A method for positioning a ram air turbine during its assembly on a primary structure of an aircraft. The method includes the steps of: placing a first distance sensor on a first element among a first flap and the ram air turbine, a second distance sensor on a second element among a second flap and the ram air turbine, the first and second distance sensors being configured to respectively emit first and second signals corresponding to measured values over time of a distance between each of the first and second distance sensors and at least one mobile target attached to the ram air turbine or the first and second flap, pivoting the mast between the retracted and deployed positions, analyzing the first and second signals, and, if necessary, repositioning the ram air turbine according to the step of analyzing the first and second signals.

A power electronics cooling system includes a ram air fan with one or more blades and a ram air fan motor connected via an output shaft. The ram air fan draws in air and passes it across a heat exchanger to cool one or more cooling liquids. One or more pumps pressurize and pump the cooling liquids to various electronic components, including one or more motor controllers. The pumps may be mechanically or electrically coupled to the output shaft of the ram air fan, such that the motor of the ram air fan provides energy to the pumps.

A toggle release mechanism includes a base element, a toggle element and an actuating rod. The toggle element is rotatably mounted at a first end to the base element about a first axis for rotation between a locking position and a release position. The actuating rod has a central portion extending through the toggle element and first and second end portions projecting on opposed sides thereof for engagement with actuators arranged on opposed sides of the release mechanism. The actuating rod also includes a mounting flange projecting therefrom at a boundary between the central portion and a first end portion. The mounting flange has a first hole therein for receiving a first fastener. A surface of the toggle element facing the mounting flange has a bore formed therein for receiving the first fastener. The mechanism also includes a mounting element slidably received on the second end of the rod.

A locking mechanism for a ram air turbine actuator can include at least one of spherical locking pawls configured to retain an outer member and spherical pawl rollers configured to radially actuate the spherical locking pawls by axial movement of the spherical pawl rollers.

A method of electrically powering an electrical load in an aircraft, the method including electrically powering the electrical load with a main source that generates electricity; measuring an instantaneous parameter characterizing the main source; determining a level of use of the main source from the measured instantaneous parameter; adjusting the voltage of the main source as a function of the level of use; measuring an output voltage from the main source; comparing the measured voltage or the level of use with a predetermined threshold value; and whenever the measured voltage is less than the predetermined threshold value, electrically powering the electrical load from an auxiliary source that stores electricity so as to supply additional electric power to the electrical load.

An apparatus for unlocking an actuator comprises a first member mounted in a housing for rotation about an axis and having a circumferentially extending surface, a recess being formed in a section of the circumferentially extending surface. A second member for operative connection to a lock release element of an actuator is mounted for movement in a direction generally transverse to the axis of rotation of the first member and has a follower element resiliently biased into contact with the circumferentially extending surface of the first member. A rotary actuator is provided for rotating the first member about the axis between a first, locking position in which the follower element engages on the circumferentially extending surface and a second, unlocking position in which the follower element is at least partially received within the recess.

In accordance with at least one aspect of this disclosure, an electric aircraft can include an electrical accumulator, an electric propulsion system operatively connected to the electrical accumulator and configured to convert electrical energy into propulsive force, and a ram air turbine (RAT) operatively connected to the electrical accumulator to store energy. The RAT can be selectively deployable between a stowed position wherein the RAT is not exposed to ram air and a deployed position wherein the RAT is exposed to ram air to store energy in the electrical accumulator.

A release mechanism comprises a locking body mounted for reciprocating movement in a first axial direction between a locked position and a released position. A force transmitting element is coupled to the locking body for transmitting a force (F) to the locking body for moving the locking body from the locked position to the released position. A biasing element acts on the locking body in a direction for moving the locking body from the released position to the locked position. The locking body comprises a slot having a first slot portion extending in said first direction, and a second slot portion extending transversely from one side of said first slot portion at an end thereof. The slot slidably receives an actuating element therein.

A system for providing alternating current (AC) power to an aircraft component includes a ram air turbine (RAT) configured to generate AC power. The system also includes an energy storage device configured to output direct current (DC) power. The system also includes an inverter configured to convert the DC power to the AC power. The system also includes a controller coupled to the RAT and the inverter and configured to cause the inverter to provide the AC power to the aircraft component, and to control the RAT to provide the AC power to the aircraft component in response to determining that the RAT can provide the AC power.

A locking mechanism comprises a piston element comprising a piston groove extending in an axial direction along a radially outer surface of the piston element, a housing comprising a bore for receiving the piston element for reciprocating axial movement between a locked position and an unlocked position, a locking ball received in the piston groove and a locking ring mounted for rotational movement about the piston element between a locking position and an unlocking position, the locking ring comprising a radially inner locking ring groove, the locking ring groove having a recess formed in a radially inner surface thereof for receiving the locking ball in the unlocking position of the locking ring. The piston groove comprises a first axially extending section and a second axially extending section, the radial depth (D1) of the first axially extending section being greater than the radial depth (D2) of the second axially extending section.