Modeling and Data Compatibility Analysis of Laser Guided Missile
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A model of the missile s aerodynamic has been developed by Kongsberg DefenseSystems (KDS) based on information from CFD analysis and wind tunnel tests. It isdesirable to supplement the existing model by using data from actual missile flights inorder to improve the model validity. A system identification scheme based on actualflight data involves test flights, data compatibility analysis, model identification andverification. Data compatibility analysis, which is the main focus for this thesis,concerns the determination of systematic errors in the measurements. The purposeof this thesis is to investigate methods for a data compatibility analysis scheme for alaser guided missile.During this report a nonlinear six degree of freedom model of the missile has beendeveloped and the aerodynamic model equations have been evaluated in terms of anidentification process. Methods to determine errors in the sensor measurements havebeen developed. The methods are based on the extended Kalman filter and nonlinearobserver proposed by Vik & Fossen (2001). The filters performance where verifiedin a case study where they illustrated high performance in terms of convergencerate and estimate accuracy. A data compatibility analysis scheme, based on the casestudy results, is suggested, involving several pre-flight tests and an inertial navigationsystem (INS) for on-board filtering. The data compatibility analysis scheme wastested with data from a missile test flight. The position error found by using theunfiltered measurements from the IMU, gives reason to believe that the error inmissile point of impact, occurred due to sensor measurement errors. Significant biasand scale-factor errors are estimated by the filters and the final position estimatecorresponds to the actual missile point of impact.