Study of a nozzle vector control for a low cost mini-launcher
This study is addressed to the control system of a mini-launcher. A reaction control based on purge pressure from a solid propellant engine of a main stage, or using cold gas from a storage tank will be the control method. Pulse modulator system will be the actuation method studied, and simulations...
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| Tipo de recurso: | tesis de maestría |
| Fecha de publicación: | 2011 |
| País: | España |
| Institución: | Universitat Politècnica de Catalunya (UPC) |
| Repositorio: | UPCommons. Portal del coneixement obert de la UPC |
| Idioma: | inglés |
| OAI Identifier: | oai:upcommons.upc.edu:2099.1/12521 |
| Acceso en línea: | https://hdl.handle.net/2099.1/12521 |
| Access Level: | acceso abierto |
| Palabra clave: | Microspacecraft Artificial satellites Nozzle Vector Control Low cost mini-launcher Solid propellant Coets (Aeronàutica) Satèl·lits artificials Àrees temàtiques de la UPC::Aeronàutica i espai::Aeronaus::Coets Àrees temàtiques de la UPC::Enginyeria de la telecomunicació::Radiocomunicació i exploració electromagnètica::Satèl·lits i ràdioenllaços |
| Sumario: | This study is addressed to the control system of a mini-launcher. A reaction control based on purge pressure from a solid propellant engine of a main stage, or using cold gas from a storage tank will be the control method. Pulse modulator system will be the actuation method studied, and simulations about its suitability will be done with Simulink. In this thesis, we try to check if this method is able to be implemented in a low cost way the Wiki-Launcher, a mini-launcher less than 100 kg. At the time we try to check if the control allowed by the reaction control can manage all the phases of the flight. Both possible control configurations are going to be analyzed. |
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