Honeywell International Inc.

James D Waid

Kenneth Steven Morgan

Brian E Fly

Michael O Vaujin

Kevin E Dutton

Martin P Ignac

Adam Boseley

Phil Hess

A method and system for navigating an unmanned aerial vehicle (UAV) for aerial refueling is described. A system processor in the UAV receives navigation data from a tanker aircraft and calculates a plurality of relative navigation solutions with respect to the tanker aircraft. The system processor compares the plurality of relative navigation solutions to identify any inconsistent solutions. The inconsistent solutions are discarded and the system processor navigates the UAV in position for refueling using the remaining relative navigation solutions.

Relative navigation for aerial refueling of an unmanned aerial vehicle

A method and apparatus for calculating corrections to a navigation solution based on differential GPS data includes receiving GPS ephemeris from at least three GPS satellites. A PVT solution is resolved from the GPS ephemeris. The PVT solution includes a Circular Error Probable (CEP). Differential GPS data for calculating the corrections to the PVT solution is received. A corrected PVT solution is then based upon the differential GPS data. The corrected PVT solution is compared to an area defined by the CEP. Where the corrected PVT solution is not within the area, the corrected PVT solution is rejected in favor of the PVT solution for determining an accurate navigational solution.

Integrity of differential GPS corrections in navigation devices using military type GPS receivers

A system and method for detecting and excluding false GPS signals are disclosed, which predict a GPS measurement value with a high degree of confidence, compare the predicted value with measured values, and reject a false measurement based on the comparison results. As one example, a tightly coupled GPS/Inertial Navigation System (GPS/INS) is disclosed, which uses a Kalman filter for comparison of a predicted GPS measurement value with measured values (e.g., the residuals) to form the basis for the rejection of false measurements. This rejection is referred to as a chi-squared reject, and can be extended in time in order to apply the same test to a reacquired signal following the loss of an original validated GPS signal. The Kalman filter propagates the receiver's clock bias rate, and enables the system to predict the GPS measurements at the time of reacquisition. The residuals are compared to a limit defined by the uncertainties of the prediction and the measurement errors expected to be involved.

System and method for detecting false navigation signals

A method for guiding the approach and landing of an aircraft is provided. The method involves receiving navigation information from the aircraft, receiving navigation information from an aircraft carrier, integrating the navigation information from the aircraft with the navigation information from the aircraft carrier to determine a relative velocity and a relative position between the aircraft and the aircraft carrier, and propagating the relative velocity and the relative position forward in time for navigation purposes.

Methods and systems of relative navigation for shipboard landings

Methods and systems for providing an estimate of effectiveness of a selected weapon against a selected target prior to release of the weapon are described. One described method comprises receiving a position uncertainty for a weapon platform, receiving a position uncertainty for a selected target, and determining an ability of the selected weapon to navigate to the selected target. An estimated effectiveness of the selected weapon is determined utilizing one or more of the weapon platform position uncertainty, the target position uncertainty, the navigation capability of the selected weapon, and a kill radius for the selected weapon.

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Bradenton, FL, United States of America

James D Waid