Change search
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Design, Analysis and Fabrication of a Rocket Simulator Prototype For Thrust Vectoring Stabilization
2015 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

University of Würzburg, Informatics VIII aims in developing a rocket simulator test bed in aspect of implementing a control algorithm for thrust vectoring concept. This thesis explains the idea of developing a miniaturized rocket model which is equipped with an actuating nozzle. The main content discussed in this project involves in designing a rocket prototype for thrust vectoring mechanisms where the control algorithm about to be developed can be implemented and tested for. From the various thrust vectoring mechanisms available, selection of mechanically actuated system is finalized because of its benefits in use. Here mechanical actuation is done with the help of servo supported by a bearing.The next phase is about describing the type of nozzle suitable for the work and proceeding with determination of the required parameters for the selected nozzle. By reviewing the available literature background, Bell shaped Convergent-Divergent nozzle is considered to be relevant and reasonably preferred for the thrust vectoring mechanism. Theoretical calculations were made for the specific criterion in respect with all technical details necessary for designing the nozzle. CAD model of the nozzle is then finalized and designed in Catia V5 R18 CAD software.Analyzing and visualizing the fluid flow parameters of the nozzle is done with the help of Ansys 14.5 software. Here the compressed air is used as the fluid flow medium. Analysis is made to find the pressure, density variation along the axis of the nozzle. The obtained analytical results are then validated with the theoretically calculated results. Once verification is done the components are given for manufacturing.Designed thrust vectoring setup should weigh very less for it to be lifted by the force produced by the nozzle. So the components are manufactured in a light weight material called PVC. The manufactured components are then assembled and tested in the laboratory.

Place, publisher, year, edition, pages
2015. , 64 p.
Keyword [en]
Technology, Thrust vectoring, rocket simulator, nozzle
Keyword [sv]
Teknik
Identifiers
URN: urn:nbn:se:ltu:diva-58620Local ID: f33407ae-047d-436c-a3b4-caf39444afe9OAI: oai:DiVA.org:ltu-58620DiVA: diva2:1032008
External cooperation
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Supervisors
Examiners
Note
Validerat; 20150928 (global_studentproject_submitter)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

Open Access in DiVA

fulltext(3375 kB)253 downloads
File information
File name FULLTEXT02.pdfFile size 3375 kBChecksum SHA-512
52e9d5c798d8e74351fc0119bfd3854a319b693499f58896fb302422642dfcc287cf1de54d8707c7b803ea59e83107fe6e574abd8b95c2d26d5a9813ddcccf0b
Type fulltextMimetype application/pdf

Search outside of DiVA

GoogleGoogle Scholar
Total: 253 downloads
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

urn-nbn

Altmetric score

urn-nbn
Total: 128 hits
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf