Multidisciplinary design optimization for aerodynamic and propulsion components of rockets
Rockets are vehicles that people have worked hard on and made great progress in return throughout history. Over the years rockets have continued to evolve and have been clas- sified in different categories. Multistage rockets represent one of these categories. The purpose of multistage rockets is to...
| Autor: | |
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| Tipo de recurso: | tesis de maestría |
| Fecha de publicación: | 2022 |
| 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:2117/371114 |
| Acceso en línea: | https://hdl.handle.net/2117/371114 |
| Access Level: | acceso abierto |
| Palabra clave: | Rockets (Aeronautics)--Research Rocket optimization Trajectory optimization Maximize payload ratio Rockets (Aeronautics) Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió |
| Sumario: | Rockets are vehicles that people have worked hard on and made great progress in return throughout history. Over the years rockets have continued to evolve and have been clas- sified in different categories. Multistage rockets represent one of these categories. The purpose of multistage rockets is to place the fuel at different stages and to ensure that each stage operates within specified time intervals. The research in the present work is focused on serial multistage rockets. Thus a single stage, after completing a stage task, i.e. after consuming its fuel, becomes disconnected and leaves the whole structure and reduces the amount of total load. In other words, it makes the rocket lighter. Right after the previous stage has left, the next stage is ignited and so starts its duty and continues to carry the rocket to higher altitude by burning its fuel. In particular, present research is car- ried out on rockets consisting of 2 and 3 stages. During the studies, the most attention was paid to the aerodynamic forces and moments, because they have a serious effect on the stability of the rocket. The stability of the rocket is as important as rocket design. For this purpose, an attempt was made to balance the center of gravity and the center of pressure by calculating. Likewise, aerodynamic forces and moments affect the speed and position of the rocket. The main center of the study was 6 DOF blocks in Simulink. To meet the objectives, the Earth-centered Earth fixed coordinate system was also used. In this way, all values could be obtained in a loop. Different coordinate systems were the most useful approach for observing and evaluating outputs. The model, which was created with the contribution of all these, was run by designing 2 and 3 stages. All together 4 main points were investigated. First aim was to investigate the minimum fuel to reach the constant altitude with the constant payload in both designs. Secondly, the minimum and maximum fuel quantities found in the first step were considered constant, and the maximum payload amount that could be increased to a certain height was investigated. Third, the known min- imum and maximum fuel amounts and which payload can be safely lifted to what height were examined. Fourth, the most reasonable height that can be obtained by increasing the amount of payload and fuel was investigated. |
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