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.

A thrust vector control actuator is provided including a ram first portion, a ram second portion, the ram second portion housed within the ram first portion and defining a damper cavity between the ram first portion and the ram second portion and the ram second portion configured to operably connect to an output link, and a magneto-rheologic fluid located within the damper cavity, the magneto-rheologic fluid configured to rigidly connect the ram first portion and the ram second portion in a first state, the magneto-rheologic fluid being solid in the first state, and a second state wherein the ram second portion is moveable relative to the ram first portion and the magneto-rheologic fluid is at least partially liquefied.

A thrust vector control actuator is provided including a ram first portion, a ram second portion, the ram second portion housed within the ram first portion and defining a damper cavity between the ram first portion and the ram second portion and the ram second portion configured to operably connect to an output link, and a magneto-rheologic fluid located within the damper cavity, the magneto-rheologic fluid configured to rigidly connect the ram first portion and the ram second portion in a first state, the magneto-rheologic fluid being solid in the first state, and a second state wherein the ram second portion is moveable relative to the ram first portion and the magneto-rheologic fluid is at least partially liquefied.

Apparatus for providing mechanical feedback of a position of an actuator to a controller in a high vibration environment. The apparatus includes a member that contacts a cam surface of the actuator such that movement of the actuator and cam surface causes the member to move. The apparatus also includes a spring that exerts a force on the member toward the cam surface to maintain contact between the member and the cam surface. The apparatus also includes a damper that dampens motion of the member, thereby eliminating resonant movement of the spring and member caused by vibrations.

A pump system includes a turbine shaft including a turbine disposed thereon to rotate the turbine shaft at a turbine shaft speed due to fluid flow through the turbine, a centrifugal pump directly connected to the turbine shaft and configured to pump hydraulic fluid at the turbine shaft speed, a bleed port disposed downstream of the centrifugal pump, and a valve configured to be fluidly connected to the bleed port and configured to meter flow to the turbine to regulate the turbine shaft speed at least partially as a function of pressure from the bleed port.

An aiming assembly comprising an instrument and aiming device, the aiming device comprises: a frame, a mobile part comprising a plate, the instrument being fixed onto the plate, the mobile part and the instrument having a centre of gravity, the mobile part being rotationally mobile relative to the frame on a first axis of rotation, and comprising a support configured to cooperate with the plate to allow the plate to be rotationally mobile relative to the frame about a second axis of rotation at right angles to the first axis of rotation, and rotationally mobile relative to the frame on the first axis, the first and second axes of rotation intersecting at a point of intersection. The point of intersection coincides with the centre of gravity of the mobile part and of the instrument, and the support comprises a flexible part configured to compensate for the differential expansions on the second axis of rotation between the frame and the plate.

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 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 cold gas thruster having a two-stage solenoid is provided. Pressurized gas from the inlet flows to the back side of the piston to hold the piston closed. The pressure is maintained by a check ball held by the solenoid armature. When the solenoid is energized, the armature allows the check ball to move to bleed off the pressure holding the piston closed. The piston moves away from its seat and allows the pressurized gas to flow to the outlet creating thrust. When the solenoid coil is de-energized, the check ball is forced against its seat, which blocks the escape of pressure on the back side of the piston, so that it can re-pressurize back up to the inlet pressure. This creates a force imbalance and moves the piston to close the valve and stop the thrust. Different nozzles can be used for different thrust profiles without changing the solenoid.

Rocket control is a difficult and unpredictable task in environments with inclement weather. As a result, launch missions are often strictly limited based on weather conditions. The present invention provides a device for controlling a rocket to account for environmental uncertainties and maintain optimal mission performance. In embodiments, the device is a radiation hardened field programmable gate array with an embedded artificial intelligence program contained in a graphics processing unit that is used for rocket reaction control by generating thrust vector commands.