A computer-implemented method of controlling autonomous movement of a mobile object (110) in an aircraft operating area (104) is provided. An autonomous control computing system receives an image (102) from a digital camera (604) positioned to view (308) at least a portion of the mobile object. The system provides the image (102) to a machine learning model to detect within the image (102) one or more self objects (304, 306) affixed to the mobile object (110) and one or more intruder objects (106, 108). The system predicts future locations for the self objects (304, 306) based on a navigation path for the mobile object (110). In response to detecting an overlap between the future locations for the self objects (304, 306) and the intruder objects (106, 108), the system alters the navigation path to prevent a collision. A computer-implemented method of automatically determining a distance to an object in a two-dimensional image is also disclosed.
In some embodiments, a system is provided that includes an edge computing device and at least one camera configured to obtain image data depicting at least a portion of an operations area. The edge computing device includes a non-transitory computer-readable medium that has a model data store and computer-executable instructions stored thereon. The instructions cause the edge computing device to perform actions including receiving at least one image from the at least one camera; processing the at least one image using at least one machine learning model stored in the model data store to determine at least one environmental state within the operations area; and controlling a device based on the determined at least one environmental state. The machine learning model is trained by a model management computing system that obtains training data via low-bandwidth connections to edge computing devices.
In an embodiment, an airport electric vehicle charging system is provided to provide and maintain power to an aircraft. The system is configured to be electrically coupled to a power source that is positioned proximate a gate of an airport and that provides alternating current (AC) power, and which employs: an aircraft power branch configured to acquire first AC power and facilitate providing the first AC power to an aircraft proximate the gate; a ground support equipment (GSE) charging branch configured to acquire second AC power, the GSE charging branch including a battery charger including an AC-DC converter configured to convert the second AC power to direct current (DC) power; and a battery bank comprising one or more batteries electrically coupled to the battery charger. The battery charger is configured to facilitate providing the DC power for charging at least one of (a) the battery bank or (b) one or more electrified GSEs. A controller is also provided in the system to acquire an AC power feedback signal regarding the AC power provided by the power source, acquire an aircraft power feedback signal regarding power consumption of the aircraft coupled to the aircraft power branch; and determine a maximum available excess power based on the AC power feedback signal and the aircraft power feedback signal.
In an embodiment, an airport electric vehicle charging system includes a current transducer electrically coupled with a power source; a solid state converter electrically coupl cable with an aircraft at or near an airport gate and configured to provide and maintain power to the aircraft; and a controller. The system further includes a first feedback loop between the controller and the current transducer; a second feedback loop between the controller and the solid state converter; and a battery charger electrically coupled with tire power source and configured to charge one or more electric vehicles. The first feedback loop provides a first feedback signal generated by the current transducer to the controller. The second feedback loop provides a second feedback signal generated by the solid state converter to the controller. The battery charger is configured to consume power from the power source in accordance with the first and second feedback signals.
An integrated ground support system (10) for an aircraft is described herein, the system including a frame (32) on which the system is arranged as a singular assembly. An engine (14), drive train (18), alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.
F02B 63/04 - Adaptations of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for electric generators
F02B 63/06 - Adaptations of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for pumps
6.
VARIABLE PNEUMATIC OUTPUT WITH CONSTANT ELECTRICAL OUTPUT DRIVEN BY A SINGLE ENGINE
An integrated ground support system (10) for an aircraft is described herein, the system including a frame (32) on which the system is arranged as a singular assembly. An engine (14), drive train (18), alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.
B64F 1/34 - Ground or aircraft-carrier-deck installations for starting propulsion plant
F02B 63/04 - Adaptations of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for electric generators
Event recognition systems include a camera and a controller. The controller is communicatively connectable to the camera, and includes a processor and logic that, when executed by the processor, causes the event recognition system to perform operations including: recognizing an event involving an equipment object based upon image data captured by the camera, executing an event procedure based upon the event, the event procedure including controlling the equipment object, and transmitting the image data to a network-based client based upon the event.
Video messaging systems includes a plurality of camera systems, a plurality of network-based clients, a messaging hub communicatively connectable to the plurality of network-based clients, and a video frame transmission service communicatively connected to the messaging hub. The messaging hub is configured to transmit image data as encoded data to each of the plurality of network-based clients. The video frame transmission service is configured to selectively connect with at least one of the plurality of camera systems for a time period that is based upon a request received from at least one of the plurality of network-based clients.
Event recognition systems include a camera and a controller. The controller is communicatively connectable to the camera, and includes a processor and logic that, when executed by the processor, causes the event recognition system to perform operations including: recognizing an event involving an equipment object based upon image data captured by the camera, executing an event procedure based upon the event, the event procedure including controlling the equipment object, and transmitting the image data to a network-based client based upon the event.
A power unit for producing both alternating current and direct current includes a switcher connected to a direct current source, wherein the switcher includes circuitry configured to produce both alternating current having first characteristics and direct current having second characteristics, wherein the circuitry comprises a plurality of insulated gate bipolar transistor circuits and drive circuits connected to the insulated gate bipolar transistor circuits. The switcher may receive variable voltage and frequency or constant voltage and frequency. In either case, the switcher circuitry is able to provide power of the desired characteristics. The power unit may be used to power aircraft when the aircraft is on the ground.
A system for monitoring aircraft/airport operations is disclosed which includes a controller operatively coupled to a network, a data storage device comprising flight information data that is operatively coupled to the network, a data storage device comprising gate information data that is operatively coupled to the network and at least one user interface wherein a user may access the flight information data and the gate information data. A method of monitoring airport operations is also disclosed which includes accessing a single integrated system having access to flight information data and gate information data and monitoring at least one activity relating to airport operations based upon information accessed in the single integrated system.
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