A liquid fuel rocket engine according to one example includes a combustor, a liquid fuel repository connected to the combustor via a fuel line and a first valve, an oxidizer repository connected to the combustor via an oxidizer line and a second valve, a valve controller configured to output a valve control current to the first valve, the valve controller storing instructions for determining at least one actual minimum impulse bit of a valve based on a current profile and a voltage profile of a single operation of the first valve, and to adjust valve controls to account for the at least one actual minimum impulse bit.

A variable flow area injector for a liquid rocket engine. The injector has a poppet with a variable outer width portion and a housing with a variable inner width portion. An annular flow path is defined between the variable width portions. Increased throttling of the engine passively increases the annular flow area of the injector by forcing the poppet in a distal direction. Decreased throttling allows a restoring spring to move the poppet in a proximal direction to decrease the annular flow area. A bellows can be included to dampen movement of the poppet. The bellows may be in a propellant-filled cavity separate from the main propellant flow path and have a series of openings through which the separate propellant flows.

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 thrust vector control actuator is provided including a ram, a first plate housed within the ram, a second plate housed within the ram, and a dividing wall housed within the ram. The dividing wall being located between the first plate and the second plate. The dividing wall defines a first chamber within the ram comprising the first plate and a second chamber within the ram comprising the second plate. The actuator also includes an output rod housed within the ram. The output rod having a first end and a second end. The second end is configured to operably connect to an output link. The actuator also includes a load relieving mechanism located within the ram. The load relieving mechanism configured to operatively connect the ram and the output rod. The load relieving mechanism is configured to absorb at least one transient load on the output rod.

A power take-off (PTO) system includes a spur pinion on a shaft, used to turn a sector face gear that is coupled to a surface to be turned, such as a jet vane in a rocket nozzle. These may be parts of a thrust vectoring system, with the PTO system used to connect to a control surface actuator for a control surface such as a fin. The mechanical coupling between the fin and the jet vane may enable steering of a flight vehicle such as a missile at both low speeds and high speeds, with the thrust vectoring by the jet vane effective at low airspeeds and the control surface movement used for steering at high airspeeds. The PTO system may be backward compatible with prior systems, while allowing a more direct connection between the control surface actuator and the thrust vectoring system, with a reduced number of parts.

A power take-off (PTO) system includes a spur pinion on a shaft, used to turn a sector face gear that is coupled to a surface to be turned, such as a jet vane in a rocket nozzle. These may be parts of a thrust vectoring system, with the PTO system used to connect to a control surface actuator for a control surface such as a fin. The mechanical coupling between the fin and the jet vane may enable steering of a flight vehicle such as a missile at both low speeds and high speeds, with the thrust vectoring by the jet vane effective at low airspeeds and the control surface movement used for steering at high airspeeds. The PTO system may be backward compatible with prior systems, while allowing a more direct connection between the control surface actuator and the thrust vectoring system, with a reduced number of parts.

A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

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.

A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

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.