GE Aviation Systems LLC Patente

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.

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).

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 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 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.

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).

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.

A method (400) for monitoring the health of an electric power train (12) is disclosed herein. The method of monitoring the health of the electric power train (12) includes, detecting partial discharge (404) within the electric power train (12) with a partial discharge sensor (102), imaging (406) the electric power train (12) with a camera (100) to generate an image, comparing (408) the detected partial discharge with a partial discharge threshold, comparing (410) the image of the electric power train (12) to a threshold representation, and determining (412) the health of the electric power train (12) based upon the detection of partial discharge and the image of the electric power train (12).

A component (52), (54) for an electrical machine (14) includes an annular body (105), (113) having a set of slots (106), (111) extending axially along a periphery of the body (105), (113). A support block (131) having an elongate body (133) defining a first bore (135) extending axially therethrough is disposed within a respective slot (106), (111). A first electrically conductive winding (90), (109) is disposed to extend axially through the first bore (135).

An apparatus for a sensor for monitoring the health of an electric power train (12) is disclosed herein. A camera (100) includes a camera housing (202) having an imaging end (208) with an end wall (210). A lens (220) positions at or within the end wall (210) and an air circuit (230) passing through the end wall (210) and positioned to direct a supply of air (A) along or at the lens (220). The camera (100) images the electric power train (12) or electric machine (56) to determine the health of the electric power train (12).

A method (500) for monitoring the health of an electric power train (12) or electric machine (56, 120) thereof are disclosed herein. The method (500) includes imaging (508) a rotor (124) at a start of a spin down process to determine a first rotor temperature, and imaging (510) the rotor (124) at an end of or after the spin down process to determine a second rotor temperature to determining a rotor temperature reduction. A maximum rotor temperature can be determined as a summation of the temperature after the spin down process and the rotor temperature reduction, which can be used to indicate health of the electric power train (12) or electric machine (56, 120).

A system (100) and a method (700) for estimating a position (510) of an object (170). The object (170) includes a gradiometer (110). The method (700) includes calculating a gravity vector (270) using a gravity spatial derivative (210) generated by the gradiometer (110) and a plurality of body velocities (220) generated by a body velocity source (120), calculating a gravity potential (430) based on the gravity vector (270), and estimating an inertial measurement unit (IMU)-based position (250) of the object (170) using the gravity vector (270), a body acceleration (230), and a body attitude (240). The IMU (130) generates the body acceleration (230) and the body attitude (240). The method (700) includes estimating a gravity vector-based position (310) of the object (170) using the gravity vector (270) and estimating a gravity map-based position (410) of the object (170) using the gravity potential (430) and one or more gravitational maps (440). The method (700) estimating a position (510) of the object (170) based on the IMU-based position (250), the gravity vector-based position (310), and the gravity map-based position (410). The method (700) includes outputting the position (510) of the object (170) to an output device (150).

Systems (124), methods (700), and other embodiments described herein relate to maintaining the integrity of data transmitted via a time-sensitive network (TSN) end system (124). In one embodiment, a method (700) includes, in response to receiving a data message (314) from an application (512), forming an integrity-enhanced TSN data message (344) by appending an integrity field (330, 332, 334, 336) to the data message (314). The integrity field (330, 332, 334, 336) is at least one or more of a timestamp (320), a checksum (322), a source identifier (324), and a sequence value (326). The method (700) includes transmitting the integrity-enhanced TSN data message (344) to a physical layer (310) via a TSN end system protocol stack (300). The TSN end system protocol stack (300) includes at least one or more of an application interface layer (302), a middleware layer (304), a network stack layer (306), and a TSN end station (308).

A composite airfoil assembly (100) and method of forming includes a spar assembly (120) with a spar core (126) and a spar fiber layer (128) at least partially surrounding the spar core (126), as well as a root assembly (130) with a sleeve assembly (127) carrying a set of spaced wedges (135) defining at least one slot (136) configured to receive a first end (121) of the spar assembly (120).

A method of decentralized collaborative target searching, target tracking, or both, includes initializing a probability distribution over a probabilistic search area (100) with an a priori probability distribution of target locations (302), transmitting the probability distribution to a plurality of vehicles (102A, 104A, 106A, 200, 304), capturing, using a plurality of sensors (304A) on the plurality of vehicles (102A, 104A, 106A, 200, 304), sensor data relating to locations of a target, updating the a priori probability distribution (302) based on the sensor data or based on data observations (600) outside of the plurality of vehicles (102A, 104A, 106A, 200, 304), or both, to provide an updated probability distribution, determining optimal trajectories (102, 104, 106) for the plurality of vehicles (102A, 104A, 106A, 200, 304) using the updated probability distribution and using an ergodic principle to define optimality and based on each vehicle (102A, 104A, 106A, 200, 304) of the plurality of vehicles (102A, 104A, 106A, 200, 304) calculating its own optimal trajectory (102, 104, 106) to enable decentralized calculations, and detecting or tracking, or both, the target based on the determining of the optimal trajectories (102, 104, 106).

A power distribution system (11), (111) for an aircraft (10), and method (400) of operating includes, including determining, by a supplemental electrical power system (30), an operating mode of the aircraft (10), selecting, by the supplemental electrical power system (30), at least one supplementary power source (34a), (34b), (34c) of a set of at least two supplementary power sources (34), and at least one of receiving, by the selected at least one supplementary power source (34a), (34b), (34c), a first current (51) from the primary power bus (23), or selectively providing a second current (52) to the primary power bus (23) from the selected at least one supplementary power source (34a), (34b), (34c).

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A method (200, 300) and apparatus (190) for forming a rotor (52) for an electric machine includes serially adding (202) layers (171, 172, 173, 174) of material to form a rotor body (100) (100) having a radially-extending post (108) configured to receive a set of electrically-conductive windings (115), and also having a radially-extending winding end turn support (161, 162) formed contiguously from the rotor body (100).

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Systems and methods for control of vehicles are provided. A computer-implemented method in example embodiments may include receiving (502), at a computing system comprising one or more processors positioned in a vehicle, voice data from one or more audio sensors positioned in the vehicle. The system can determine (504) whether configuration of a reference voiceprint for a speech processing system of the vehicle is authorized based at least in part on performance data associated with the vehicle. In response to determining that configuration of the reference voiceprint is authorized, a first reference voiceprint based on the reference voice data can be stored (508) and the speech processing system configured (510) to authenticate input voice data for a first set of voice commands based on the reference voiceprint.

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