Multicomponent propellants

Utilization of Multicomponent Propellants. One approach to the utilization of a metallized system such as that involving hydrazine, aluminum, and oxygen is to inject the three components separately into the combustion chamber (tripropellant system). This avoids the problems associated with the suspension of the metal in the fuel or oxidizer (and is therefore not a heterogeneous propellant), but it imposes other prob-... 

IV. D. The extension of the propellant combination from two compounds, ie., a bipropellant system, to more than two compounds, ie., a multicomponent propellant system, offers the potential of increasing performance above levels obtainable with propellant systems limited to two propellants. However, this increase in performance results simply from the possibility of conveniently introducing more elements into the combustion process. 

P.I. Gold, Chemical species and chemical reactions of importance in nonequilibrium propellant performance calculations, NASA Accession No N66-33714, Rept No NASA-CR-65442, avail CFSTI, SciTechAerosp Rept 4 (19), 3722 (1966) CA 67, 4484 (1967) 47) S.S. Cherry L.J. van Nice, Pyrodynamics 6 (3-4), 275 (1969) CA 70, 98394 (1969) 48) R.E. Lo, Theoretical performance of the multicomponent rocket propellant system (oxygen, fluorine/ beryllium, lithium hydride)/hydrogen, Deutsche Versuchsanst Luft- und Raumfehri Rept11968, DLR-Mitt-68-21 (Ger), avail CFSTI, SciTech Aerosp Rept 7 (1), 161 (1969) CA 71,... 

Traditionally the liquid systems are considered to be either bipropellants or mono-propellants although as discussed in later sections multicomponent systems are feasible. The most common liquid systems are the bipropellant ones in which the fuel and oxidizer are introduced separately into the rocket combustion chamber. 

Figure 4.26. Flow system and setup for simultaneous multicomponent gradient scanning by flame photometric FI A embodying standard addition. The sample (5) is initially aspirated into loop L, which upon turning of the valve (V) is propelled forward by pump P through the FI A system and toward the detector (F), the sample being sandwiched between the inert carrier solution (water) and an infinitely long zone of standard carrier solution (SC) F, flame nebulizer-burner T, timer A/, scanning monochromator O, storage oscilloscope and R, X-Y recorder.

Energetic Materials 29. The Fast Thermal Decomposition Characterizatics of a Multicomponent Material Liquid Gun Propellant 1845 Combustion and Flame 74, 81-89. 

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