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Development of a reaction control system software
2002 (English)Independent thesis Advanced level (professional degree), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The purpose of this thesis work was to develop a steady state generic propulsion system model and to make a literature study on verification processes of a spacecraft propulsion system. The model is developed in Matlab 6.1 and its purpose is to predict the subsystem performance. To make the model easy to use, a graphical user interface is implemented using GUIDE (Graphical User Development Environment). The model comprises of several modules describing the propulsion system. These modules are: nozzle, combustion chamber, pressure drop, regulated and blow down module. Each module consists of a mathematical model that calculates certain performance parameters, such as specific impulse and combustion flame temperature. The model developed is a part of the verification process, which consists of verification analysis and verification tests. Verification analysis uses software models to predict the system performance, such as the model developed in this thesis. The results were successful. A generic model was made within the time demarcation of 20 weeks. The model was verified using a sophisticated program, such as the Gordon McBride code, to compare with. The flame temperature was verified and the resulting accuracy ended at 95.4%, which is good enough for a generic model.

Place, publisher, year, edition, pages
Keyword [en]
Technology, space, propulsion, RCS, verification, modelling
Keyword [sv]
URN: urn:nbn:se:ltu:diva-50415ISRN: LTU-EX--02/369--SELocal ID: 7aedfc68-436a-4e03-bddd-d7af9a9fa7ccOAI: diva2:1023774
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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