Abstract: A method, apparatus, and computer program product for detecting anomalies in a landing system. In one embodiment, a magnitude difference between a blended inertial deviation magnitude and a raw deviation magnitude is identified to form a magnitude difference. The magnitude difference is compared to a magnitude threshold. If the magnitude difference exceeds the magnitude threshold, an anomaly in the data is detected.

Abstract: A method for estimating inertial acceleration bias errors including obtaining uncorrected acceleration measurements on board a vehicle; obtaining independent position and independent velocity data of the vehicle; transforming the uncorrected acceleration measurements into a reference frame of the independent position and independent velocity data; blending the transformed acceleration measurements with the independent position and the independent velocity data to produce feedback errors; transforming the feedback errors into the reference frame of the acceleration measurements; multiplying the feedback errors by a gain and integrating to estimate the acceleration measurement bias errors.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: A method, apparatus, and computer program product for detecting anomalies in a landing system. In one embodiment, a magnitude difference between a blended inertial deviation magnitude and a raw deviation magnitude is identified to form a magnitude difference. The magnitude difference is compared to a magnitude threshold. If the magnitude difference exceeds the magnitude threshold, an anomaly in the data is detected.

Abstract: A method for estimating inertial acceleration bias errors including obtaining uncorrected acceleration measurements on board a vehicle; obtaining independent position and independent velocity data of the vehicle; transforming the uncorrected acceleration measurements into a reference frame of the independent position and independent velocity data; blending the transformed acceleration measurements with the independent position and the independent velocity data to produce feedback errors; transforming the feedback errors into the reference frame of the acceleration measurements; multiplying the feedback errors by a gain and integrating to estimate the acceleration measurement bias errors.