Thermochemical Analysis of Hypergolic Propellants Based on Triethylaluminum/Nitrous Oxide

Table 1

Density and molecular weight of propellant components.

Name	MW	Specific gravity (water = 1)	Ref.
Nitrous oxide	44.01	1.2228^a	[17]
Nitrogen tetroxide/NO2	92.01	1.443	[7]
Liquid oxygen	32	1.1905^b	[7]
Nitric acid	63.01	1.5129	[7]
Hydrazine	32.05	1.0036	[7]
MMH	46.07	0.875	[7]
UDMH	60.1	0.791	[7]
Methanol	32.04	0.7914	[7]
TEA	114.17	0.832	[7]
Hexane	86.18	0.6606	[7]
Nitromethane	61.04	1.1371	[7]
1-Nitropropane	89.09	0.9961	[7]
Aniline	93.13	1.0217	[7]
Air	28.84	0.959^c	[7]

^a1.013 bars, 184.5 K ^b1.013 bars, 80 K; ^c59.75 K.