Abstract: A system (10) is provided for maintaining continuity of hydraulic power from an aircraft engine-driven hydraulic pump (28) to a first set of propulsion control hydraulic loads for controlling the aircraft engine (30). The engine-driven hydraulic pump provides hydraulic power to a second set of airframe hydraulic loads. The engine-driven hydraulic pump has a pump suction (26) having a first pressure and a pump discharge (34) having a second pressure that is greater than the first pressure. The system includes an accumulator (16) coupled to the engine-driven hydraulic pump suction, and the accumulator is chargeable at a third pressure that is less than the first pressure. A relief valve (18) is coupled to the engine-driven hydraulic pump suction, and the relief valve has a relief setpoint at a fourth pressure that is greater than the second pressure.

Abstract: An inlet air demoisturizing system utilizes a plurality of screens between the inlet of a cryogenic engine and a heat exchanger therefor. In a first embodiment, a curtain of liquid air flows on the forward side of the screen to pre-cool the gaseous intake air below the freezing point of water. In a second embodiment, a mist of liquid air is used to pre-cool the air prior to arrival at the screen. The screen traps ice crystals precipitated from the air. In each embodiment, a second sprayer washes the screen with a curtain of liquid water to remove the ice crystals therefrom. Collector troughs collect the liquid air and suspended ice crystals for removal from the engine inlet.

Abstract: A servovalve of the type wherein changes in two primary control pressures, as determined by a primary stage valve, positions a secondary output control valve. The primary stage valve is in the form of two nozzles which direct fluid jets against opposite sides of a rotatable cylinder such that the back pressures from the two jets, which control the position of the secondary output control valve, can be varied as the cylinder rotates. The cylinder is driven by a stepper motor which, in turn, can be controlled by the output of digital computer apparatus.

Abstract: A mechanical apparatus for retaining actuator control in the event of a failure in one of the two cables used to regulate a two cable quadrant type actuator. In response to a cable failure the mechanism transforms the dual cable system into a tension loaded single cable configuration. Operationally, the failure of a cable releases its associated quadrant, which then rotates in response to a tension device acting between the two quadrants until it is driven against a fixed stop. The onset of the quadrant rotation actuates a quadrant lock device to prevent relative motion between the operable quadrant and the output actuation means. The tension device connecting the two quadrants now acts between the inoperable quadrant, resting against a fixed stop, and operable quadrant, such that the operable quadrant has a force tending to rotate it whenever the control cable tension is not balanced by the effects of the tension device.