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Unit V – 07A306 - Elements of Aeronautics Aircraft Power Plants and Rocket Engines U. Selvakumar, Lecturer, Dept of aero, BIT, Sathy Unit V – 07A306 - Elements of Aeronautics Syllabus Principles of operation of rockets Types of rockets Typical applications Exploration into space Unit V – 07A306 - Elements of Aeronautics Text and References Principal Textbooks : Gas Turbine Theory H. Cohen , G.F.C. Rogers , H.I.H . Saravanamutto – Third Edition 1987 Rocket Propulsion Elements – George. P. Sutton – Third Edition 1967 Supplemental References : The Jet Engine Rolls – Royce Publication – 1986 Introduction to Space Sciences and Spacecraft Applications – B.A. Campbell , S.W. McCandless JR 1996 Unit V – 07A306 - Elements of Aeronautics Helpful Resources http://www.utsi.edu/Academic/graduate.html http:/www.eevl.ac.uk http://www.aoe.vt.edu/Mason/ACinfoTOC.html Unit V – 07A306 - Elements of Aeronautics Types of Rockets Based on Gas acceleration mechanism Thermal Electrostatic Electromagnetic Based on Energy Source Chemical ( always “thermal” ) Nuclear ( Thermal , Electric ) Solar ( Thermal , Electric) Based on Thrust Level High thrust ( >= 1g ) Low thrust ( 105 – 102 g ) > Solid Liquid /Gas > Monopropellant Hybrid Bipropellant Unit V – 07A306 - Elements of Aeronautics SolidPropellant Rocket Motor Mixed fuel and oxidizer External ignition Burn to completion Unit V – 07A306 - Elements of Aeronautics SolidPropellant Rocket Motor Thrust is proportional to burning area Grain pattern affects the thrust profile Propellant chamber must withstand high 'P' and 'T' Environmentally unfriendly exhaust gases Unit V – 07A306 - Elements of Aeronautics Liquid / GasPropellant Rocket Motor Monopropellant : Catalytic ignition Chemical decomposition Bipropellant : Separate fuel and oxidizer Hypergolic ( spontaneous ) ignition External ignition Throttlable Start and stop cycling Unit V – 07A306 - Elements of Aeronautics Liquid / GasPropellant Rocket Motor Unit V – 07A306 - Elements of Aeronautics HybridPropellant Rocket Motor Solid fuel and liquid oxidizer Nitrous oxide (oxidizer) Hydroxy Terminated Polybutadyene (fuel) Separate fuel and oxidizer Issues : Hard start Blow back Complete mixing of oxidizer and fuel toward completion of burn Unit V – 07A306 - Elements of Aeronautics HybridPropellant Rocket Motor Unit V – 07A306 - Elements of Aeronautics Rocket Thrust Thrust = m propellant V exhaust + A exit ( p exit p ambient ) = m ceff m = mass flow rate of onboard propellant Unit V – 07A306 - Elements of Aeronautics Rocket Parameters I sp =Thrust /Weight flow rate of propellant Unit =m/ s/m/ s =s μ = minitial /m final Mass ratio λ = m payload /minitial Payload ratio η = m structure /minitial Structural ratio ε = m propellant /minitial Propellant ratio minitial =m payload mstructural/enginem propellant mfinal =m payload m structural/engine Ɛ+λ+η = 1 ... Syllabus Principles of operation of rockets Types of rockets Typical applications Exploration into space Unit V – 07A306 - Elements of Aeronautics Text? ?and? ?References Principal Textbooks :... Aeronautics SolidPropellant? ?Rocket? ?Motor Mixed fuel? ?and? ?oxidizer External ignition Burn to completion Unit V – 07A306 - Elements of Aeronautics SolidPropellant? ?Rocket? ?Motor Thrust is proportional to burning area ... Propellant chamber must withstand high ''P''? ?and? ? ''T'' Environmentally unfriendly exhaust gases Unit V – 07A306 - Elements of Aeronautics Liquid / GasPropellant? ?Rocket? ?Motor Monopropellant :