Redundant Technology Of Inertial Navigation Systems In Airborne Avionics Systems

As the request of flight safety improves and the complexity of the tasks grows, modern aircraftsput forward higher and higher requirements of reliability to the airborne integrated avionics systems.As the core component of avionics system, inertial navigation systems are also facing increasingdemand of reliability. At present, redundant configuration of airborne inertial navigation system forfault-tolerance performance, and the introduction of satellite navigation system of navigation and airdata system for aiding inertial navigation information and achieving high precision, which will helpnavigation systems meet the strict request of accuracy and reliability, have become the research focusin the field of navigation systems.Firstly, this paper has given a demand analysis to redundant configuration of inertial navigationsystems in avionics systems, redundant configurations composed of different types of inertialnavigation systems have been analyzed and compared. A redundancy scheme of inertial navigationsystems with superior performance has been advanced based on the reliability research using seriesparallel model and Markov state transition model.For the redundant configuration composed of several sets of inertial navigation systems, this paperputs forward an performance analysis algorithm based on zero-velocity correct, which divides theredundant systems into primary and standby systems so as to realize an initial structure optimization.After establishing the redundancy structure, this paper firstly launches research work oninformation processing technology for the redundant systems without auxiliary measurements. Aninformation fusion algorithm using difference filter has been put forward, which can improve theoutput consistency among several sets of inertial navigation systems; On this basis, this paper hasadvanced a consistency diagnosis algorithm using wavelet transform, which can provide fault detectionand fault location for redundant systems.For the redundant inertial navigation systems with auxiliary measurements provided by GPS andADS, this paper designed and realized a federal filter for the information fusion of RINS/GPS/ADSsystems, and fuzzy reasoning system has been introduce to optimize the performance of Kaman filters;On this basis, a fault detection, isolation and system reconfiguration mechanism using residualchi-square test has been put forward. Simulation results have shown that, the fault detection algorithmsin this paper provide a high detection sensitivity to both RINS structure and RINS/GPS/ADS structure,and the fault location、isolation and system reconstruction measures can effectively improve the reliability of the navigation systems.Based on the key algorithms mentioned above, a simulation platform is designed and realized,which can provide effective simulation to the outputs of airborne navigation systems, as well as the keyalgorithms on information fusion、fault detection、isolation and system reconfiguration. The simulationresults have proved the efficiency of the algorithms, the multi-function and good operability of theplatform.The research results in this paper lay a good foundation and platform for the semi-physicalsimulation and verification to the information fusion and fault diagnosis algorithms of navigationsystems based on the redundant configuration of inertial navigation system configuration, which hasimportant engineering value for application.