FIELD: radio engineering.
SUBSTANCE: invention relates to radio engineering and can be used in designing and upgrading navigation field integrity monitoring means for global navigation satellite systems (GNSS) in terms of monitoring reliability of information received by user navigation equipment (UNE) of an aircraft. In the disclosed method, in the absence of a received additional information transmission (AIT) in the allowable time interval (ATI) at the reference moment in time, the primary valid pairs (PVP) of GNSS are determined by comparing the values of the spatial coordinates of the aircraft generated using the satellite signals received from the GNSS data. If there is a received AIT in the ATI, as well as in the case of a simultaneous absence of the AIT in the ATI and the PVP at the reference moment in time, two-stage control of the reliability of the information received by the aircraft UNE is performed. At the first stage, the value of the first conditional sign of reliability (FCSR) is determined. At the same time, in case of availability of the received AIT in the ATI, the value of the FCSR is determined by detecting compliance or non-compliance of the base and control estimates of the distances between the aircraft and the local control-correcting station (LCCS), and in the case of simultaneous absence of the received AIT in the ATI and the PVP at the reference moment in time, by detecting compliance or non-compliance of the base and predicted estimates of the distance between the aircraft and the LCCS. At the second stage, the value of the second conditional sign of reliability (SCSR) is determined by identifying the conformity or non-conformity of the values formed by UNE of the own spatial coordinates of the aircraft and the predicted values of these coordinates. Decision on the accuracy of the information received by the UNE in the above cases is formed only if the values of the FCSR and SCSR do not contradict the given requirements for information reliability. This makes it possible to significantly reduce the growth of erroneous decisions caused by increase in the distance between the aircraft and the LCCS in the case of the presence of the received AIT in the ATI, as well as in the case of the simultaneous absence of the AIT in the ATI and the PVP at the reference moment in time.
EFFECT: high probability of correct control of reliability of information received by the aircraft UNE.
1 cl, 1 dwg
