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 rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

A flow control system (22) includes a fuel passage network (34) that has first (36) and second (38) network portions that are in a parallel flow arrangement with each other. A fueldraulic device (40) is located in the first network portion. Operation of the fueldraulic device varies flow through the first network portion. A flow restriction orifice (42) is located in the fuel passage network and is arranged in series with, and upstream of, the fueldraulic device. The flow restriction orifice is operable to generate a pressure differential that varies responsive to the flow through the first network portion. A flow control valve (44) is located in the second network portion. The flow control valve is operable responsive to the pressure differential across the flow restriction orifice to control flow through the second network portion.

The proposed technology relates to a thrust control apparatus of a propulsion system, and more particularly, to a thrust control apparatus of a solid propulsion system equipped with an aerospike pintle nozzle. The present invention is to simultaneously control the magnitude and direction of thrust by installing a pintle and a thrust vectoring unit at the rear end of a combustion tube of a solid propulsion system.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

Provided is a thrust control apparatus having a plug area variable spike pintle nozzle, in which an aerospike-shaped pintle can be used in a pintle nozzle for precise thrust control. The thrust control apparatus includes a combustion chamber, a motor housing, and an outer pintle nozzle. The motor housing has a driving motor within the combustion chamber. The outer pintle nozzle is moved in a lateral direction by the driving motor.

A modulation device for modulating a gas ejection section, the device being for placing in a nozzle upstream from the throat of the nozzle, the modulation device including a plug having a downstream end forming a member for partially obstructing the nozzle throat; and a plug guide having an internal housing in which the upstream end of the plug is present. The upstream end of the plug is suitable for sliding in the internal housing of the plug guide between a first position in which the upstream end of the plug is present in an upstream portion of the internal housing, and a second position in which the upstream end is present in a downstream portion of the internal housing. The upstream end of the plug is held in the first position by at least one retaining element for breaking under the effect of heat.

A system allowing for the tilting of the rocket motor such that, in the tilted position, the centre of the nozzle is located at least approximately on the neutral orientation axis of said rocket motor.

An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.

The proposed technology relates to a thrust control apparatus of a propulsion system, and more particularly, to a thrust control apparatus of a solid propulsion system equipped with an aerospike pintle nozzle. The present invention is to simultaneously control the magnitude and direction of thrust by installing a pintle and a thrust vectoring unit at the rear end of a combustion tube of a solid propulsion system.