|
|
Flying atmospheric carrier for rocket launches
Musil, Tomáš ; Mašek, Jakub (referee) ; Daněk, Vladimír (advisor)
The main objective of this thesis is to introduce the reader to the problematics of air-launch and to a custom design solution applying this concept. The specifics of this method of bringing a payload into orbit are described and explained. Overview of projects which use aircraft to launch spacecraft is included. Determination of primary parameters of a launch vehicle designed to carry a payload of a specified mass is conducted. The required flight performance has been estimated, a computational model has been developed in software MATLAB, and a multidisciplinary optimization of the design parameters has been performed using a genetic algorithm optimization method. Parameters of the designed air-launched rocket are compared with those of a ground-launched rocket. According to the specific criteria, the Airbus A310-300 aircraft was selected as the most suitable transport aircraft to be used for launching the designed launch vehicle. The last part of the thesis is devoted to the proposal of necessary modifications and estimation of the flight performance.
|
|
|
Overview of current spaceships
Špačková, Jana ; Daněk, Vladimír (referee) ; Zikmund, Pavel (advisor)
Target of this work is to create an overview of commonly used and in this time developed transports used for carrying payload to space and comparing these transportation means. First part of the work is divided into three sections, rockets reaching the Earth’s orbit, rockets flying bellow it and other means of space transport. These sections are further sorted by states and its stage of development they are currently in. Second part of the work is focused on comparing previously described transports from the perspective of safety, power and also costs needed for running and manufacturing them. In the end there are results from the comparing section of this work and comments on the probable path of the near future development of the space transportation.
|
|
|
Measurement of Micro-Accelerations on Board of the Russian Spacecraft „Universat -2“
Fedosov, Viktor ; Kureš, Miroslav (referee) ; Bezděk, Aleš (referee) ; Daněk, Vladimír (advisor)
The Thesis of the dissertation work present results of the accelerometer test operation on board of the Russian small spacecraft Universat – 2. This technical experiment was performed in the frame of the project TEASER (Technological Experiment And Space Environmental Resistance) financed by Ministry of Industry and Trade of the Czech Republic. The principal aim of the project was development and application of end-to-end tests procedures for MAC04TS. Generally, End-to-end Testing is intended for verification of the new product comprehensive operational sequence. In the context of the accelerometer this process includes following aspects: On-Ground Qualification of the instrument flight model and its integration with space platform, operation in orbit to verify the device functionality and performances. The MAC04TS is the new modification of the triaxial electrostatic high sensitive microaccelerometer MAC (or MACEK) designed for measurement of non-gravitational accelerations acting to orbiting spacecraft. Mentioned non-conservative perturbations are primary constraint for theoretical predictions of the spacecrafts orbit evolution. Problem of the precise orbit determination is important not only for ballistic mission analysis and support but at planning and realization of the science researches in Geophysics, Geodesy or in Space Physics branches… Presented text to examination is devoted to partial task of the MAC04TS end-to-end testing, especially, measurement and analysis of the micro-gravitational accelerations in the instrument position on board of the spacecraft. Solution of the problem is based on two methods. The first method was based on the calculation of the accelerations by telemetry information about satellite attitude motion. The second method consisted in direct measuring the accelerations by the triaxial low frequency accelerometer MAC04TS and subsequent smoothing measurement data. Comparison of the acceleration values, obtained by different ways, was carried out as a result of constructing the approximation of the measured acceleration values by their calculated values. The approximation was constructed by the least squares method. Both methods gave similar results. The received estimations of the accelerometer measurements can be used for the analysis of the accelerometer verification.
|
|
| |
|
| |
|
| |
|
|
Survey of the Space Rocketplanes Development
Kapoun, Tomáš ; Cejpek, Jakub (referee) ; Daněk, Vladimír (advisor)
This bachelor thesis maps the historical and technical development of space shuttles from their inception to the present. In the introduction shuttles are divided into categories and then the reasons of formation of these machines are described. The second part deals with the development itself has various designs and not only the USA and the USSR, but describes the Space Shuttle in Europe and Japan. The penultimate chapter describes two tragic accidents USA Shuttles and their causes. The last part of this work is the conclusion with the intended development of astronautics in the near future.
|
|
| |
|
|
History of civil avaition from beginning till the end of 1918
Soukop, Robin ; Daněk, Vladimír (referee) ; Chlebek, Jiří (advisor)
This bachelor thesis contains whole review of the civil aviation history from the first steps and early attempts at fly till year 1918 when flying became a common part of lifes and show of human advanced as well. Attention is paid to all relevant events of the aviation history from the first kites till the fly of the Wright brothers. As well like the events this thesis resumes all persones who influenced the aviation most with their lifes and particular contribution included.
|
|
|
Reusable launcher flight mission
Metelka, Dominik ; Daněk, Vladimír (referee) ; Zikmund, Pavel (advisor)
Tato práce je rozdělena do dvou hlavních částí, které jsou také hlavní cíle. Cílem první části je popis mise vícenásobně použitelného prvního stupně nosné rakety. V této části je nejdříve přiblíženo téma znovupoužitelných kosmických systémů a jejich vývoj do současné doby. Hlavně jsou však v této části popsány operačně používané vícenásobně použitelné nosné rakety, kde u každé z nich je poté popsána jejich letecká mise. Dále jsou zmíněny některé důležité nosné rakety ve vývoji a také jaké jsou způsoby návratu prvního stupně. Druhá část je praktická a cílem je návrh mise návratu prvního stupně nosné rakety na zemi. Pro výpočty byly zvoleny parametry podle současné rakety Falcon 9, ze kterých byla analyticky vypočtena finální rychlost a výška, ve které se první stupeň oddělí od zbytku rakety. Pro návrat a celkový let byl pomocí programu MATLAB napsán skript, který vypočítal a vykreslil potřebné parametry a charakteristiky. Díky tomu bylo také zjištěno, v jaké výšce bude potřeba znovu zažehnout motory, aby první stupeň bezpečně přistál na zemi.
|
guest ::
RSS feed.