Raumfahrtantriebe I
Spacecraft Propulsion I

Modul MW2120

Dieses Modul wird durch Professur für Raumfahrtantriebe (Prof. Haidn) bereitgestellt.

Diese Modulbeschreibung enthält neben den eigentlichen Beschreibungen der Inhalte, Lernergebnisse, Lehr- und Lernmethoden und Prüfungsformen auch Verweise auf die aktuellen Lehrveranstaltungen und Termine für die Modulprüfung in den jeweiligen Abschnitten.

Modulversion vom WS 2013/4

Von dieser Modulbeschreibung gibt es historische Versionen. Eine Modulbeschreibung ist immer so lange gültig, bis sie von einer neuen abgelöst wird.

verfügbare Modulversionen
WS 2017/8WS 2013/4

Basisdaten

MW2120 ist ein Modul in auf das unregelmäßig angeboten wird.

Das Modul ist Bestandteil der folgenden Kataloge in den Studienangeboten der Physik.

  • Allgemeiner Katalog der nichtphysikalischen Wahlfächer
GesamtaufwandPräsenzveranstaltungenUmfang (ECTS)
150 h  h 5 CP

Inhalte, Lernergebnisse und Voraussetzungen

Inhalt

In the lecture "Raumfahrtantriebe 1", the fundamentals of rocket propulsion technology are conveyed using the example of commercial space transport systems. In addition to the basic concepts of orbital mechanics, typical characteristics of rocket engines are introduced and discussed. Liquid-propellant rocket engines constitute a major topic of the lectures. Fuel types, construction methods, the individual thrust chamber components, and turbopump units are explained separately. The special features of auxiliary and satellite engines are discussed separately. Also, the main features and characteristics of the groups of solid and hybrid propellants, ramjets, as well as electrical and nuclear rocket propulsion systems are examined. In addition to the fundamentals, special features of current engine developments are given, as well as insights into the industrial environment and the European organization of the rocket propulsion business. The lecture is complemented and deepened by exercises which the students can use in self-studying.

Lernergebnisse

After taking part in the "Rocket Propulsion 1" course, the students can define important terms of the rocket technique and name important influencing variables. They can understand the complexity of the processes in rocket propulsion. It is possible for them to analyze real rocket engines using simplified replacement models about essential characteristics and to evaluate them using their performance characteristics.

Voraussetzungen

Thermodynamics 1, Fluid Mechanics 1, Gas dynamics

Lehrveranstaltungen, Lern- und Lehrmethoden und Literaturhinweise

Lehrveranstaltungen und Termine

ArtSWSTitelDozent(en)Termine
VO 2 Raumfahrtantriebe 1 (MW2120) Do, 08:30–10:00, 5506.EG.608M
VO 1 Übung zu Raumfahrtantriebe 1 (MW2120) Do, 10:15–11:00, 5506.EG.608M

Lern- und Lehrmethoden

In the course, the content of the lectures is given by oral and media presentation. In the summer semester, the lectures will be held in German and during the winter semester in English. Concepts and basic relationships are presented and deepened using real applications or computer examples. The presentation of the lectures, additional information, and exercises with sample solutions, as well as a comprehensive questionnaire for self-studying are provided by the TUM learning platform. A special exam questions period is held shortly before the examination date. Individual questions can be discussed directly after the lecture with the lecturers or in the assistant lecturer's office (by scheduling an appointment). A non-compulsory teaching excursion complements the module.

Medienformen

Oral exposition, media presentation, laptop PC with beamer, and handouts. In the exercises, important relations are repeated, and one of the exercises is pre-calculated. Further exercises with sample solutions are provided for self-study.

Literatur

George P. Sutton, Oscar Biblarz: "Rocket Propulsion Elements"; 7th Ed., Wiley-Interscience, 2000, ISBN 0-471-32642-9

Modulprüfung

Beschreibung der Prüfungs- und Studienleistungen

The learning success is verified using a written exam consisting of two parts of approximately same size equally weighted. The first part is a short questionnaire which checks the knowledge of the subject-specific basic concepts and essential principles. In the subsequent calculation part, the student is supposed to apply the mathematical relationships presented in the lectures to various problems in the area of liquid and solid propellant rocket propulsion. The written exam lasts 90 minutes: 45 minutes for the short questions and 45 minutes for the calculation part. No tools are allowed for the short questions section, while all tools are allowed for the calculation part. Each semester the written exam is offered in both German and English language.

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