The liquid-propellant rocket engine has the characteristics that allow it to deliver thrust at a high-performance level, with an efficiency and operational flexibility that enables a number of mission applications to go forward. Monopropellant and bipropellant versions of this category of engine are discussed in some detail in this chapter. Storable and cryogenic propellants are introduced, and their on-board storage requirements are discussed. Pressure-feed and turbopump-feed approaches for moving liquid propellants from their respective storage tanks to the injector head of the engine’s thrust chamber are presented. Liquid injector design considerations are discussed. Thrust chamber design issues are detailed, including dealing with combustion instability symptoms. This chapter is closed out with a discussion of thrust vector control techniques for flight control, via exploiting the main engine nozzle exhaust flow.
Liquid-Propellant Rocket Engines
Powered Flight ; Kapitel : 11 ; 381-415
2012-01-25
35 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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|VARIABLE-THRUST LIQUID PROPELLANT ROCKET ENGINES
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