Abstract: A ram air turbine (RAT) restow system includes an actuator assembly with a piston interposed between an upper fluid compartment and a lower fluid compartment. The actuator assembly is configured to selectively move the piston between a deployed position and a stowed position. A hydraulic restow circuit is interposed between the actuator assembly and a hydraulic fluid system that is configured to output fluid. The hydraulic restow circuit includes a restow valve configured to operate in a first position that establishes a first fluid path to deliver the fluid to the upper fluid compartment and a second position that establishes a second fluid path to deliver the fluid to the lower fluid compartment.

Abstract: A ram air turbine release system including a turbine defining a rotational axis including at least one notch therein for receiving a plunger to prevent rotation of the turbine mechanically by moving between a first position and a second position, and a first bearing system contacting at least a portion of an outer surface of the plunger configured to reduce friction produced when the plunder moves between the first positon and the second position.

Abstract: A hydraulic control valve includes a sleeve with actuator and biasing member ends and a spool with first and second lands. The sleeve defines a bore extending along a spool movement axis, a source port proximate the stow solenoid end and in communication with the bore, and a supply port between the source port and the biasing end. The spool is slidably disposed within the bore, is movable along the spool movement axis between first and second positions, fluidly separates the source port from the supply port in the first position, and allows the bore to fluidly couple the source port with the supply port in the second position. The first land extends circumferentially about the spool and has a first land length, the second land extending circumferentially about the spool and has a second land length, and the first land length is larger than the second land length.

Abstract: Disclosed is an aircraft system comprising: a linkage comprising a first end, an opposing second end and a clevis therebetween; a motion limiter configured to engage the clevis; wherein: the first end is configured for connecting to one of a strut of a ram air turbine (RAT) and an enclosure door, and the second end is configured for connecting with another of the strut and the door; and the motion limiter limits rotation between the first end of the linkage and the second end of the linkage.

Abstract: A ram air turbine release system including a turbine defining a rotational axis including at least one notch therein for receiving a plunger to prevent rotation of the turbine mechanically by moving between a first position and a second position, and a first bearing system contacting at least a portion of an outer surface of the plunger configured to reduce friction produced when the plunder moves between the first positon and the second position.

Abstract: A ram air turbine (RAT) restow system includes an actuator assembly with a piston interposed between an upper fluid compartment and a lower fluid compartment. The actuator assembly is configured to selectively move the piston between a deployed position and a stowed position. A hydraulic restow circuit is interposed between the actuator assembly and a hydraulic fluid system that is configured to output fluid. The hydraulic restow circuit includes a restow valve configured to operate in a first position that establishes a first fluid path to deliver the fluid to the upper fluid compartment and a second position that establishes a second fluid path to deliver the fluid to the lower fluid compartment.

Abstract: A hydraulic control valve includes a sleeve with actuator and biasing member ends and a spool with first and second lands. The sleeve defines a bore extending along a spool movement axis, a source port proximate the stow solenoid end and in communication with the bore, and a supply port between the source port and the biasing end. The spool is slidably disposed within the bore, is movable along the spool movement axis between first and second positions, fluidly separates the source port from the supply port in the first position, and allows the bore to fluidly couple the source port with the supply port in the second position. The first land extends circumferentially about the spool and has a first land length, the second land extending circumferentially about the spool and has a second land length, and the first land length is larger than the second land length.

Abstract: A single-unit nose cone for a ram air including: a dome portion located at a forward end of the single unit nose cone; a dome stand portion adjacent to the dome portion; a seat portion adjacent to the dome stand portion; and a stem portion adjacent to the seat portion and located at an aft end of the single-unit nose cone, wherein the dome portion, the dome stand portion, the seat portion, and the stem portion are composed from a single piece of material having a density of about 0.286 pound/cubic inch (7916 kilogram/cubic meter).

Abstract: A ram air turbine (RAT) system can include a fluid circuit, a turbine, a shaft connected to the turbine to turn with the turbine, and a hydraulic pump connected (e.g., directly) to the shaft and connected to the fluid circuit to pump fluid within the fluid circuit. The hydraulic pump can be a variable displacement pump, for example (e.g., configured to govern a speed of the shaft and turbine). The hydraulic pump can be used to power and provide speed control to an electric generator.

Abstract: Power generation systems for aircraft are described. The power generation systems include at least one aircraft component and a ram air turbine assembly configured to provide power to the at least one aircraft component. The ram air turbine assembly includes a turbine, a power generator operably connected to the turbine, and a continuously variable transmission arranged between the turbine and the power generator, the continuously variable transmission configured to receive an input rotational speed from the turbine and output a constant output rotation speed to enable power generation at the power generator.

Abstract: Disclosed is an aircraft system comprising: a linkage comprising a first end, an opposing second end and a clevis therebetween; a motion limiter configured to engage the clevis; wherein: the first end is configured for connecting to one of a strut of a ram air turbine (RAT) and an enclosure door, and the second end is configured for connecting with another of the strut and the door; and the motion limiter limits rotation between the first end of the linkage and the second end of the linkage.

Abstract: A ram air turbine (RAT) system is provided. The RAT system includes a main generator, a RAT power generation unit, first circuitry, a storage device and second circuitry. The main generator and the RAT power generation unit are connectable to an aircraft bus by the first circuitry. The first circuitry includes a first switch which is controllable such that power is selectively provided to the aircraft bus from one of the main generator and the RAT power generation unit. The storage device is connectable to the aircraft bus by the second circuitry. The second circuitry includes a second switch which is controllable such that power is selectively provided to the aircraft bus from the storage device.

Abstract: A hybrid ram air turbine assembly includes a turbine portion having a plurality of turbine blades connected to a turbine shaft via a hub. A pivot joint is connected to the turbine portion by a hydraulic pump and an electric generator. The hydraulic pump and the electric generator are in-line with each other, and the turbine shaft is connected to a generator input shaft via a first gear set.

Abstract: A ram air turbine actuator having: a housing; at least one solenoid; a latch mechanism operably connected to the at least one solenoid and located within the housing, the latch mechanism in operation moves from a first position to second position when the at least one solenoid is activated; and a hydraulic pressure system operably connected to the latch mechanism, the hydraulic pressure system in operation moves the latch mechanism from the second position to the first position using hydraulic pressure from a hydraulic fluid, when the at least one solenoid is deactivated. The hydraulic pressure system is located within the housing. The hydraulic pressure is relieved when the latch mechanism is in the first position.

Abstract: A single-unit nose cone for a ram air including: a dome portion located at a forward end of the single unit nose cone; a dome stand portion adjacent to the dome portion; a seat portion adjacent to the dome stand portion; and a stem portion adjacent to the seat portion and located at an aft end of the single-unit nose cone, wherein the dome portion, the dome stand portion, the seat portion, and the stem portion are composed from a single piece of material having a density of about 0.286 pound/cubic inch (7916 kilogram/cubic meter).

Abstract: A hybrid ram air turbine assembly includes a turbine portion having a plurality of turbine blades connected to a turbine shaft via a hub. A pivot joint is connected to the turbine portion by a hydraulic pump and an electric generator. The hydraulic pump and the electric generator are in-line with each other, and the turbine shaft is connected to a generator input shaft via a first gear set.

Abstract: A ram air turbine (RAT) system is provided. The RAT system includes a main generator, a RAT power generation unit, first circuitry, a storage device and second circuitry. The main generator and the RAT power generation unit are connectable to an aircraft bus by the first circuitry. The first circuitry includes a first switch which is controllable such that power is selectively provided to the aircraft bus from one of the main generator and the RAT power generation unit. The storage device is connectable to the aircraft bus by the second circuitry. The second circuitry includes a second switch which is controllable such that power is selectively provided to the aircraft bus from the storage device.

Abstract: A speed sensing adapter plate is provided and includes an adapter housing having a perimeter and a central portion and including a body having first and second opposite sides, mounting features disposed in the perimeter to extend from the first side to the second side, a shaft, bearings and a speed sensor. The shaft is disposed in the central portion and includes first and second splines at the first and second sides, respectively, and a flange. The flange is axially interposed between the first and second splines such that input rotational energy is transmittable from the first spline to the second spline via the flange. The bearings are disposed to rotatably support the shaft within the adapter housing. The speed sensor is coupled to the perimeter of the adapter housing and is configured to measure a rotational speed of the shaft from rotational energy driven rotations of the flange.

Abstract: A linear actuator includes a fixed first end, a second end movable linearly along a central axis of the actuator, an inner cylinder configured to urge axial movement of the second end, and a piston assembly including a piston rod located inside of the inner cylinder. One or more locking pawls are located in pawl openings in the piston rod. The one or more locking pawls are selectably engagable with the inner cylinder to prevent relative motion of the piston rod and the inner cylinder. A lockbolt selectably releases the one or more locking pawls from engagement with the inner cylinder and includes an antilock pin engagable with a pawl opening in the one or more locking pawls to urge the one or more locking pawls away from the inner cylinder with axial movement of the lockbolt.

Abstract: Described herein is a system for increasing the robustness of a sealing surface and eliminating an expensive plating operation. The system includes an axially rotatable object comprising a first material that is subject to corrosion. The system also includes a radial shaft seal positioned radially outward from the axially rotatable object. The system also includes a sleeve coupled to the axially rotatable object, positioned between the axially rotatable object and the radial shaft seal and comprising a second material that is corrosion resistant.