Aircraft Carrier Ins Alignment

Mastery of the sky is the main focus in the modern war. As one of the main battle armaments of the aircraft carrier, the carrier borne plane plays a damned important tactic role in scrabbling for mastery of the sky. The carrier borne plane is a launch platform of air-borne missile.Before the carrier borne plane takes off, its inertial navigation system must be aligned to the navigation frame,and the alignment precision has a direct influence on the carrier borne plane's safety and the air-borne missile's odds in hiting the target. Therefore,the rapid and accurate initial alignment of the inertial navigation system of the carrier borne plane becomes a key technology of the carrier weapon system forming battle effectiveness.In the thesis,the technology of initial alignment and transfer alignment of the inertial navigation system of the carrier borne plane when the aircraft carrier is moored or is cruising is researched. The main work done in this thesis is as follows:1. The basic theory of the alignment of the strapdown inertial navigation system is systemically researched. The mechanics equation and the attitude angle differential equation of the inertial navigation system are deduced. Error equations of the strapdown inertial navigation system (SINS) based on the principle of error propagation are derived. The lever arm effect between installation place of the inertial measurement unit (IMU) and the center of gravity of the carrier borne plane and the lever arm effect between the aircraft carrier master inertial navigation system and the carrier borne plane master inertial navigation system are analyzed. The compensation algorithm of the lever arm effect is presented. The model of the aircraft carrier flexure deformation is made. Through simulation the effect of the aircraft carrier flexure deformation on the alignment is analyzed.2. The basic theory about Kalman filter is deep researched. The Kalman filtering principle is introduced. The discrete Kalman filtering basic equations and discretization of state equations of the continues system are introduced. The principle about the fuzzy adaptive Kalman filtering is investigated. Aiming at the uncertainty measurement noise in the measurement equations of the initial self-alignment,the fuzzy adaptive Kalman filtering algorithm is designed by considering the effect of the mean of residual error in measurement equations and the ratio of practical covariance to genuine covariance of residual error on the measurement covariance matrix.3. Initial self-alignment of the inertial navigation system of the carrier borne plane when the aircraft carrier is moored is deep researched. In the representative sea condition, models of rolling and piching and yawing are built. The algorithm of SINS coarse self-alignment and precision self-alignment condition based on gravity is...