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Aircraft/missile central navigation system having inertial detectors generating angle/speed increments and pre processing with sculling/coning compensation applied providing second lower frequency increments deriving angle/speed increments
Aircraft/missile central navigation system having inertial detectors generating angle/speed increments and pre processing with sculling/coning compensation applied providing second lower frequency increments deriving angle/speed increments
The navigation information method produces angle and speed increments with inertial detectors. Pre processing is applied to the parameters producing second increments at a lower frequency. The pre processing is carried out with compensation for the phenomenon of coning and sculling and filtering carried out modifying the pass band. The angle and speed information are then derived from the second increments.
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