METHOD OF MIXING OF HYPERGOLIC PROPELLANTS

摘要

rocket engines and gas generators. SUBSTANCE: method designed for realizing working process in mixing head of chamber of liquid propellant rocket engine comes to the following: one component of propellant is delivered in form of cylindrical film, second component is mixed with first one being delivered in transverse direction relative to film of first component in form of regulated cellular uniformly distributed system of jets. Mixed components form combined uninterrupted flow for a period not exceeding duration of liquid-phase induction. Second component can be fed tangentially relative to cylindrical flow of first component. Control of working process by this method it possible to improve homogeneity of mixture, reduce maximum median diameter with resulting increase in completeness of fuel combustion, improve dynamic characteristics of ignition process and decrease reduced length of combustion chamber. EFFECT: improved mixing of propellants. 3 cl, 4 dwg