Abstract
Liquid rocket motors are introduced and the details of various types of nozzles, including conical, bell, plug, and extendable nozzles, are described. Nozzle thrust, velocity, and discharge coefficients are explained. The variation of specific impulse with nozzle expansion ratio and the effects of altitude and propellant density on performance are described. The general features of liquid propellant rocket motors are described and detailed performance analyses of LH2/LOX, RP-1/LOX, and LCH4/LOX propellant combinations are presented. The characteristics of various rocket propellants, including cryogenic, hypergolic, and monopropellant materials, are described. Liquid propellant rocket motor operational considerations such as combustion chambers, propellant injectors, nozzle heat transfer, combustion instability, condensation in nozzles, and thrust vector control are discussed. The layout and structural design of propellant tanks is illustrated and the different types of propellant feed systems are discussed.
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