Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.

A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.

A thruster control device has an opening degree estimating section and an opening degree control section. The opening degree estimating section calculates an estimated opening degree of a valve showing a rate at which the valve is opened, based on a balance of an acting force applied to a valve element of the valve to adjust a quantity of combustion gas to be ejected from a thruster and a fluid force applied to the valve element by the ejected combustion gas. The opening degree control section determines a target opening degree based on the estimated opening degree to control the opening degree of the valve.

A thruster control device has an opening degree estimating section and an opening degree control section. The opening degree estimating section calculates an estimated opening degree of a valve showing a rate at which the valve is opened, based on a balance of an acting force applied to a valve element of the valve to adjust a quantity of combustion gas to be ejected from a thruster and a fluid force applied to the valve element by the ejected combustion gas. The opening degree control section determines a target opening degree based on the estimated opening degree to control the opening degree of the valve.

A rocket catapult assembly for an ejection seat may comprise a drive motor, a metering tube, a first cartridge, and a second cartridge. The metering tube may include an outer wall having a gas pervious section and a gas impervious section. The drive motor may be configured to translate the metering tube and align the gas pervious section or gas impervious section with a first cartridge and a second cartridge to produce a desired thrust of the rocket catapult assembly.

A rocket catapult assembly for an ejection seat may comprise a drive motor, a metering tube, a first cartridge, and a second cartridge. The metering tube may include an outer wall having a gas pervious section and a gas impervious section. The drive motor may be configured to translate the metering tube and align the gas pervious section or gas impervious section with a first cartridge and a second cartridge to produce a desired thrust of the rocket catapult assembly.

An air-breathing rocket engine in certain embodiments comprises an outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake and an annular primary combustion chamber between the inner front wall of the shell and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector ports and one or more ignition ports are situated at the front end of the second circumferential gap.

An air-breathing rocket engine in certain embodiments comprises an outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake and an annular primary combustion chamber between the inner front wall of the shell and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector ports and one or more ignition ports are situated at the front end of the second circumferential gap.

Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.

Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.