Abstract: An AGL (above ground level) altitude module may determine an AGL value for the aircraft. An air data MSL (mean sea level) module may determine an air data MSL value for the aircraft based on an air data measurement. A blending module may generate a synthesized operational altitude value for the aircraft based on the AGL value and the air data MSL value. At least one of may be executed: transmitting the synthesized operational altitude value for display to a user of the aircraft; or partially or fully controlling operation of the aircraft according to the synthesized operational altitude value.

Abstract: A system may include static pressure sensors and dynamic pressure sensors coupled to an aircraft. The system may include an IAS (indicated airspeed) module configured to calculate IAS signals and a pressure altitude module configured to calculate pressure altitude signals from the static pressure signals. The system may include a dynamic fault monitor module configured to generate dynamic fault signals indicating whether faults are detected in the IAS signals. The system may include a static fault monitor module configured to generate static fault signals indicating whether faults are detected in the pressure altitude signals. The system may include a voter module configured to select IAS signals and pressure altitude signals. The system may include an aircraft control router configured (a) transmit the selected signals for display or (b) control the aircraft according to the selected signals.

Abstract: A system may determine, by a ground speed module, a ground speed value for the aircraft. The system may determine, by an air speed module, an air speed value for the aircraft. The system may determine, by an altitude module, an altitude value of the aircraft. The system may generate, by a blending module, a synthesized operational speed value for the aircraft based on the ground speed value, the air speed value, and the altitude value. The system may perform at least one of: sending the synthesized operation speed value for display to a user of the aircraft; or partially or fully controlling operation of the aircraft according to the synthesized operational speed value.

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.