This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

An aircraft system monitors health of passive safety brakes on a plurality of auxiliary lift wing devices of an aircraft wing. The wing includes an actuator driveline, and a plurality of actuators are secured to the driveline for extending and retracting the auxiliary lift wing devices. Each actuator incorporates a passive safety brake, and a flight computer enables the actuators to synchronously extend and retract the auxiliary lift wing devices. Torque sensors are fixed to the actuator driveline, each torque sensor being positioned adjacent an actuator for sensing static torque values at that actuator location. When an aerodynamic load acting on any one extended auxiliary lift wing device creates a higher static torque value at one actuator location relative to others, the aircraft system generates a warning signal and/or message to indicate occurrence of a potential safety brake failure within the one actuator.

An aircraft system monitors health of passive safety brakes on a plurality of auxiliary lift wing devices of an aircraft wing. The wing includes an actuator driveline, and a plurality of actuators are secured to the driveline for extending and retracting the auxiliary lift wing devices. Each actuator incorporates a passive safety brake, and a flight computer enables the actuators to synchronously extend and retract the auxiliary lift wing devices. Torque sensors are fixed to the actuator driveline, each torque sensor being positioned adjacent an actuator for sensing static torque values at that actuator location. When an aerodynamic load acting on any one extended auxiliary lift wing device creates a higher static torque value at one actuator location relative to others, the aircraft system generates a warning signal and/or message to indicate occurrence of a potential safety brake failure within the one actuator.

A metamaterial-based substrate (meta-substrate) for piezoelectric energy harvesters. The design of the meta-substrate combines kirigami and auxetic topologies to create a high-performance platform including preferable mechanical properties of both metamaterial morphable structures. The creative design of the meta-substrate can improve strain-induced vibration applications in structural health monitoring, internet-of-things systems, micro-electromechanical systems, wireless sensor networks, vibration energy harvesters, and other applications whose efficiency is dependent on their deformation performance. The meta-substrate energy harvesting device includes a meta-material substrate comprising an auxetic frame having two kirigami cuts and a piezoelectric element adhered to the auxetic frame by means of a thin layer of elastic glue.

Methods and systems are provided for assisting operation of a vehicle using speech recognition and transcription to provide a conversation log graphical user interface (GUI) display that consolidates communications with respect to the vehicle. One method involves receiving a data message from a system onboard the vehicle and generating a graphical representation of the data message within the conversation log GUI display, wherein the graphical representation of the data message includes a selectable element and is displayed on the conversation log GUI display concurrently with a graphical representation of a transcription of an audio communication with respect to the vehicle. The depicted data message and transcription are chronologically positioned with respect to one another in accordance with a timestamp associated with the data message. The conversation log GUI display dynamically updates in response to selection of the selectable element.

A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

Systems and methods for mission-based path modifications are presented herein. One or more processors may be coupled with memory and housed in a vehicle. The one or more processors may receive data indicative of an issue with at least one function of the vehicle during a mission defined by a type of cargo and a flight path comprising a plurality of segments. The one or more processors may determine, responsive to the issue with the at least one function, an action to perform for the vehicle based on the issue, a current segment of the plurality of segments, and the mission. The one or more processors may execute, during the current segment or a subsequent segment of the plurality of segments, the action on the vehicle.

Systems and methods for mission-based path modifications are presented herein. One or more processors may be coupled with memory and housed in a vehicle. The one or more processors may receive data indicative of an issue with at least one function of the vehicle during a mission defined by a type of cargo and a flight path comprising a plurality of segments. The one or more processors may determine, responsive to the issue with the at least one function, an action to perform for the vehicle based on the issue, a current segment of the plurality of segments, and the mission. The one or more processors may execute, during the current segment or a subsequent segment of the plurality of segments, the action on the vehicle.