GB761070A - Propellant composition - Google Patents

Abstract

A spontaneously inflammable fuel composition for thrust engines, such as rocket motors and jet engines, comprises a mixture of fuming nitric acid and a sulphide of formula RR1S wherein R is an alkenyl radicle containing 2-4 carbon atoms and R1 is an alkenyl radicle containing 2-4 carbon atoms, an alkyl radicle containing 1-4 carbon atoms or a phenyl radicle, the amount of nitric acid being from 80 to about 100 per cent of the quantity stoichiometrically required for complete oxidation of the sulphide. Where commercial fuming nitric acid is employed, a small amount of N2O5 may be added to the acid to render it anhydrous. Ignition accelerators, such as nitrogen dioxide, sulphuric acid or nitroso-sulphuric acid, may also be added to the fuming nitric acid. Light hydrocarbon oils may be added to the sulphides. In the case of di-alkenyl sulphides, other reducing agents, particularly olefinically-unsaturated amines such as vinylamine, allylamine, diallylamine, diallyl toluidine or allyl xylidines, may be added. Sulphides mentioned are divinyl diallyl, dibutenyl, methyl allyl, ethyl vinyl, butenyl butyl and phenyl allyl sulphides and mixtures of these sulphides. In the examples, fuel compositions are described which consist of white fuming nitric acid and diallyl sulphide (with or without diallyl aniline, furfurylamine or a light hydrocarbon oil having an end point of about 250 DEG F.), divinyl sulphide, dibutenyl sulphide, butenyl butyl sulphide or allyl phenyl sulphide. In further examples, fuel compositions are described which consist of red fuming nitric acid, or a blend of white fuming nitric acid and sulphuric acid, together with divinyl sulphide, or a blend of diallyl sulphide and a light hydrocarbon oil having an end point of about 250 DEG F. The nitric acid and the sulphide may be injected separately but simultaneously into the combustion zone of the thrust engine.