A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (I.sub.c), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (e.sub.p), the position error (e.sub.p) being a difference between a reference position (Pos.sub.ref) and a measured position (Pos.sub.meas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (I.sub.d) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

A method and device for protecting an adjacent rupturable component including positioning a sheet of puncture resistant, flexible material including one or more openings at or about the structure opening wherein the one or more openings accommodate the rupturable component; permanently or semi-permanently attaching the sheet to the structure at a first portion of an area of the sheet; and positioning the rupturable component through the one or more openings, such that one or more portions of the rupturable component near the one or more openings are protected by the sheet if the structure becomes frayed; wherein the sheet prevents damage to the rupturable component if the structure frays or fractures at or about the structure opening.

Quick coupling device 1 for transferring liquid for an aircraft, comprising a female member 7 configured to be connected to a first reservoir, said female member 7 forming a passage and comprising a cylindrical portion 13 and a radial portion 14, a male member 2 configured to be connected to a second reservoir, said male member 2 forming a passage, slidably mounted in a liquid-tight manner in the female member 7 and comprising a cylindrical portion 3 and a radial portion 4, and a member 40 for locking the male member 2 in the female member 7, the locking member 40 being disposed between the radial portion 14 of the female member 7 and the radial portion 4 of the male member 2, the locking member 40 surrounding the male member 2 and leaving a limited sliding extent for the male member 2 with respect to the female member 7, engaging with the female member 7 in the locked position and releasing the female member 7 in the unlocked position, the locking member 40 comprising an axial blocking lock that can be actuated by an axial then rotating movement and that can be released by an axial then rotating movement, and a rotation brake, the lock and the brake being active in the locked position.

A valve apparatus for an aircraft fluid system is disclosed including a valve housing and a valve member. The valve member is configured to move between a first position in which fluid is able to flow along the fluid flow path, and a second position in which the fluid flow path restricted. A valve member drive means is configured to operate the valve member via an actuator external to the housing. The valve apparatus further includes a sensor configured to monitor a feature in the housing to determine the position of the valve member.

A method for controlling at least a first turboshaft engine and a second turboshaft engine of a rotorcraft, which set a common kinematic linkage in motion, the rotorcraft having an output electric machine cooperating with a first output kinematic linkage of the first turboshaft engine, the rotorcraft having an input electric machine cooperating with a gas generator of the second turboshaft engine. The method includes the following steps: supplying fuel to the first turboshaft engine, operating the output electric machine in electrical energy generator mode, supplying fuel to the second turboshaft engine, and operating the input electric machine in motor mode in order to supply a second non-zero power to said common kinematic linkage.

A system includes an optical pressure sensor. A controller is operatively connected to receive input from the optical pressure sensor. An output connection is operatively connected to communicate output data from the controller. The controller includes machine readable 5 instructions configured to cause the controller to receive data from an optical pressure sensor, detect an accumulation of contaminant on the optical pressure sensor, and initiate a corrective action through the output connection in response to detecting the accumulation of contaminant.

A measurement system and method for liquid quantity in a receptable, the measurement system including a plurality of sensor units at various locations of the receptacle, the receptable including the liquid therein, each of the plurality of sensor units being on an outside surface of the receptacle, a data receiver coupled to the plurality of sensor units via one or more connectors and configured to receive measurements from the plurality of sensor units via the one or more connectors, and a processor coupled to the data receiver and configured to convert the received measurements from the plurality of sensor units to a measured quantity of liquid inside the receptable.

A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (I.sub.c), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (e.sub.p), the position error (e.sub.p) being a difference between a reference position (Pos.sub.ref) and a measured position (Pos.sub.meas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (I.sub.d) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

Described herein are systems and methods for liquid phase separation for fuel tanks and other vessels. Particularly, aspects of the present disclosure are directed to a backpressure regulator configured to open when pressure of a mixture upstream of the backpressure regulator exceeds a predetermined setpoint and a hydrophobic membrane upstream of the backpressure regulator and downstream of a first conduit. The predetermined setpoint may be determined by at least a bubble point pressure of the hydrophobic membrane. Additionally, the backpressure regulator may be fluidically connected to and downstream of the first conduit, and to at least one pump operably connected to and upstream of the first conduit and the hydrophobic membrane may be fluidically connected to and upstream of a second conduit. The backpressure regulator may be fluidically connected to and upstream of a third conduit and the third conduit may be downstream the first conduit.

A second layer of physical protection against failure for a fuel line of a vehicle for use with high pressure and cryogenic fuels increases safety. The primary fuel line can be assembled from one or more components. The secondary protection is a single outer sleeve that includes a selectively permeable or impermeable membrane and may be reinforced. The sleeve and enclosed volume can also be used to protect against oxygen liquification in cryogenic applications. A means to detect failure of the primary fuel line and optional means to vent leaking fuel depend on the application. Clamp designs may be used to mount and clamp such assemblies in a vehicle structure.