Abstract This chapter handles the second group of space vehicle propulsion. It is concerned with rocket propulsion. A historical introduction of rockets is briefly reviewed. Rockets were invented in China after discovery of gunpowder. It was first employed in fireworks in feasts and other celebrations and later on was utilized in wars. Classifications of rockets based on methods of propulsion, launch mode, range, rocket engine, number of stages, and applications are next emphasized. Rocket performance parameters, namely, thrust force, effective exhaust velocity, exhaust velocity, characteristic velocity, thrust coefficient, specific impulse, total impulse, specific propellant combustion, propellant mass fraction, impulse-to-weight ratio, and different efficiencies, are defined. The governing equations for single and series as well as parallel multistage rocket are derived. Advantages and disadvantages of staging are discussed. Chemical rockets are first classified as solid, liquid, and hybrid types. Rocket engines of each type are next analyzed. Composition of solid propellant and its burning rate is thoroughly discussed. Liquid-propellant rocket engine (LRE) is either monopropellant or bipropellant. The feeding system and its pumps and turbines are briefly highlighted. Hybrid-propellant rockets which combine both liquid and solid propellants are discussed. A closure of this chapter by highlighting other thermal rockets and nuclear and electric propulsion rockets is given.
Rocket Propulsion
01.01.2016
85 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Engineering Index Backfile | 1947
|TIBKAT | 1960
|Engineering Index Backfile | 1961
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