A ram-body for use with a spherical bearing has an inner circumferential surface. The ram-body comprises at least a first concave section provided in said inner circumferential surface. In some examples, a second concave section may be provided diametrically opposite to the first concave section. In some examples, the concave sections may be lunular shaped. A method of manufacturing the ram-body is also described. A ram-body and spherical bearing assembly is also described.

Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

Methods, systems, and apparatuses for an electric aircraft may be shown and described. The electric aircraft may include a body; a first wing and a second wing, each of the first wing and the second wing having a plurality of stabilizers and a plurality of flaps; a cockpit; and at least one of a dielectric elastomer power generator, a wind turbine, an electric jet turbine, and a rotational electromagnetic power generator mounted on a central plane surface on the body.

An actuator release mechanism includes: a longitudinal sleeve movable along an axis between a lock and release positions; drive means for causing the longitudinal sleeve to move along the axis; and bias means to bias the longitudinal sleeve to the lock position. The drive means includes: a rotary solenoid having a first direction of rotation and a second direction of rotation; a toggle member having a toggle shaft connected to and rotatable with the rotary solenoid, and a toggle head in engagement with the longitudinal sleeve by pins extending radially inwards from the longitudinal sleeve and a helical guide rail provided on a radially outer surface of the toggle head. The longitudinal sleeve is mounted around the toggle head, such that rotation of the solenoid causes rotation of the toggle member and the guide rails which causes the pin(s) to ride along the guide rail to rotate the sleeve.

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.

Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric-based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.

The invention relates to a system for synchronising energy sources coupled to an electrical grid supplying at least one electrical load of an aircraft, said system comprising; a main source of electrical energy supplying said electrical load comprising a multi-stage generator, said multi-stage generator comprising; a primary stage comprising a generator with permanent magnets, a secondary stage comprising an excitation, and a tertiary stage comprising a main generator; an auxiliary source of electrical energy supplying said electrical load; and a device for synchronising the main source and the auxiliary source, designed to measure an electrical voltage at the outlet of the primary stage of the main source, and to control the supply of said electrical load by means of the auxiliary source of electrical energy at an electrical voltage slaved to the characteristics of frequency and phase of the electrical voltage of the primary stage.

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.

An installation configuration for a ram air turbine on an aircraft arranged to operate during a low speed operation. An example aircraft includes a fuselage and a lifting body connected to the fuselage and configured to provide a lifting force on the fuselage, the lifting body including a suction surface and a pressure surface disposed on opposite sides of the lifting body from each other, the suction surface extending from a leading edge of the lifting body to a trailing edge of the lifting body. A ram air turbine is coupled to the lifting body and configured to move between a retracted position where the ram air turbine is stowed inside the aircraft and an extended position where the ram air turbine is disposed above the suction surface of the lifting body.

A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.