Method of realizing combined navigation system structure for aviation

Abstract

The combined navigation system for aviation consists of inertia navigation system, satellite navigation system, VOR-DME and altimeter. After fault diagnosis to judge the normality and the availability of the separate navigation systems, the normal navigation systems are combined to form one multistage multi-layer structure. By means of information fusion, high precision navigation information is obtained from the combined navigation system. In case of some navigation system with fault, the failed navigation system is isolated and the system is reconstructed for further navigation. The present invention can raise the reliability and availability of the combined navigation system for aviation.

Description

technical field [0001] The invention relates to an integrated navigation system architecture, in particular to an aviation integrated navigation system architecture suitable for a new generation of national air traffic management system. Background technique [0002] High-performance aviation navigation is the key technology of the new generation of national air traffic control system and an inevitable requirement for the safety of aircraft navigation. The new generation of national air traffic control system puts forward higher requirements for the accuracy, integrity, continuity and availability of the aviation navigation system . [0003] At present, civil aviation navigation in the world has developed from a single navigation method to a high-precision, high-reliability, comprehensive, and intelligent aviation integrated navigation system; the information processing method has also changed from a single data source to multiple navigation sensors and multiple data sources...

AI Technical Summary

Problems solved by technology

The existing navigation integrated navigation architecture is mainly centralized and distributed. The centralized structure is to send all the measurement data of the navigation system to a central processor for processing and fusion, data alignment, data interconnection and filtering. The structure requires a data transmission bus with a wide frequency band to transmit high-speed raw data. Data interconnection is difficult, and the system must have a large capacity. The calculation burden is heavy, and a central processing unit with strong processing power is required. Therefore, the system The survivability is poor; the existing distributed structure mainly adopts the federated filtering structure, as shown in Figure 1, which is characterized by: the measurement information of n subsystems is sent to the local filter for local filtering before being transmitted to the main filter , and then send the processed information and reference system information to the main filter to form a global estimate and improve the accuracy of the navigation system. Although this structure has low requirements on channel capacity and strong system vitality, in the federated filter structure, the local filter must Have a reference system, once the reference system fails, the entire navigation system fails

Therefore, adopting a centralized or distributed system structure and combining the characteristics of inertial navigation system, satellite navigation system, VOR-DME, and altimeter system to form an aviation integrated navigation system cannot meet the requirements of aviation integrated navigation for the new generation of national air traffic management system. System Architecture Needs for High Precision, High Reliability and High Availability

Images