GB1210601A - Rocket propulsion system - Google Patents

Abstract

1,210,601. Rocket propulsion. MOTORENUND TURBINEN-UNION MUNCHEN G.m.b.H. Jan.30, 1968 [Feb.11, 1967], No.4832/68. Heading F1J. The invention relates to a rocket propulsion system using cryogenic propellant components for example liquid hydrogen and liquid oxygen, wherein one or more of the propellants are, prior to launching of the propulsion system, heated by the ambient temperature and converted to the gaseous state and in which after the starting phase the liquid propellants are heated by heat transfer from the combustion chamber and propulsion nozzle and are supplied into the combustion chamber in the gaseous state. In Figs.1 and 2 the system comprises combustion chamber 1 and propulsion nozzle 2 and propellant storage tanks 14, 19, one propellant, say fuel, passing from tank 14 through line 15 and thence through passages 9 extending along the nozzle 2 whereby the nozzle is cooled and the fuel converted to the gaseous state, the gaseous fuel then passing through line 18 to injector assembly 4, 6 into the combustion chamber. Similarly, the other propellant say oxidizer passes from tank 19 through line 20 and thence through passages 8 extending along the combustion chamber 1 whereby the combustion chamber is cooled and the oxidizer converted to the gaseous state, the gaseous oxidizer then passing through line 22 to injector assembly 5, 7 into the combustion chamber. The supply lines 15, 20 are not insulated so that at starting the fuel and oxidizer in the lines are converted to the gaseous state by the ambient temperature. The tanks 14 and 19 are however insulated as indicated at 23, 24. In Fig.4 (not shown), the gaseous propellants are mixed in line 30 before discharge into the combustion chamber and metal powder is injected into the gaseous propellant mixture. In Fig. 5 additional lines 32, 33 lead from the upper parts of the propellant tanks 14, 19, valves 34, 35 being provided in the lines. The lines 32, 33 connect with lines 15, 20 downstream of valves 36, 37 all respectively. Gaseous fuel and oxidizer forming in the tanks 14, 19 passes through lines 32, 33 and thence to the combustion chamber. In Fig.7 (not shown) reservoir chambers 40 are provided in the propellant supply lines adjacent to control valves 4, 5. In Fig.9 a main propulsion system 1 and an auxiliary propulsion system 43 are provided. Fuel and oxidizer are contained in tanks 14, 19 as before, liquid propellants passing through lines 45, 46 to the main propulsion unit and gaseous propellants formed in the tanks passing through lines 47, 48 under control of valves 50, 49 to the auxiliary propulsion unit.