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MAE 4262: ROCKETS AND MISSION ANALYSIS

Fall 2014, Tuesday and Thursday 11:00 am 12:15 pm, F.W. Olin Life Sciences 130 Course Website: http://my.fit.edu/~dkirk/4262

Daniel R. Kirk

Professor

Email: dkirk@fit.edu

Phone: (321) 674-7622

Office: Olin Engineering Center 215

Office Hours: Tuesday and Thursday 2:00 4:00 pm

Overview

This course addresses rocket propulsion, with the primary emphasis being on chemical rockets.

Aspects of fluid dynamics, compressible flows, equilibrium thermodynamics, heat transfer, and

combustion, which govern of rocket-propulsion applications, will be covered. The course will

emphasize theoretical concepts and their application to solving basic problems in rocket science.

Required Text:

Sforza, P. M. Theory of Aerospace Propulsion, Elsevier 2012 Supplemental Texts:

P.G. Hill and C.R. Peterson, Mechanics and Thermodynamics of Propulsion, Addison-Wesley, Second Edition (1992).

The course will also rely heavily on class notes as well as supplemental references.

Course and Learning Objectives:

Rocket Propulsion is an application based course which uses physics and engineering principles

to design and analyze propulsion systems. At the conclusion of the course, each student will be

able to:

Explain the principles of operation and advantages/disadvantages for chemical and electric rocket propulsion components and systems.

Analyze the performance of an ideal rocket engine and describe non-idealities that are inherent to actual systems.

Select a rocket propulsion system based on mission requirements and make appropriate propellant choices.

Perform calculations to determine rocket chamber temperature and chemical composition for various propellant combinations.

Calculate specific impulse and explain the difference between frozen and shifting equilibrium nozzle flows.

Design and specify elements of a liquid propellant rocket engine, including: cycle selection, propellant combinations, combustion chamber, injectors, nozzle geometry, heat

transfer and cooling characteristics.

Design a solid propellant rocket motor based on propellant combinations, burning rates and grain geometry.

Understand basic principles behind electric, nuclear and nuclear thermal propulsion concepts

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Grading:

Homework: 25%, Exams: 45% (15% each), Comprehensive Final Exam: 30%, Concept Quizzes:

~5%

Notes:

1. Concept Quizzes will be given almost every class. Most importantly, this is an opportunity for me to see if you understand the fundamentals of what is being presented,

as well as for self-assessment. These quizzes can only help your grade.

2. Homework submission flexibility ~ 24 hours when necessary. If you decide to work in groups, indicate on the first page who you worked with.

3. The grade weightings are approximate, and I will vary them somewhat, but only if it is in your favor. For example, if you show consistent improvement throughout the course,

your grade will reflect your improvement.

4. The syllabus is an outline of the course content, and contains an ambitious amount of material. Some of the content may be abbreviated or extended for additional lectures,

based on the pace of the course. For particularly challenging topics, class or review

sessions will be dedicated to going over example problems.

5. Consult the Student Handbook and Plagiarism Policy for any questions regarding academic conduct and integrity.