FIELD: physics.
SUBSTANCE: group of inventions relates to two systems for integrating and indicating data on angular spatial position and a method for determining a false solution in respect to the angular spatial position of the aircraft. System according to first version comprises main support inertial unit, hybrid support unit, as well as both systems contain main position indication system of aircraft, reserve position indication system of the aircraft, data integration system for angular spatial position, device for controlling angular spatial position. To determine a false solution with respect to the angular spatial position of the aircraft, solutions are generated based on integrated data on the angular spatial position, which is calculated from the results of one or more measurements obtained from the data source to generate a solution from the angular spatial position, comparing first solution on angular spatial position with second solution on angular spatial position, and when first decision on angular spatial position differs from second solution on angular spatial position by value exceeding specified threshold value, displayed by the main display system and/or standby indication system, which of the said solutions - first or second - is false, based on which of the first or second solutions is the most different from the solution based on the integrated angular spatial position data.
EFFECT: failure localization when determining angular spatial position of an aircraft is provided.
20 cl, 7 dwg
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