Three or more receivers installed in a UAV receive signals from a number of satellites, and generate, based on these received signals, observation data items including information items about distances from the satellites to the receivers. An information processing apparatus calculates, based on these observation data items and on position data items of the plurality of satellites, estimated reception positions at which one or more of the receivers are estimated to receive the signals from the satellites. The information processing apparatus calculates, based on these estimated reception positions and on an estimated posture of the UAV, estimated positions of a ranging apparatus in the UAV. The ranging apparatus measures a distance to a target by applying a laser beam to the target in synchronization with timings at which the receivers receives the signals from the satellites.

A method of determining three-dimensional attitude is provided. The method includes measuring a carrier phase of each satellite signal received at plurality of spaced antenna. A carrier phase difference between the measured carrier phase for each satellite signal from each satellite received at each antenna is determined. The integrity of the integer ambiguity resolution relating to the carrier phase difference is assured by applying a least-square-error solution using differential carrier phase measurements with applied integer ambiguities between at least two of the plurality of antennas and observing measurement residuals after the least-square-error solution is computed and applying an instantaneous test, an interval test and a solution separation function. Three-dimensional attitude is determined from the carrier phase differences upon completion of the integer ambiguity resolution and the assurance of integrity of the integer ambiguity resolution.

In order to provide an aircraft with GLS (GBAS (Ground-Based Augmentation System) Landing System) data packets for a satellite navigation-based automatic landing, the GLS data packets comprising GBAS correction data for a satellite navigation and FAS data that describes a set approach path of the aircraft, SBAS (Satellite-Based Augmentation System) correction data for the satellite navigation are received from an SBAS satellite. The received SBAS correction data are converted into GBAS correction data. The GBAS correction data obtained by the conversion are combined with the FAS data in the GLS data packets. The GLS data packets are transmitted to the aircraft via a radio link.

In order to provide an aircraft with GLS (GBAS (Ground-Based Augmentation System) Landing System) data packets for a satellite navigation-based automatic landing, the GLS data packets comprising GBAS correction data for a satellite navigation and FAS data that describes a set approach path of the aircraft, SBAS (Satellite-Based Augmentation System) correction data for the satellite navigation are received from an SBAS satellite. The received SBAS correction data are converted into GBAS correction data. The GBAS correction data obtained by the conversion are combined with the FAS data in the GLS data packets. The GLS data packets are transmitted to the aircraft via a radio link.

A flight control module for detecting anomalies ILS localizer signals during landing of an aircraft is provided. The flight control module includes a communication interface coupled to a processor. The communication interface is configured to receive an ILS localizer deviation. The processor is configured to compute a plurality of localizer deviations and compare the ILS localizer deviation to an average of the plurality of localizer deviations to detect a low-frequency anomaly in the ILS localizer deviation. The processor is configured to initiate a transition from controlling the aircraft based on the ILS localizer deviation to controlling the aircraft based on a selected one of the plurality of localizer deviations when the low-frequency anomaly is detected.

A flight control module for detecting anomalies ILS localizer signals during landing of an aircraft is provided. The flight control module includes a communication interface coupled to a processor. The communication interface is configured to receive an ILS localizer deviation. The processor is configured to compute a plurality of localizer deviations and compare the ILS localizer deviation to an average of the plurality of localizer deviations to detect a low-frequency anomaly in the ILS localizer deviation. The processor is configured to initiate a transition from controlling the aircraft based on the ILS localizer deviation to controlling the aircraft based on a selected one of the plurality of localizer deviations when the low-frequency anomaly is detected.

A system and related method for determining precision navigation solutions is disclosed. The system decorrelates GPS carrier-phase ambiguities derived from multiple-source GPS information via Least-squares AMBiguity Decorrelation Adjustment (LAMBDA) algorithms. The set of decorrelated floating-point ambiguities is used to compute protection levels and the probability of almost fix (PAF), or the probability that the partial almost-fix solution corresponding to the decorrelated ambiguities is within the region of correctly-fixed or low-error almost-fixed ambiguities. While the PAF remains below threshold and the protection levels remain below alert levels, the optimal navigation solution (floating-point, partial almost-fix, or fully fixed) is generated by fixing the decorrelated ambiguities are one at a time in the LAMBDA domain and replacing the appropriate carrier-phase ambiguities with the corresponding fixed ambiguities, reverting to the last solution if PAF reaches the threshold or if protection levels reach the alert levels.

The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

An interface device that enables a GNSS-based precision approach through the Ground Base Augmentation System (GBAS) function known as the GNSS Landing System (GLS) and/or through Satellite Based Augmentation Systems (SBAS) based Localizer Performance with Vertical Guidance (LPV). The GLS interface device allows a GLS-capable multi-mode receiver to be used on a non-GLS-capable airplane without extensive changes to other airplane systems. The GLS interface device works by intercepting information to and from the multi-mode receiver and modifying the information to make the interface compatible with an airplane that uses ILS guidance. Similarly, the information modifications will make the airplane appear to the multi-mode receiver as if it were a GLS-capable airplane.