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Reusable launcher flight mission
Metelka, Dominik ; Daněk, Vladimír (oponent) ; Zikmund, Pavel (vedoucí práce)
This thesis is split into two main parts which are also the main objectives. The aim of the first part is to describe a mission of a reusable launcher. Firstly, the topic of reusable launch systems and their development until today was approached. Most importantly, the operational reusable launch vehicles are described with the explanation of each booster’s flight mission. Furthermore, alongside some important launch vehicles in development, there is a separate chapter listing the first stage’s return options. The second part is practical with the aim of designing a mission of the launcher reusable first stage. For the calculations, the parameters were chosen according to a current Falcon 9 rocket, from which the final velocity and altitude at which the first stage separates, were analytically calculated. For the return and overall flight mission, a MATLAB script was written to calculate and plot all necessary parameters and characteristics. In the end, the altitude for the engine reignition was also determined to safely land on the ground.
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Reusable launcher flight mission
Metelka, Dominik ; Daněk, Vladimír (oponent) ; Zikmund, Pavel (vedoucí práce)
This thesis is split into two main parts which are also the main objectives. The aim of the first part is to describe a mission of a reusable launcher. Firstly, the topic of reusable launch systems and their development until today was approached. Most importantly, the operational reusable launch vehicles are described with the explanation of each booster’s flight mission. Furthermore, alongside some important launch vehicles in development, there is a separate chapter listing the first stage’s return options. The second part is practical with the aim of designing a mission of the launcher reusable first stage. For the calculations, the parameters were chosen according to a current Falcon 9 rocket, from which the final velocity and altitude at which the first stage separates, were analytically calculated. For the return and overall flight mission, a MATLAB script was written to calculate and plot all necessary parameters and characteristics. In the end, the altitude for the engine reignition was also determined to safely land on the ground.
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