GE Aviation Systems LLC

An electrical power system architecture (200) is described herein. In some approaches, an electrical system for an aircraft (100) includes an electrical source (202), an electrical load (204), and a power distribution system (206). The power distribution system (206) includes a plurality of power channels (208) connecting the electrical source (202) to the electrical load (204). The electrical power is distributed in each power channel (208) under normal operating conditions and, in the event of a power channel failure, the electrical power is distributed by a subset of the plurality of power channels (208) such that the aircraft (100) can maintain aircraft flight conditions during the power channel failure.

A system (200) and method for temperature monitoring of power switching devices are described herein. In some approaches, a system (200) for modelling a temperature rise within a transistor (204) with an integrated temperature sensing diode (206) includes a current source (214) and a control unit (216) (218). The current source (214) is configured to provide a current to the integrated temperature sensing diode (206). The control unit (216) (218) is operably coupled to the current source (214) and the integrated temperature sensing diode (206) and configured to receive a temperature dependent voltage signal, determine a temperature rise in the transistor (204) and output a trip signal (238) to turn off the transistor (204) based on the temperature rise.

An electric distribution architecture is described herein. In some embodiments, the electric distribution architecture (300) for an aircraft (100) includes at least one electrical source (314, 324), a plurality of loads (348) including at least one high energy load (350) and at least one low energy load (354) and a power distribution system (332). The power distribution system (332) includes a plurality of contactors (338, 340, 342) configured to selectively distribute electrical power from each of the at least one electrical source (314, 324) to each of the plurality of loads (348). In some approaches, at least one first fast acting high energy protection device (316, 326) is electrically coupled in series with each at least one electrical source (314, 324), and at least one second fast acting high energy protection device (358) is electrically coupled in series with each of the at least one high energy loads (350). In some approaches, the power distribution system (332) is devoid of any high energy protection devices (316, 326, 352).

An airfoil assembly (130, 230) having a trunnion (134, 234) and a spar (136, 236). The trunnion (134, 234) having an inner surface (152, 252) defining a socket (153, 253) with a flared section with an open top. The spar extending from the socket (153, 253) and through the open top (154, 254). Further, the spar (136, 236) being formed by a plurality of composite plies (163, 263) including a radially innermost ply (160, 260) having a respective centerline (176, 276), and a radially outermost ply (162, 262) having a respective centerline (176, 276) that is parallel to the respective centerline (176, 276) of the radially innermost ply (160, 260).

A system and method for fault protection are described herein. An electrical power system architecture (100) for an aircraft includes at least one electrical source (102), at least one electrical load (112), and a power distribution system (106) connecting the at least one electrical source (102) to the at least one electrical load (112). The power distribution system (106) is grounded to an electrical ground (118) of the aircraft through a high impedance grounding circuit (108) and a plurality of protection devices (124) are coupled electrically upstream and downstream of the high impedance grounding circuit (108). In some approaches, the electrical power system architecture (100) includes a fault detection circuit (126) configured to detect a fault and a controller (128) to selectively open or close the plurality of protection devices (124) based on the detected fault. In some approaches, an electrical wiring interconnection system separates positive power 1(114) and negative power lines (116) of the power distribution system (106) for reducing line-to-line faults.

Systems and methods for early detection of electrical arcs or electrical component failures in enclosed modules are provided. A system (100, 200) for detecting electrical component failures or electrical arcs includes: an enclosed module (102, 202) including electrical components (110); a light sensor (118, 218A) in the enclosed module (102, 202) detecting light emitted within the enclosed module (102, 202); and a control circuit (122, 222) operatively coupled to the light sensor (118, 218A), the control circuit (122, 222) triggering a predetermined action upon detection of light in excess of a predetermined light threshold level or detection of predetermined light activity by the light sensor (118, 218A). The predetermined action may include triggering an alert and/or a switch (120, 220) addressing the detection of a possible electrical discharge in the enclosed module (102, 202).

Systems and methods for early detection of smoke or electrical component failure in enclosed modules are provided. A system for detecting smoke, soot, or particulates within enclosures, includes: an enclosed module comprising electrical components; a light source in the enclosed module emitting light continuously or at predetermined time intervals; a light sensor in the enclosed module detecting light emitted by the light source; and a control circuit operatively coupled to the light sensor, the control circuit triggering a predetermined action upon light detected by the light sensor from the light source being at least partially obstructed and falling below a predetermined light threshold level. The predetermined action may include triggering an alert and/or a switch addressing the detection of possible smoke in the enclosed module.

A handheld mobile device (104) may be configured for use within a cockpit or cabin of an aircraft (100). The handheld mobile device (104) may include a display (1004) and memory (1008, 1010) that includes an application configured to utilize the display. The handheld mobile device (104) may also include a processor (1002) coupled to the memory (1008, 1010). The application, via the processor (1002), may be configured to receive aircraft-specific configuration data. The application may also receive, from a tracker module (108), input data corresponding to blade height and position. The application may additionally receive airframe vibration data from an accelerometer module (112). The application may further calculate recommendations regarding track and balance. The application may also further output, via the display (1004), the track and balance recommendations.

A modular power distribution assembly (25) includes a frame (80) defined by a first set of parallel supports (81) and a second set of parallel supports (82), the second set of parallel supports (82) connecting the first set of parallel supports (81), the frame (80) defining a generally planar assembly defining a first side (91) and a second side (92) opposite the first side (91), as well as a set of components (41, 74) extending from a side (91, 92) of the frame (80) and operably coupled to the frame (80). The set of components (41, 74) includes a set of power modules (26, 28).

A proximity sensor (200) comprises a reference inductor (L21), a first set of sensor inductors (L22, L23, L24), a first set of comparators (U22, U23, U24), each comparator of the first set of comparators corresponding to one of the sensor inductors of the first set of sensor inductors, and an alternative current voltage source (V21) to output a sinusoidal voltage to the reference inductor and each of the sensor inductors. Each comparator of the first set of comparators (U22, U23, U24) receives a voltage across the reference inductor (L21) as a reference voltage and each comparator of the first set of comparators (U22, U23, U24) receives a voltage across a corresponding sensor inductor (L22, L23, L24) as an input voltage.