Research On Error Excitatedation In Flexible SINS Caused By Airborne Installation Way

As modern navigation equipments, inertial navigation system(INS) has been widely used in both military and civil aircraft, especially in the fields of modern military aeronautics where they hold a pivotal position. Now it has become one of crucial signs of technological level and military strength of a country. As a result of the principle, design, manufacture craft, installment, algorithm and so on, the inertial measurement unit (IMU) in SINS may causes navigation localization error. Especially, because IMU is directly installed on the carrier, the change of installation way of which can make SINS not to distinguish and measure the carrier's movement accurately. Accordingly, it can influence the excitatedation effect of strapdown inertial navigation system's (SINS's) error model parameter, and affect the navigation accuracy without any compensation. Therefore, research on error excitatedation in flexible SINS caused byairborne installation will play an important role in inertial measurement system error modeling and in improving hit precision of the strategy and the tactical weapon relying on the inertial system.Because of all above, this thesis studies systematically and detailedly on the error excitatedation in flexible SINS caused byairborne installation,.The main contributions are as following:Carry on thorough analysis and induction on the inertial measurement system's error model in flexible SINS, it can provide the basis to have a further research on the error excitatedation caused byairborne installation.Analyze systematically from theoretical point of viewing the installation error, conclude the system's error model when there is position-installing error. On the basis of analyzing IMU's angle-installing error, this paper proposes the system's error model in this condition. And the simulation results represent the disadvantages in SINS stemming from installation error. The research can provide an effective basis on the initial alignment of the gimbaled INS and compensation to the system.Analyze the effective excitatedation of the flight trajectory for the inertial measurement system, in this foundation, study the error model excitatedation caused byairborne installation way, and validate the relation between them. This research is valuable for distinguishing the error model parameter in dynamic condition making use of the error model excitatedation caused byairborne installation way.On the basis of theory analysis and simulation validation, this paper has designed and developed the inertial measurement system error model confirmation simulation platform, it can provide an effective research method and environment for studying the error model excitatedation caused byairborne installation and validating its vital role in the inertial measurement system error model verification test plan.