Abstract: The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics (10, 11) and means of connecting these at least two power supply electronics to at least two user systems (12, 13, 14, 15), characterised in that these connecting means comprise a network of connecting contactors (16, 17; 32, 33) from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

Abstract: A power system including at least two self-controlled synchronous machines operating in parallel synchronously, a central three-phase converter to which all these machines are connected in parallel, at least two rotor position sensors. The system also includes at least one control module that receives phase currents from each synchronous machine, signals output from position sensors, and a required reference torque value and that powers the three-phase central converter so as to slave the phase currents for each machine as a function of the required reference torque.

Abstract: The invention relates to a power system comprising at least two self-controlled synchronous machines (MS1, MS2) operating in parallel synchronously, a central three-phase converter (20; 50) to which all these machines are connected in parallel, at least two rotor position sensors (23, 24; 45, 46, 47, 48), characterised in that it comprises at least one control module (25; 30, 31; 53, 54, 55, 56) that receives phase currents from each synchronous machine, signals output from position sensors (23, 24), and a required reference torque value (Cref) and that powers the three-phase central converter (20) so as to slave the phase currents for each machine as a function of the required reference torque (Cref). The invention also concerns a control method for such a system.

Abstract: The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics (10, 11) and means of connecting these at least two power supply electronics to at least two user systems (12, 13, 14, 15), characterised in that these connecting means comprise a network of connecting contactors (16, 17; 32, 33) from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

Abstract: There is provided an adjustable window hinge suitable for casement and awning windows, the window hinge having a longitudinally extending track securable to a window frame, a shoe slidable along the track, a sash arm having one end pivotably connected to the shoe and the other end connected to the window, a support frame having a first end pivotably connected to the sash arm and a second end pivotably connected to the track, the second end being pivotably connected to the track by a rack and pinion arrangement such that rotational movement of the pinion will result in a longitudinal displacement of the stud along the longitudinally extending track.

Abstract: In wall siding panels having vertical edge portions adapted to overlap, fasteners prevent the vertical joint so formed from bending or bulging outwardly. The panels have declinations and flat lengthwise, horizontal shoulders joining the declinations to resemble clapboard finishing. A female aperture is formed in each shoulder of one panel adjacent its vertical edge portion, and a male projection is formed in each shoulder of the other panel adjacent its vertical edge portion. When a pair of two longitudinally-spaced, oppositely-directed projections are provided, which are selectively used so as to permit panel overlapping in any order edge portions are overlapped, each projection elements have identical profiles.