High-performance dual-mode integral propulsion system
AssigneeTRW Inc.
InventorRobert L. Sackheim
Life of this patent
Estimating the term…
Abstract
A propulsion system in which pure hydrazine is used as the fuel for both a bipropellant rocket engine for high-thrust performance and in multiple monopropellant thrusters for station keeping and attitude control functions. Use of a common fuel for both modes of operation significantly reduces propellant weight and inert propulsion system weight for any given mission requirements, and therefore increases the payload that can be delivered to and maintained in a desired orbit. Further, for station-keeping, the monopropellant thrusters can be augmented in performance by employing either electrothermal or additional direct chemical energy, arc jet operation, or force field acceleration, to provide increased specific impulse values up to 2,000 seconds or higher.
Claims3
A high-performance liquid fuel bipropellant high-thrust rocket engine, comprising:
- a fuel supply including a supply tank, fuel line and fuel supply valve;
- an oxidant supply including a supply tank, oxidant line and oxidant supply valve;
- a combustion chamber having an inlet for the fuel and oxidant connected to the fuel and oxidant lines;
- and
- means for minimizing unwanted combustions after shutdown of the engine by delaying closure of the fuel supply valve until after closure of the oxidant supply valve, to ensure that combustion is completed in the combustion chamber.
A method of operating a high-performance liquid-fuel bipropellant high-thrust rocket engine, the method comprising the steps of:
- operating the engine with fuel and oxidizer supply valves open to supply fuel and oxidizer to a combustion chamber;
- shutting down the engine by closing the fuel and oxidizer supply valves to terminate flow of the fuel and oxidizer to the engine combustion chamber;
- and
- controlling the engine during shutdown to minimize combustion of fuel in a region downstream of the fuel supply valve and upstream of the combustion chamber by delaying closure of the fuel supply valve until after closure of the oxidizer supply valve, thereby ensuring that all remaining quantities of the oxidizer have been reacted with fuel in the combustion chamber and not in the region where combustion may otherwise take place.
A dual-mode rocket propulsion system, comprising:
- a high-performance liquid-fuel bipropellant high-thrust engine having a combustion chamber;
- a liquid fuel tank connected to the combustion chamber of the high-thrust engine through a fuel supply valve and a fuel supply line;
- an oxidizer tank connected to the combustion chamber of the high-thrust engine through an oxidizer supply valve and an oxidizer supply line;
- a plurality of monopropellant reaction control motors for station keeping and attitude control connected to the liquid fuel tank and employing the same fuel as the high-thrust engine, thus saving substantial propellant weight and propulsion system inert weight for given mission requirements to provide a high effective payload;
- and
- means for minimizing unwanted combustions after shutdown of the engine by delaying closure of the fuel supply valve until after closure of the oxidant supply valve, to ensure that combustion is completed in the combustion chamber.
Dependencies are inferred from the claim text.