METHOD OF TROUBLESHOOTING AND FAILURES OF AIRCRAFT MEASUREMENT PARAMETERS OF MOVEMENT AND SATELLITE NAVIGATION SYSTEMS OF MOVING OBJECTS Russian patent published in 2018 - IPC G01C25/00 

FIELD: instrument engineering.

SUBSTANCE: invention relates to the field of navigational instrument making and can be used in systems for detecting malfunctions and failures of airborne motion measurement meters (for example, Doppler navigation system, bar-altimeter, radio altimeter, etc.) and satellite navigation equipment of moving objects. Main dynamic properties of the object are used – the area of the possible location of the object is predicted at the time of subsequent satellite navigation measurements. In this case, the corrected location of the object in space for subsequent satellite navigation measurements is the intersection of the space areas of the subsequent satellite navigation measurements with the predicted areas. By comparing and statistically analyzing the areas of the space of successive satellite navigation measurements of the location of the object and the predicted area of the space of the possible location of the object (based on its dynamic properties for moving in space) at the time of the subsequent measurements, it is possible to draw conclusions about the reliability of the indications of satellite navigation aids or the readings of the on-board measuring instruments of the motion parameters. To implement the method, the device consists of a computational unit 3, which receives the current measurement data from the SNS (input E), on-board parameters of the motion parameters of the object BI1..BIn (inputs F1 to Fn) and the wind sensor (input G). Block 3 realizes the calculation of the corrected location of the object using the dynamic recurrence correction algorithm [1]. To fix the time slices of the SNS, BI and wind sensor signals input to the calculating unit 3, the time synchronization signals from the time synchronization device 4 are provided. Block 3 calculates the corrected volume of space using the DRC algorithm, and in block 6 (comparison scheme), the ratio of the predicted area of space to the area of the current navigation measurement space is compared with the threshold value (Λ_ETC ∩ Λ_MOD)/Λ_MOD≤K_THR. Threshold value is entered in block 6. Predicted values of the area of the possible location of the object are stored in the random access memory (RAM), block 2. If condition Λ_ETC/Λ_MOD≤K_THR. At the output of block 6, a signal is generated, which is the control for writing the stack in RAM (block 2) and forms the time instant t_j for the time synchronization device 4. RAM stores all the intermediate results of measurements of the SNS, BI, and the wind sensor in the range of at least m consecutive measurements (for the SNS as the system with the lowest update rate of information) and n measurements from the time t_j (stack control signal for RAM). Together with the measurement values in the RAM, the time intervals for data input from the SNS, BI and wind sensor are also recorded.

EFFECT: increase of functional reliability.

1 cl, 4 dwg