A system and a method include a user interface including a display and an input device. The input device is configured to be operated to provide parameters for a flight of an aircraft. A control unit is in communication with the user interface. The control unit is configured to receive the parameters from the user interface, and determine one or both of emissions of the aircraft during phases of the flight of the aircraft, or emissions costs for the flight of the aircraft.

Systems and methods are provided for airport network-based surface collision avoidance. An aircraft position is received from at least one geospatial sensor. An intruder aircraft position is received via a communication system. A ground surface network is retrieved from an aircraft moving database. The intruder aircraft position is mapped to a first ground surface pathway and the aircraft position is mapped to a second ground surface pathway. A sum of half of a wingspan of the intruder aircraft and half of a wingspan of the aircraft is compared to a distance between a first centerline of the first ground surface pathway and a second centerline of the second ground surface pathway. A potential wingtip collision alert is issued for display based on the comparison.

Systems and methods for optimizing energy usage and/or emissions for a given flight by providing an optimum profile for an aerial vehicle. The systems can utilize weather data and a performance model of the aerial vehicle to calculate energy usage by the aerial vehicle at various altitudes and speeds along the flight route. The systems can further determine the optimal altitude and speed profile along the flight route for the aerial vehicle, which defines the altitudes along the flight route that result in the minimum energy usage for the aerial vehicle. The systems can further provide reports to users.

Systems and methods for optimizing energy usage and/or emissions for a given flight by providing an optimum profile for an aerial vehicle. The systems can utilize weather data and a performance model of the aerial vehicle to calculate energy usage by the aerial vehicle at various altitudes and speeds along the flight route. The systems can further determine the optimal altitude and speed profile along the flight route for the aerial vehicle, which defines the altitudes along the flight route that result in the minimum energy usage for the aerial vehicle. The systems can further provide reports to users.

The present invention relates to a power electronics unit for controlling an electric drive machine, with an inverter arranged in a housing for actuating a hydraulic pump, wherein at least a first electrical plug connector and a second electrical plug connector are formed between the inverter and the hydraulic pump. The first electrical plug connector and the second electrical plug connector have a common central fixing point on an inner side of the housing. Furthermore, the present invention relates to an electric drive machine and an electric drive train.

The present invention relates to a power electronics unit for controlling an electric drive machine, with an inverter arranged in a housing for actuating a hydraulic pump, wherein at least a first electrical plug connector and a second electrical plug connector are formed between the inverter and the hydraulic pump. The first electrical plug connector and the second electrical plug connector have a common central fixing point on an inner side of the housing. Furthermore, the present invention relates to an electric drive machine and an electric drive train.

A system and a method for detecting and protecting an aircraft against inappropriate piloting by a pilot potentially experiencing spatial disorientation related to a somatogravic illusion. The method includes: obtaining flight information and status information; estimating a current value of a perceived longitudinal attitude based on the flight information; computing a difference between the current value of the perceived longitudinal attitude and a current value of an actual longitudinal attitude; and then determining, when this deviation is greater than or equal to a predetermined longitudinal attitude deviation threshold, whether a piloting action performed by the pilot is inappropriate based on the status information of the aircraft; and then activating, when the performed piloting action is inappropriate, a protective measure.

A method for providing a color-annotated display on an aircraft. Embodiments include receiving an image from a camera on the aircraft, determining one or more color regions in the image, accessing a color map based upon the one or more color regions, generating a color-annotated image, wherein one or more regions in the color-annotated image corresponding to the one or more color regions in the image are remapped based upon the color map, and displaying the color-annotated image in the aircraft.

A method for providing a color-annotated display on an aircraft. Embodiments include receiving an image from a camera on the aircraft, determining one or more color regions in the image, accessing a color map based upon the one or more color regions, generating a color-annotated image, wherein one or more regions in the color-annotated image corresponding to the one or more color regions in the image are remapped based upon the color map, and displaying the color-annotated image in the aircraft.

A method includes receiving information of a free route airspace (FRA) downpath along a flight plan of an aircraft, and displaying, on at least one display device on the aircraft, the FRA on an avionics display. The method also includes displaying, on an avionics display of the at least one display device, a graphical user interface (GUI) showing an FRA route factor selection panel comprising multiple selectable flight plan parameter priorities available to be used to generate an FRA flight plan extending at least partially through the FRA. The method also includes receiving a selection of one or more of the FRA flight plan parameter priorities and selected by using the GUI. The method also includes displaying, on an avionics display of the at least one display device, at least one automatically generated FRA flight plan generated by using at least one of the selected flight plan parameter priorities.