FIELD: aircraft engineering.
SUBSTANCE: invention relates to development of aircraft (AC) control systems, particularly, to valid data accessing and diagnostics of aircraft angular velocity sensors (AVSs) with excess number of transducers and identification of their failures. Determination of the valid two-dimensional angular velocity vector relative to aircraft transverse axes and identification of AVSs failures are based on the readings got at cyclic timed inquiry of four AVSs. The measurement axes of the latter should be located in the plane perpendicular to the aircraft lengthwise axis and be noncollinear. Besides, it includes the computation of said vector with the help of aligner cosines of said AVSs measurement axes. In compliance with this invention, said vector is computed at all possible combinations of AVSs pairs. Derived vectors are distributed to groups composed by three two-dimensional vectors computed from the readings of three AVSs while mean vectors are defined by group vectors and indices of scatter relative to the mean average. Defined is the minimum scatter index of all groups in the current cycle and group mean vector with minimum scatter index is taken to be the valid vector approximating to one measured in the current cycle. AVSs failures are identified proceeding from the soundness of transducers their reading having been used to compute the valid vector and from the results of comparison with the tolerance of the transducer actual reading difference module not used in the calculation of the valid vector and its estimated reading. Note here that said estimated reading is defined as the projection of the valid vector onto tested AVS measurement axis.
EFFECT: accessing valid aircraft angular velocity data relative to aircraft transverse axes, faultless operation at failure of AVS of the four, and fault identification.
