A propellant injector is adapted to be installed to a hybrid rocket engine and includes an injector casing, a tube and a plurality of blades. The tube is arranged along a center axis of the propellant injector in an inner space of the injector casing. The plurality of blades is disposed to and evenly distributed over an outer surface of the tube, and is configured to cause vortices toward a combustion chamber of the hybrid rocket engine when being driven to rotate.

A propellant injector is adapted to be installed to a hybrid rocket engine and includes an injector casing, a tube and a plurality of blades. The tube is arranged along a center axis of the propellant injector in an inner space of the injector casing. The plurality of blades is disposed to and evenly distributed over an outer surface of the tube, and is configured to cause vortices toward a combustion chamber of the hybrid rocket engine when being driven to rotate.

A rocket engine comprises a combustion chamber and a rocket nozzle that communicates with the combustion chamber. A metal wire supply device supplies a metal wire, which is fuel, to the combustion chamber. A water vapor generator supplies water vapor as an oxidant to the combustion chamber. An ignition device ignites the metal wire in a water vapor atmosphere.

A hybrid propulsion unit, for a space vehicle or rocket, includes an external body defining a combustion chamber configured to receive a block of solid propellant, a pressurized reservoir configured to receive a liquid propellant, and a nozzle to eject the combustion gases produced by the reaction of the propellants. The pressurized reservoir being placed inside the external body, surrounded by the block of solid propellant. The propulsion unit further includes a plurality of liquid-propellant injectors disposed axially between parts of the solid propellant to improve the efficacy of the combustion. A space vehicle, of the launch vehicle type, equipped with such hybrid propulsion unit.

A hybrid propulsion unit, for a space vehicle or rocket, includes an external body defining a combustion chamber configured to receive a block of solid propellant, a pressurized reservoir configured to receive a liquid propellant, and a nozzle to eject the combustion gases produced by the reaction of the propellants. The pressurized reservoir being placed inside the external body, surrounded by the block of solid propellant. The propulsion unit further includes a plurality of liquid-propellant injectors disposed axially between parts of the solid propellant to improve the efficacy of the combustion. A space vehicle, of the launch vehicle type, equipped with such hybrid propulsion unit.

A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.

A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.

Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal end of the housing. The injector ring can include a plurality of angled injector units each including a first injector and a second injector angled towards an impingement point. A first fluid stream of a liquid propellant dispensed from the first injector can collide with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation. At least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall to create a swirl flow of the atomized injector fluid

Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal end of the housing. The injector ring can include a plurality of angled injector units each including a first injector and a second injector angled towards an impingement point. A first fluid stream of a liquid propellant dispensed from the first injector can collide with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation. At least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall to create a swirl flow of the atomized injector fluid

Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.