Abstract: A system for determining a heading of a vehicle is disclosed. The system includes a magnetometer configured to generate a magnetic heading output signal, and one or more rate gyros configured to generate a gyro angular rate output signal. The system may further include a controller configured to determine a magnetometer heading rate based on the magnetic heading output signal and a gyro heading rate based on the gyro angular rate output signal. The controller may calculate a difference value between the magnetometer heading rate and the gyro heading rate. If the difference value is above a difference threshold value, the controller may calculate an integration value between the magnetometer heading rate and the gyro heading rate, report a positive magnetometer error state if the integration value is above an integration threshold value, and report a negative magnetometer error state if the integration value is below the integration threshold value.

Abstract: A system for determining a heading of a vehicle is disclosed. The system includes a magnetometer configured to generate a magnetic heading output signal, and one or more rate gyros configured to generate a gyro angular rate output signal. The system may further include a controller configured to determine a magnetometer heading rate based on the magnetic heading output signal and a gyro heading rate based on the gyro angular rate output signal. The controller may calculate a difference value between the magnetometer heading rate and the gyro heading rate. If the difference value is above a difference threshold value, the controller may calculate an integration value between the magnetometer heading rate and the gyro heading rate, report a positive magnetometer error state if the integration value is above an integration threshold value, and report a negative magnetometer error state if the integration value is below the integration threshold value.

Abstract: An avionics computing device of an aircraft including a rotor may include a non-transitory computer-readable medium and a processor communicatively coupled to the non-transitory computer-readable medium. Upon an occurrence of a condition indicative of a requirement to perform an autorotation maneuver, the processor may be configured to generate autorotation guidance commands based on a generated feasible three-dimensional autorotation trajectory. The generated feasible three-dimensional autorotation trajectory may be for the autorotation maneuver of an aircraft including a rotor. The generated autorotation guidance commands may be configured to guide a pilot of the aircraft to perform the autorotation maneuver of the aircraft along the generated feasible three-dimensional autorotation trajectory. The processor may further be configured to output data associated with the generated autorotation guidance commands to an input/output device for presentation to the pilot.