Systems and methods providing an actionable cockpit in an aircraft. The actionable cockpit is a flight control system/method that includes a human machine interface (HMI) in the cockpit of the aircraft. The actionable cockpit is configured to effectively convert one or more non-interactive charts/pages and non-interactive windows and webpages displayed by pilots into interactive versions of themselves, and, to respond to pilot selections on the interactive versions by transferring selected information seamlessly between the multiple sources/applications. Additionally, embodiments of the actionable cockpit can map the pilot selections to an intended concept or target avionic system, suggest possible follow up actions related to the concept, and automatically begin an action when it is selected.

A system for autonomous flight collision avoidance in ana electric aircraft, where the system includes an electric aircraft. The electric aircraft includes a at least a sensor coupled to the electric aircraft, where the at least a sensor coupled to the aircraft is configured to detect an obstacle in the electric aircraft's flight path and transmit the obstacle to a flight controller. The electric aircraft also includes a flight controller where the flight controller is configured to receive the obstacle from the at least a sensor coupled to the electric aircraft, determine an adjusted flight path as a function of the obstacle, and transmit the adjusted flight path to a pilot display. The system further includes a pilot display, where the pilot display is configured to receive the adjusted flight path form the flight controller and display the adjusted flight path to a user.

A system for autonomous flight collision avoidance in ana electric aircraft, where the system includes an electric aircraft. The electric aircraft includes a at least a sensor coupled to the electric aircraft, where the at least a sensor coupled to the aircraft is configured to detect an obstacle in the electric aircraft's flight path and transmit the obstacle to a flight controller. The electric aircraft also includes a flight controller where the flight controller is configured to receive the obstacle from the at least a sensor coupled to the electric aircraft, determine an adjusted flight path as a function of the obstacle, and transmit the adjusted flight path to a pilot display. The system further includes a pilot display, where the pilot display is configured to receive the adjusted flight path form the flight controller and display the adjusted flight path to a user.

A system for fly by view in an electric aircraft, where the system includes an electric aircraft, where the electric aircraft further includes at least a flight component mechanically coupled to the electric aircraft, a battery assembly and at least on video transmitter coupled to the electric aircraft, where the at least one video transmitter is configured to transmit a pilot stream to a first-person-view headset. The system also includes a first-person-view headset, where the first-person-view headset is configured to receive the pilot stream from at least one video transmitter, and display the pilot stream to a user, where displaying the pilot stream includes displaying a flight time remaining metric as a function of the remaining charge of the battery, and displaying a flight component output metric as a function of the performance of the flight component.

A method and system for automating the de-icing/anti-icing of an aircraft that includes the generation of a treatment plan that incudes input from at least one weather source. The treatment plan may then be reviewed by a pilot to any updates. After being finalized, the treatment plan is distributed to at least one de-icing vehicle to perform the de-icing/anti-icing of the aircraft. During execution of the de-icing/anti-icing, real-time updates may be provided by the system to the pilot of the aircraft.

A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

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.