The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.

A wireless autopilot system includes a mounting plate for securement onto a flight control surface of an aircraft, an airfoil, and a flight control device. The flight control device is connected to the mounting plate, and an elongated bracket functions as an anti-flutter counterbalance. A servomotor is connected to the airfoil by the elongated bracket, and a controller having a wireless transceiver for communicating with an application on an externally located processor enabled device is located within the main body. Changes in the position of the servomotor during flight are instructed by the application, and result in a change to the orientation of the aircraft.

A ram air turbine (RAT) assembly includes a turbine having at least one turbine blade that rotates about a turbine driveshaft, a lower gear box coupled to the driveshaft, a generator/pump housing and a strut connected between the lower gear box and the generator/pump housing. The assembly also includes a damping element connected to one of the strut and the lower gear box. The damping element includes an actuator including an extendable member and a mass element connected to the extendable member and that can be moved by the extendable member from a retracted position to an extended position, wherein the mass element is closer to the actuator when in the retracted position than when in the extended position.

The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

An aircraft hydraulic control system includes a pump system, a fluid circuit, and a controller. The pump system includes a hydraulic pump and a ram air turbine assembly. The fluid circuit delivers hydraulic fluid to the hydraulic pump and receives the hydraulic fluid output from the hydraulic pump. The controller is in signal communication with the hydraulic pump. The controller determines a rotational frequency of a ram air turbine included in the ram air turbine assembly, and controls the hydraulic pump so as to control the flow of hydraulic fluid in the fluid circuit. The flow of hydraulic fluid in the fluid circuit controls a fluid pressure of the aircraft.

The present disclosure provides for ram air turbine deployment actuator assemblies utilizing an actuator heater. More particularly, the present disclosure provides for ram air turbine deployment actuator assemblies utilizing an integrated electric heater element in the actuator housing. The present disclosure provides that by warming the hydraulic fluid in a ram air turbine deployment actuator assembly via an actuator heating member (e.g., by warming the hydraulic fluid in a hydraulic fluid cavity or chamber that provides an integrated hydraulic snubbing loop), the viscosity of the hydraulic fluid is reduced, thus helping to reduce ram air turbine deployment time via the actuator heating member of the ram air turbine deployment actuator assembly.

A ram air turbine (RAT) assembly includes a turbine having at least one turbine blade that rotates about a turbine driveshaft, a lower gear box coupled to the driveshaft, a generator/pump housing and a strut connected between the lower gear box and the generator/pump housing. The assembly also includes a damping element connected to one of the strut and the lower gear box. The damping element includes an actuator including an extendable member and a mass element connected to the extendable member and that can be moved by the extendable member from a retracted position to an extended position, wherein the mass element is closer to the actuator when in the retracted position than when in the extended position.

An electricity generation and propulsion system of an aircraft is provided. The electricity generation and propulsion system includes a fuselage, a hybrid-electric power generation system operably disposed in the fuselage and a ram air turbine (RAT) device. The RAT device is coupled with the hybrid-electric power generation system and is stowable in the fuselage and deployable to an exterior of the fuselage. The RAT device is operable as a RAT when deployed into an airstream that drives rotations of the RAT from which the hybrid-electric power generation system generates electricity, and the RAT device is operable as a propulsor when deployed and driven by the hybrid-electric power generation system.