Airborne Integrated Navigation Technology

For the military airplane, the airborne navigation system must be considered the independentily, navigation precision and reliability. It has much meaning of making use of the airborne equipment to improve the general performance of navigation system by adopting multi-sensor integrated navigation technology. This thesis presents an integrated navigation system, which consists of strap-down inertial navigation system (SINS), air data system (ADS), tactical air navigation (TACAN) and airborne optical- electric sighting system (OES).Flight track generator is the basis of the simulation which studies on inertial navigation and integrated navigation. Firstly, the flight parameters offer the ideal output of the gyros and accelerometers for the navigation simulation calculation. Secondly, the flight parameters offer the benchmark in order to test the inertial navigation algorithm and integrated navigation algorithm in correctness and performance. In this thesis, a great circular flight track generator is designed. Using the great circular flight track generator can generate the complex flight track.The reasearchs on SINS, ADS, TACAN and OES integrated system are organized as following:1, The SINS, ADS, TACAN and OES's mathematic models are established and simulations are made on the SINS/ADS, SINS/TACAN and SINS/OES integrated system respectively. The simulation results show that the mathematic models are correct.2, In view of improving the accuracy and reliability of the military airplane navigation sysytem, it is presented the development of an integrated navigation system for the military airplane using ADS, TACAN and OES to integrate with SINS. Integrated of SINS, ADS, TACAN and OES wuold fuse together the virtues of each system for a better performance. Thus the federated Kalman filter algorithm is employed in this integrated system, which is based on two reasons. The first one is that there are more than two navigation systems involved, using federated Kalman filter could overcome the disadvantages of the traditional centralized Kalman filter, which is suffer from dimension disaster, lower real-time capability and worse robustness. That second one is that the integrated system has different integrated modes in different working conditions. For example, it employs SINS/ADS/OES integrated mode mostly when the TACAN signal is disturbed, and uses SINS/ADS/TACAN when the landmark cann't be acquired because of bad weather. Hence, different integrated modes are decided by different kinds of system's signal acquired.3, For the SINS/ADS/TACAN/OES integrated navigation system, simulation is made on a typical track, which is generated by the flight track generator, and the simulation results show that the SINS/ADS/TACAN/OES integrated navigation system can make use of the sub-system's information and improve the reliability and accuracy of the military airplane navigation system.