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Přehled vývoje malých a středních nosných raket
Dítě, Radovan ; Petrásek, Miloslav (oponent) ; Daněk, Vladimír (vedoucí práce)
Tato bakalářská práce je odbornou rešerší zabývající se vývojem malých a středních nosných raket. Práce je rozdělena do čtyř hlavních částí. První část pojednává o základních princi-pech raketové techniky a typech raketových pohonů. Druhá část se zabývá historickým vý-vojem raketové techniky. Ve třetí části je popsán vývoj malých a středních nosných raket. Poslední, čtvrtá část se věnuje současnému stavu malých nosných raket.
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Přehled vývoje nosných raket pro pilotované lety
Šurkala, Martin ; Daniel, Miloš (oponent) ; Daněk, Vladimír (vedoucí práce)
Bakalářská práce popisuje vývoj raketové techniky od jejích počátků aţ po kosmické lety. V první části jsou popsány základní principy reaktivního pohonu a stručný vývoj prvních raket. Následuje kapitola, jeţ popisuje vznik moderní kosmonautiky v podání největších vědců, kteří v oblasti raketové techniky působili na počátku 20. století. V následující části práce je uveden německý raketový program, na který navazují vesmírné programy USA a SSSR (Ruska). V poslední části jsou uvedeny rakety vyuţívány Evropou, Čínou a soukromou společností SpaceX. V této práci nejsou zpracovány pouze v minulosti pouţité nosiče, nýbrţ také nosiče, které se teprve pro svoji první cestu připravují.
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Přehled současných kosmických prostředků
Špačková, Jana ; Daněk, Vladimír (oponent) ; Zikmund, Pavel (vedoucí práce)
Cílem této bakalářské práce je vytvořit přehled běžně používaných a v současné době vyvíjených dopravních prostředků pro přepravu užitečného zatížení do vesmíru a tyto prostředky vzájemně porovnat. První část práce je rozdělena na nosné rakety létající na oběžnou dráhu Země, nosné rakety létající pod oběžnou dráhu Země a na ostatní transportní prostředky vesmírné dopravy. Tyto kapitoly jsou dále členěny dle států a dle stavu vývoje, ve kterém se dopravní prostředky momentálně nacházejí. Druhá část práce se zaměřuje na srovnání prostředků popsaných v první části z hlediska bezpečnosti, výkonů a nákladů využitých na výrobu a provoz. V závěru jsou vyhodnoceny výsledky srovnávací části a je zde okomentován předpoklad vývoje vesmírné dopravy v blízké budoucnosti.
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Magnetorheological Strut for Vibration Isolation System of Space Launcher
Macháček, Ondřej ; Borin, Dmitry (oponent) ; dr hab. inż. Janusz Gołdasz, prof. PK (oponent) ; Mazůrek, Ivan (vedoucí práce)
The dissertation thesis deals with the design of magnetorheological (MR) strut for vibration isolation system (VIS) of the launch vehicle. Previously used VIS and their struts are described in state of the art. Each of the struts which contained any fluid was sealed by static seals and elastic bellows made of steel. The strut of a passive system called ELVIS was chosen as an inspiration and therefore analysed thoroughly. The strut is three-parametric that means the damper is elastically connected. The stiffness of this connection is identical to the projection of bellows volumetric stiffness into the axial direction which is called the pressure thrust stiffness. The method of the pressure thrust stiffness determination from the bellows dimensions is presented in the thesis. Moreover, the parameters which can be used for the modification of the ratio between axial and pressure thrust stiffness of bellows is also discussed. This ratio affects the dynamic behaviour of the strut, thus also the behaviour of whole VIS. The multi-body model of VIS based on the Stewart platform mechanism and detailed multi-body model of a single strut was created for the prediction of their dynamic behaviour in a vibration environment. Simulations have revealed the parameters which affect the efficiency of the MR strut: the time response and the dynamic force range of the MR valve. The range of these parameters which should ensure an effective vibration isolation by the MR strut in the specific VIS was determined by the multi-body model; specifically, time response: 0-5 ms and the dynamic force range 5-10. The final design of the MR strut for the VIS of the launch vehicle preceded the design, manufacture and testing of the experimental strut. The parameters of the experimental strut were measured and consequently used for the verification of models used in the thesis. Knowledge obtained during the tests were used in the final design of the strut. One of the most important detections was that the ferrite (material used in the magnetic circuit) cracked during the semi-active control of the experimental strut. Therefore, a method of the fast magnetic circuit designing was established and subsequently patented. The method is based on a shape modification of the magnetic circuit which ensures shorter time response and the magnetic circuit is manufactured by 3D printing. The MR strut designed in this thesis has a predicted time response of 1.2 ms and dynamic range 10. The method which was used for the design process is summarised in conclusions.
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Vibroizolační plošina pro kosmonautiku
Švábík, Roman ; Klapka, Milan (oponent) ; Mazůrek, Ivan (vedoucí práce)
Bakalářská práce se zabývá návrhem testovacího standu sloužícího převážně k testování vibroizolačních vlastností vibroizolační plošiny kosmického nosiče. Práce obsahuje stručný přehled vibroizolačních systémů, konstrukční požadavky na testovací stand, návrhy konstrukčních variant a výkresovou dokumentaci.
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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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Magnetorheological Strut for Vibration Isolation System of Space Launcher
Macháček, Ondřej ; Borin, Dmitry (oponent) ; dr hab. inż. Janusz Gołdasz, prof. PK (oponent) ; Mazůrek, Ivan (vedoucí práce)
The dissertation thesis deals with the design of magnetorheological (MR) strut for vibration isolation system (VIS) of the launch vehicle. Previously used VIS and their struts are described in state of the art. Each of the struts which contained any fluid was sealed by static seals and elastic bellows made of steel. The strut of a passive system called ELVIS was chosen as an inspiration and therefore analysed thoroughly. The strut is three-parametric that means the damper is elastically connected. The stiffness of this connection is identical to the projection of bellows volumetric stiffness into the axial direction which is called the pressure thrust stiffness. The method of the pressure thrust stiffness determination from the bellows dimensions is presented in the thesis. Moreover, the parameters which can be used for the modification of the ratio between axial and pressure thrust stiffness of bellows is also discussed. This ratio affects the dynamic behaviour of the strut, thus also the behaviour of whole VIS. The multi-body model of VIS based on the Stewart platform mechanism and detailed multi-body model of a single strut was created for the prediction of their dynamic behaviour in a vibration environment. Simulations have revealed the parameters which affect the efficiency of the MR strut: the time response and the dynamic force range of the MR valve. The range of these parameters which should ensure an effective vibration isolation by the MR strut in the specific VIS was determined by the multi-body model; specifically, time response: 0-5 ms and the dynamic force range 5-10. The final design of the MR strut for the VIS of the launch vehicle preceded the design, manufacture and testing of the experimental strut. The parameters of the experimental strut were measured and consequently used for the verification of models used in the thesis. Knowledge obtained during the tests were used in the final design of the strut. One of the most important detections was that the ferrite (material used in the magnetic circuit) cracked during the semi-active control of the experimental strut. Therefore, a method of the fast magnetic circuit designing was established and subsequently patented. The method is based on a shape modification of the magnetic circuit which ensures shorter time response and the magnetic circuit is manufactured by 3D printing. The MR strut designed in this thesis has a predicted time response of 1.2 ms and dynamic range 10. The method which was used for the design process is summarised in conclusions.
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