Abstract: A global landing system (GLS) for retrofitting an aircraft having ILS systems, as well as autopilot or flight control computers. The GLS using horizontal and vertical guidance control points (GCPs) which are co-extensive with glideslope and localizer antenna locations, and correction lever arms representing the separation of such GCPs with on-board GPS antennas. A method of measuring such lever arm with an additional GPS receiver is also included.

Abstract: A satellite navigational receiver landing system having retrofit compatibility with integrated landing system (ILS) receivers, in accordance with the invention, includes radio frequency circuitry which converts satellite signals into intermediate signals. A first processing channel coupled to the radio frequency circuitry generates a first position, velocity and time (PVT) solution as a function of the intermediate signals, and provides a PVT data output. A second processing channel coupled to the radio frequency circuitry generates a second PVT solution as a function of the intermediate signals. Monitor circuitry provides monitor output signals as a function of the first and second PVT solutions. Shutdown circuitry provides the first PVT solution to the PVT data output under the control of a shutdown signal from the monitor circuitry.

Abstract: Satellite navigation systems and receivers of the invention include an antenna which receives satellite signals from multiple satellites. Radio frequency circuitry coupled to the antenna converts the satellite signals into intermediate signals. Multiple signal processors coupled to the radio frequency circuitry implement similar or identical signal processing algorithms on the received satellite signals to provide redundant ranging information (i.e., code and carrier measurements). One or more navigation processors coupled to the signal processors process the ranging information and provide positioning data outputs. The navigation processor implements smoothing filter functions that combine the redundant ranging data in a manner which enhances the positional accuracy. The navigation processor also implements unique fault-detection filter functions on the redundant ranging information.