A motor has an oxidizer injector, the oxidizer injector is mainly suitable for using in a combustion chamber, the oxidizer injector has a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber.

A motor has an oxidizer injector, the oxidizer injector is mainly suitable for using in a combustion chamber, the oxidizer injector has a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber.

A hybrid rocket includes a housing having first and second ends, a solid-grain fuel material in the housing and defining a bore extending from end to end, two electrodes positioned adjacent to the fuel material to ignite the fuel material at the first end, a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end, a nozzle positioned at the second end and having a converging portion and a diverging portion, and a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion. The bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the fuel material and primary oxidizer burn while flowing downstream. The diverging portion of the nozzle is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

A hybrid rocket includes a housing having first and second ends, a solid-grain fuel material in the housing and defining a bore extending from end to end, two electrodes positioned adjacent to the fuel material to ignite the fuel material at the first end, a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end, a nozzle positioned at the second end and having a converging portion and a diverging portion, and a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion. The bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the fuel material and primary oxidizer burn while flowing downstream. The diverging portion of the nozzle is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.

A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.

A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer.

An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.

An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.

A high density, generally recognized as safe hybrid rocket motor is described which has a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.