GB1291901A - Improvements in or relating to liquid propellant tanks for rocket engines - Google Patents

Abstract

1291901 Rocket propulsion units - propellant storage; forcing liquids by gaseous pressure ROLLS ROYCE Ltd 14 Jan 1970 1789/70 Headings F1J, F1R A liquid propellant tank for use in a rocket engine comprises an outlet and an inlet which is adapted to be connected to a source of pressurized gas, the tank being divided internally into at least two spaces by at least one partition positioned between the inlet and the outlet, the or each partition being provided with one-way valve means which permits liquid propellant to flow between the spaces only in the direction from the inlet to the outlet. The rocket engine shown comprises inner and outer casings 12,10 having end walls 15,17 and an intermediate wall 16 which define two propellant tanks 18,19 to contain liquid oxidiser and liquid fuel respectively. The engine comprises also a combustion chamber 80 and propulsion nozzle 82, fuel being supplied to the chamber through annular passage 94 and orifices 88 and liquid oxidiser being supplied through central passage 90 and orifices 86, the orifices being controlled by a valve member 98 having sealing surfaces 102, 104. Each tank 18,19 is divided into a series of compartments 31 by means of frusto-conical partitions 38 each of which carries at its periphery a flexible skirt 36 which co-operates with the outer casing so as to constitute a one-way valve which permits propellant flow only from left to right as shown in the drawing. The compartments 31 which are adjacent the outlets 24,26 of the tanks 18,19 respectively are smaller in volume than the remaining compartments 31. The outlets 24,26 from the tanks are initially closed by seal members 28,30 which are received in recesses in piston members 46,50 of an axially-movable piston assembly 42, the piston members being inter-connected by a member 53. A duct 72,70, 68,60,64 extends through the piston assembly and a second duct 73,62,66 extends through the piston 50, the ducts communicating with further ducts 56, 92 and 58,96 respectively. A source of fluid under pressure is provided at 74 and upon starting, the fluid is supplied to the frangible members 22, 23 which burst whereby the oxidiser and fuel in the tanks 18,19 is pressurised. At the same time the piston assembly 42 is urged to the right by the fluid under pressure causing the members 28,30 to shear and placing the outlet ducts 24,26 in communication with the ducts 72,73 respectively. Upon opening of the valve 98, oxidiser and fuel flow into the combustion chamber 80 through orifices 86 and 88 respectively. The object of the invention is to ensure that upon deceleration of the vehicle the propellants still cover the outlet ducts 24,26.