Airborne Transfer Alignment Accuracy Evaluation Study Of Tactical Weapons

With the development of the modem war, varied airborne tactical weapons equipped inertial navigation system emerge endlessly. And from the Gulf War to the Iraq War, the airborne tactical weapons are more and more important in the modern war as the medium scale striking force. The airborne tactical weapons are emit by the airplane, so the rapid and accurate transfer alignment of the inertial navigation system of the airborne tactical weapon is becoming a key technology of the airborne tactical weapon.In this thesis, the technology of the transfer alignment and transfer alignment accuracy evaluation of the inertial navigation system of the airborne tactical weapon is researched systematically and entirely.The main work done in this thesis is as follows:1. The basic theory of the transfer alignment is stated. Error equations of the platform inertial navigation system and the strapdown inertial navigation system are derived based on the principle of error propagation. The lever arm effect between the airborne master inertial navigation system and the missile slaver inertial navigation system is analyzed. The compensation algorithm of the lever arm effect is presented. The model of the airborne wing flexibility is made.2. The basic matching schemes of the transfer alignment are researched in this thesis. The state space models of the velocity matching, the attitude matching, the angular rate matching and the specific force matching transfer alignment are made. And then the simulations of them are made and the analysis of the simulation results is made.3. The federated filtering of the velocity and attitude matching rapid transfer alignment is designed. The simulation validates the performance of the federated filtering.4. The H∞ filtering of the attitude matching transfer alignment is designed. The simulation validates the performance of the H∞ filtering.5. The transfer alignment accuracy evaluation based on the difference global position navigation system (DGPS) of a certain air-to-air missile is researched. The state space model of the transfer alignment accuracy evaluation based on DGPS of a certain air-to-air missile is made. The fixed point and fixed interval Kalmansmoothers are designed to realize the transfer alignment accuracy evaluation based on DGPS of a certain air-to-air missile. And then the simulations are done.6. The on-line construction problem of the velocity matching data of the airborne master inertial navigation system is researched. The navigation frame of the airborne master inertial navigation system and the missile slaver inertial navigation system is the geographic frame and the quasi-inertial frame respectively. And then three on-line construction algorithms of the velocity matching data of the airborne master inertial navigation system are presented.The main innovations done in this thesis are as follows:1. The federated filtering of the velocity and attitude matching transfer alignment is presented. The filtering order of the federated filtering is lower and the filtering updating rate of the federated filtering is higher than that of the traditional centralized Kalman filtering of the velocity and attitude matching transfer alignment.2. The H∞ filtering of the attitude matching transfer alignment is presented. The H∞ filtering could perform the attitude matching transfer alignment under the condition that the airborne wing flexibility model is fault.3. The fixed point and fixed interval Kalman smoothers are applied in the transfer alignment accuracy evaluation based on DGPS.4. Three kinds of the on-line algorithm- the earth-referenced velocity conversion and compensation algorithm, the specific force integrated algorithm and the modified specific force integrated algorithm-are proposed for constructing the velocity matching data of the master inertial navigation system for the transfer alignment.