. "Aeronautics"@en . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . "Thermal rocket propulsion"@en . . "4.00" . "Course Contents The course focuses on thermo-(chemical) rocket propulsion system analysis and design. Topics dealt with include:\n1. Fundamentals of (thermo-chemical) rocket propulsion;\n2. Ideal rocket motor/nozzle: Ideal performances, optimum thrust, characteristic velocity and thrust coefficient, and quality\nfactors;\n3. Nozzles: Types of nozzles (conical, bell, etc.), nozzle dimensions, flow divergence, boundary layers, under- and overexpansion, and Summerfield criterion;\n4. Chemical propellants: Molar mass, specific heat ratio and adiabatic flame temperature calculation for gas mixtures\n(based on known reaction equation), mass density, dynamic viscosity, thermal conductivity;\n5. Chemical equilibrium calculations, hemical equilibrium flow, frozen flow and chemical kinetics; Introduction to program for\ncalculation of chemical equilibrium gas composition and\ngas properties (in tutorial);\n6. Heat transfer & cooling: Convection, radiation and conduction;\n7. Cooling: Thermal insulation, ablation, radiation, film, dump and regenerative cooling;\n8. Liquid rocket engine combustor design: Steady state internal ballistics, liquid\ninjection, operating pressure, chamber pressure drop, and characteristic length;\n9. Solid rocket motor combustor design*: solid regression, grain shape and internal ballistics including operating pressure,\nnecessary\ncondition(s) for stable operation, pressure sensitivity for initial temperature and change in Klemmung, local conditions (flow\nvelocity, pressure, etc.)), and two phase flow;\n10. Hybrid rocket motor combustor design*: Solid regression, grain shape, (quasi-)steady operation (operating pressure, and\nlocal\nconditions (flow velocity, pressure, etc.));\n11-13 Liquid propellant storage and feed systems including gas-pressure and pump fed systems, motor cycles and propellant\ndistribution;\n14. Capita Selecta\n* Only one of the two will be dealt with. This varies from year to year.\nStudy Goals At the end of this course, the student shall be able to perform important steps in the analysis and design of thermo-(chemical)\nrocket propulsion systems using basic methods that allow for taking into account fluid flow, heat addition, propellant thermochemistry, heat transfer and cooling, liquid, solid or hybrid ballistics, (liquid) propellant feeding, and propellant storage." . . "Presential"@en . "TRUE" . . "Master in Aerospace engineering"@en . . "Luchtvaart- en Ruimtevaarttechniek (tudelft.nl)" . "120"^^ . "Presential"@en . "In the MSc programme in Aerospace Engineering, you will have abundant opportunities for working on projects and internships across the globe, taking advantage of established relationships with Schiphol Airport, the European Space Agency, KLM, Airbus and other aerospace industries and research institutes. You will also have the option of working as a team member in international competitions in extra-curricular activities.\n\nAt TU Delft, you will obtain hands-on experience whilst working in test and laboratory facilities that are unsurpassed in Europe. Our facilities include low-speed and high-speed (up to Mach 11) wind tunnels, GPS measurement stations, the Structures and Materials Laboratory, the SIMONA research flight simulator, a Cessna Citation II flying laboratory, a collection of large and small aircraft and spacecraft parts, the Delfi Ground Station for satellite communications and a clean room for research and training on our own university satellites."@en . . . . . . . . . "2"@en . "FALSE" . . "Master"@en . "Thesis" . "2314.00" . "Euro"@en . "20560.00" . "Mandatory" . "no data"@en . "6"^^ . "TRUE" . "Upstream"@en . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .