Abstract of the Disclosure: In an aspect systems and methods for monitoring health of an electric vertical take-off and landing vehicle include at least a flight component, a first sensor, a computing device, and a pilot display. The first sensor is configured to sense a first characteristic associated with the at least a flight component and transmit the first characteristic. The computing device is communicative with the first sensor, and is configured to: receive the first characteristic, analyze the first characteristic, and determine a condition of the at least a flight component as a function of the first characteristic. The pilot display is communicative with the first sensor and the computing device and is configured to: receive the first characteristic and the condition of the at least a flight component and display the first characteristic and the condition of the at least a flight component.

Abstract of the Disclosure: In an aspect systems and methods for monitoring health of an electric vertical take-off and landing vehicle include at least a flight component, a first sensor, a computing device, and a pilot display. The first sensor is configured to sense a first characteristic associated with the at least a flight component and transmit the first characteristic. The computing device is communicative with the first sensor, and is configured to: receive the first characteristic, analyze the first characteristic, and determine a condition of the at least a flight component as a function of the first characteristic. The pilot display is communicative with the first sensor and the computing device and is configured to: receive the first characteristic and the condition of the at least a flight component and display the first characteristic and the condition of the at least a flight component.

A method includes receiving fault code data identifying one or more fault conditions detected onboard an aircraft and receiving fault context data indicating one or more conditions of the aircraft in a timeframe associated with the condition(s). The method also includes generating (based on the fault code data, the fault context data, state data indicating a current state of the aircraft, and historical maintenance data) a first checklist display including a first set of incomplete checklist items. The method further includes receiving input indicating completion of one or more checklist items of the first set of incomplete checklist items and updating the state data based on the input. The method also includes generating (based on the fault code data, the fault context data, the updated state data, and historical maintenance data) a second checklist display including a second set of incomplete checklist items.

A method includes receiving fault code data identifying one or more fault conditions detected onboard an aircraft and receiving fault context data indicating one or more conditions of the aircraft in a timeframe associated with the condition(s). The method also includes generating (based on the fault code data, the fault context data, state data indicating a current state of the aircraft, and historical maintenance data) a first checklist display including a first set of incomplete checklist items. The method further includes receiving input indicating completion of one or more checklist items of the first set of incomplete checklist items and updating the state data based on the input. The method also includes generating (based on the fault code data, the fault context data, the updated state data, and historical maintenance data) a second checklist display including a second set of incomplete checklist items.

In an aspect, a test platform for testing an embedded control system having a plurality of interconnected components is operable to: receive, at run time, configuration data for configuring a system under test (“SUT”) representing the embedded control system, the configuration data specifying: which of the components shall be simulated versus hardware-in-the-loop (HIL) components in the SUT; and an inter-component signal mapping that maps input signals to output signals of the specified simulated or HIL components of the SUT; for each of the simulated or HIL components, automatically activate, at run time, a corresponding object code portion for simulating the embedded system component in the test platform or a corresponding object code portion for facilitating communication with the HIL component connected to the test platform, respectively; and automatically map input signals of the activated object code portions to output signals of the activated code portions according to the signal mapping.

A checking method for checking a power plant of an aircraft, the power plant comprising at least one engine and an air inlet for feeding said at least one engine with air, the power plant including a cloggable filter filtering the air upstream from the engine. An aircraft power check is performed by: determining, in flight or on the ground, the current power actually being developed by the engine without making any allowance for any power losses resulting from the engine being installed in the aircraft or from a level of clogging of the filter, the aircraft power check being considered as being successful when the current power is greater than or equal to a guaranteed minimum power.

A checking method for checking a power plant of an aircraft, the power plant comprising at least one engine and an air inlet for feeding said at least one engine with air, the power plant including a cloggable filter filtering the air upstream from the engine. An aircraft power check is performed by: determining, in flight or on the ground, the current power actually being developed by the engine without making any allowance for any power losses resulting from the engine being installed in the aircraft or from a level of clogging of the filter, the aircraft power check being considered as being successful when the current power is greater than or equal to a guaranteed minimum power.

An example system for determining space availability in an aircraft includes a plurality of laser sensors configured to be positioned in a baggage container at a first wall and a second wall, and the first wall and the second wall face each other. The plurality of laser sensors emit signals within the baggage container and detect reflected responses to generate outputs. The system also includes one or more processors in communication with the plurality of laser sensors for executing instructions stored in non-transitory computer readable media to perform functions including receiving the outputs from the plurality of laser sensors, mapping contents of the baggage container based on the outputs from the plurality of laser sensors, and based on said mapping, outputting data indicative of occupied space in the baggage container.

An example system for determining space availability in an aircraft includes a plurality of laser sensors configured to be positioned in a baggage container at a first wall and a second wall, and the first wall and the second wall face each other. The plurality of laser sensors emit signals within the baggage container and detect reflected responses to generate outputs. The system also includes one or more processors in communication with the plurality of laser sensors for executing instructions stored in non-transitory computer readable media to perform functions including receiving the outputs from the plurality of laser sensors, mapping contents of the baggage container based on the outputs from the plurality of laser sensors, and based on said mapping, outputting data indicative of occupied space in the baggage container.

According to certain aspects of the disclosure, a computer-implemented method may be used for rotorcraft track and balance. The method may include capturing one or more images of at least one rotating blades of a rotorcraft and analyzing the one or more images of the at least one rotating blades to determine blade information. Additionally, the method may include determining a location of the at least one rotating blades in the one or more images based on the blade information and calculating blade position information based on the determined location of the at least one rotating blade and a parameter of a user device capturing the one or more images. Additionally, the method may include displaying the blade position information to the user device and displaying instructions on one or more adjustments to the at least one rotating blades of the rotorcraft based on the blade position information.