 KiB |
| 2. Context | |
| Author | 1 Correa, Annelise Aiex 2 Prado, Antonio Fernando Bertachini de Almeida 3 Stuchi, Teresinha de Jesus |
| Group | 1 DMC-INPE-MCT-BR |
| Editor | Winter, Othon Cabo Prado, Antonio Fernando Bertachini de Almeida |
| Book Title | Coloquio Brasileiro de Dinâmica Orbital, 10 Advances in space dynamics 3: applications in astronautics |
| Publisher | INPE |
| City | São José dos Campos |
| Pages | 298-316 |
| Series Title | Advances in space dynamics 3: applications in astronautics |
| History (UTC) | 2008-06-09 21:40:56 :: administrator -> jefferson :: 2012-08-02 17:55:04 :: jefferson -> administrator :: 2019-01-16 16:12:47 :: administrator -> simone :: 2002 2019-01-16 16:13:10 :: simone -> administrator :: 2002 2021-02-11 18:10:08 :: administrator -> :: 2002 |
| 3. Content and structure | |
| Is the master or a copy? | is the master |
| Content Stage | completed |
| Transferable | 1 |
| Keywords | ENGENHARIA E TECNOLOGIA ESPACIAL three-body problem Halo orbits Earth and the Moon Lambert Method hahmann maneuver fuel consumption |
| Abstract | The motivation of this work is the periodic solutions in the restricted three-body problem, in particular, the tridimensional periodic orbits around de collinear equilibrium points known as Halo orbits. The system studied here is formed by the Earth and the Moon, which are assumed to move in circular orbits around their center of mass, and the third body, with negligible mass which, moves under their gravitational field. In this context are also interested in finding optimal transfer orbits to put a space vehicle in one of the Halo orbits around the interior point L1. Firstly, we have applied Lambert's method for orbits transfer, in the context of the restricted three-body problem. Secondly, we analyzed the natural instability of the Halo orbits as a way of getting more economical tranfer orbits than de Lambert's method provides. Finally, we compare the total fuel consumption of these methods and discuss the advantages and limitations of each method. |
| Area | ETES |
| Arrangement | urlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Impulsive transfers from... |
| 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 | INPE-9533.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 contenttype 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 readergroup resumeid rightsholder schedulinginformation secondarymark serieseditor session shorttitle sponsor subject tertiarymark tertiarytype translator url versiontype volume |