| 1. Identity statement | ||||
| Reference Type | Journal Article | |||
| Site | mtc-m21c.sid.inpe.br | |||
| Holder Code | isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S | |||
| Identifier | 8JMKD3MGP3W34R/44DNE2B | |||
| Repository | sid.inpe.br/mtc-m21c/2021/03.29.12.51 | |||
| Metadata Repository | sid.inpe.br/mtc-m21c/2021/03.29.12.51.15 | |||
| Metadata Last Update | 2021:04.07.20.59.51 (UTC) administrator | |||
| DOI | 10.18180/tecciencia.2020.29.1 | |||
| Citation Key | OspinaContrerasRold:2020:CoDeTh | |||
| Title | Conceptual design of a three-stage rocket to transport a load of 200kg to a loworbit  | |||
| Year | 2020 | |||
| Access Date | 2024, May 03 | |||
| Type of Work | journal article | |||
| 2. Context | ||||
| Author | 1 Ospina Contreras, Daimer 2 Roldan Torres, Luis Carlos | |||
| Group | 1 COCRE-COCRE-INPE-MCTIC-GOV-BR | |||
| Affiliation | 1 Instituto Nacional de Pesquisas Espaciais (INPE) 2 Universidad San Buenaventura | |||
| Author e-Mail Address | 1 ingdaimerospina@hotmail.com 2 luis.roldant@outlook.com | |||
| Journal | Tecciencia | |||
| Volume | 15 | |||
| Number | 29 | |||
| Pages | 1-8 | |||
| History (UTC) | 2021-03-29 12:52:38 :: simone -> administrator :: 2020 2021-04-07 20:59:51 :: administrator -> simone :: 2020 | |||
| 3. Content and structure | ||||
| Is the master or a copy? | is the master | |||
| Content Stage | completed | |||
| Transferable | 1 | |||
| Content Type | External Contribution | |||
| Version Type | publisher | |||
| Keywords | Rocket rocket engine low earth orbit propellant | |||
| Abstract | This article presents the conceptual design of a three-stage rocket to carry 200 kg payload to low Earth orbits (by the acronym LEO). From a case study of the flight path of a three-stage rocket with solid propellants, proceed to select the propellant mixture that meets the design requirements and path raised flight, taking into account that it can produce nationwide. The propellant thermochemical behavior is obtained with CPROPEP software. Knowing the values of pressure, temperature and specific heat ratio in the combustion chamber proceeds to design rocket engines to ensure total velocity change in the system equivalent to those obtained in the analysis of the flight path. With the design of the propulsion duct materials that withstand the thermal loads and pressure, to give way to structural design giving an approximation of carrier rocket are chosen. | |||
| Area | ETES | |||
| Arrangement | Conceptual design of... | |||
| doc Directory Content | there are no files | |||
| source Directory Content | there are no files | |||
| agreement Directory Content |
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| 4. Conditions of access and use | ||||
| Language | en | |||
| User Group | simone | |||
| Reader Group | administrator simone | |||
| Visibility | shown | |||
| Read Permission | deny from all and allow from 150.163 | |||
| Update Permission | not transferred | |||
| 5. Allied materials | ||||
| Mirror Repository | urlib.net/www/2017/11.22.19.04.03 | |||
| Next Higher Units | 8JMKD3MGPCW/3EUJHT5 | |||
| Host Collection | urlib.net/www/2017/11.22.19.04 | |||
| 6. Notes | ||||
| Empty Fields | alternatejournal archivingpolicy archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination e-mailaddress format isbn issn label lineage mark month nextedition notes numberoffiles orcid parameterlist parentrepositories previousedition previouslowerunit progress project resumeid rightsholder schedulinginformation secondarydate secondarykey secondarymark secondarytype session shorttitle size sponsor subject targetfile tertiarymark tertiarytype url | |||
| 7. Description control | ||||
| e-Mail (login) | simone | |||
| update | ||||