Abstract: An emergency module may determine the occurrence of an autorotation condition for a rotary wing air vehicle controlled by a user. The emergency module may, responsive to determining the occurrence of the autorotation condition, control the air vehicle to enter into an autorotation. The emergency module may perform one or more non-user actions during the autorotation to assist the user with the autorotation. The emergency module may, while performing the one or more non-user actions during the autorotation, allow the user to maneuver the air vehicle by interacting one or more control interfaces of the air vehicle.

Abstract: An emergency module may determine occurrence of emergency events of a vehicle traversing through an environment. The emergency module may rank the emergency events according to importance level associated with each emergency event. The emergency module may select an emergency event based on the ranking. The emergency module may notify a user of the vehicle of the selected emergency event. The emergency module may identify corrective actions associated with the selected emergency event, the identified corrective actions including a user action and a non-user action. The emergency module may perform the non-user action of the identified corrective actions. The emergency module may notify the user of the vehicle of the user action.

Abstract: A vehicle control and interface system configured to provide dynamic flight envelope protection of an aerial vehicle is described. In particular, the system dynamically calculates allowable trajectory limits for each axis of control through all phases of flight of an aerial vehicle and provides a visualization of the calculated limits on a graphical user interface. During normal operation, the system does not allow the operator to exceed the calculated limits. Responsive to receiving specified user input to modify vehicle navigation, however, the system causes the aircraft to enter an extended envelope by degrading vehicle parameters according to a hierarchy. Moreover, the system is configured to allow the vehicle to operate in a degraded flight state during a prolonged loss of a sensor signal by setting an adjustable hover trim position of each inceptor device and allowing an operator to control horizontal acceleration of the vehicle.

Abstract: Embodiments relate to an aircraft control and interface system configured to adaptively control an aircraft according to different flight states by modifying one or more processing control loops. The system receives sensor data from one or more sensors of the aircraft. The system determines, from the sensor data, a component of the aircraft is compromised. The system determines the aircraft is in a degraded flight state due to the compromised component. The system operates the aircraft according to the degraded flight state, wherein operating the aircraft according to the degraded flight state includes: (a) modifying one or more processing loops based on the degraded flight state and (b) generating an actuator command by applying the degraded flight state and a signal based on an input from a vehicle control interface to the modified one or more processing loops.