IC4005 Aircraft and Space Propulsion Syllabus:

IC4005 Aircraft and Space Propulsion Syllabus – Anna University PG Syllabus Regulation 2021

COURSE OBJECTIVES:

 To familiarize with the concept of compressible flow and effect of shock waves.
 To recognize and distinguish the working of various aircraft engines.
 To design and match aircraft components and calculate its performance.
 To gain insight on the working principle of rocket engines, different feed systems, propellants and their properties and dynamics of rocket.
 To design rockets for various space applications and calculate rocket performance.

UNIT I WAVE MOTION AND SHOCK WAVES

Wave motion, Mach waves and Mach cone, sound waves, Shock waves – Normal and Oblique, Relation of physical properties across a shock, Deflection Relations, Method of Characteristics – Applications, Problems, Expansion Waves – Introduction.

UNIT II AIR-BREATHING ENGINES

Theory of Aircraft propulsion – Different propulsion systems – Turboprop – Turbojet, Turbojet with after burner, Turbo fan and Turbo shaft, Ramjet, Scramjet. Methods of Thrust augmentation – Thrust vector control, Fuels for jet engines.

UNIT III THERMODYNAMICS OF AIRCRAFT ENGINES

Engine – Aircraft matching – Design of inlets and nozzles – Performance characteristics of Ramjet, Turbojet, Scramjet and Turbofan engines, Problems.

UNIT IV ROCKET PROPULSION

History of rocket propulsion, Deflagration & Detonation, Combustion in solid and liquid propellants rockets, classification of propellants and propellant injection systems – Non equilibrium expansion and supersonic combustion – Propellant feed systems – Reaction Control Systems – Rocket heat transfer. Electric propulsion – classification- electro thermal – electro static – electromagnetic thrusters- geometries of Ion thrusters- beam/plume
characteristics – hall thrusters.

UNIT V ROCKET STAGING AND PERFORMANCE

Rocket equations – Escape and Orbital velocity – Multi-staging of Rockets – Space missions – Performance characteristics of rockets – Losses and efficiencies, Design of Rockets.

COURSE OUTCOMES :

On successful completion of this course, the students will be able to:
1) Use concepts of compressible flow to design variable area ducts for the given conditions.
2) Identify various aircraft engines and know its inner workings with emphasis on its limitations and applications.
3) Mix and match various components of an aircraft engine for its design conditions.
4) Classify various rocket engines based on its type and design it for requirements.
5) Use orbital mechanics principles to design payload for rockets.

REFERENCES:

1. Philip G. Hill and Carl R. Peterson, Mechanics and Thermodynamics of Propulsion, Second Edition, Addition – Wesley Publishing Company, New York, 2009.
2. Cohen, H. Rogers, G.F.C. and Saravanamuttoo, H.I.H, Gas Turbine Theory, Longman,1989
3. G.C. Oates, “Aerothermodynamics of Aircraft Engine Components”, AIAA Education Series, 1985.
4. S. M. Yahya, Fundamentals of Compressible Flow. Third edition, New Age International Pvt. Ltd,2003.
5. George P. Sutton, Oscar Biblarz. Rocket Propulsion Elements, John Wiley & Sons, 8th Edition, 2010.
6. Ramamurthy, Rocket Propulsion, Pan Macmillan (India) Ltd, 2010.
7. W.P.Gill, H.J.Smith& J.E. Ziurys, “Fundamentals of Internal Combustion Engines as applied to Reciprocating, Gas turbine & Jet Propulsion Power Plants”, Oxford & IBH Publishing Co., 1980.