Research On Radar Calibration Simulation Technology Based On Orbital Dynamics Constraints And EMBET Algorithm

As a method of radio detection and localization,the measurement errors of radar are divided into systematic errors and random errors.Especially,in the radar installation and commissioning and in the implementation of large-scale tasks,radar accuracy identification is required.This dissertation focuses on the application of EMBET self-calibration technology in radar calibration.Firstly,the common ballistic measurement system is introduced and the error models are analyzed.Then,the measurement model and the correction models of the system errors of radar and station in radar calibration are introduced respectively.Further,the basic theories and methods of EMBET technology for calibrating trajectory and radar system errors of the aircraft are described.The principle of high precision satellite-borne GNSS orbit deteminition is analyzed,which provides a comparative method for radar calibration based on EMBET technology,and can also be used for radar calibration alone.The measured data are also processed to verify the theories and methods of this deissertation.Finally,some examples are given to verify the theories and methods,some useful conclusitions are obtained,and the future research plan is prospected.The major innovative works are as follows:(1)The radar self-calibration method of EMBET technology is analyzed in detail.Firstly,the basic principle of EMBET self-calibration technology is discussed.Then according to the flight dynamics law of the aircraft,the sample treaty bundle EMBET model and the orbit dynamics constraint EMBET model are given respectively.The track mechanics model and the solution method of differential equation based on numerical intergration ate analyzed in detail.(2)The precisition of orbit determination of satellite-bone GNSS is estimated.The estimation algorithm is given.The geometric distribution of observation satellites in the satellite-bone GNSS is analyzed.The real-time orbit determination accuracy of the broadcast ephemeris/pseudo distance/Doppler,and the orbit determination accuracies of the ultra fast precise ephemeris(clock difference)/dual frequency carrier phase and the fast and final precise ephemeris(clock difference)/dual frequency carrier phase are presented respectively.(3)The effect of noise on the estimation results is analyzed.It is pointed out that the estimation results meet the requirements without noise;in the presence of noise,when the error of the pitch angle zero value is<0.01mrad,the estimation results satisfy the requirements,and for a serious deviation from the range zero and azimuth zero values,with the R0 error<50m and AO error<0.5mrad,the estimation results can not satisfy the requirements.It is concluded that the "color noise" of random errors causes the deviation of the estimated results and noise has the greatest impact on the estimation accuracy of the azimuth zero value.Next is the range zero value,which has a relatively small impact on the estimation accuracy of the elevation zero value.(4)In order to overcome the influence of random errors on the estimation,improved methods for radar quasi real-time accuracy verification are proposed,and three new processing patterns are given:(?)single radar/single satellite/double arcs,(?)single radar/double(multi)satellites/double(multi)arcs,(?)detection of satellite with multi-radars.Specific verifications are carried out,and it shows that the pattern(?)has the highest precision and the fastest calculation speed,followed by the pattern(?);the effect of the pattern(?)is worse than the parrens(?)and(?);for the pattern single radar/single satellite/single arc,it has good effect for the noise free simulation data,but has poor effect for the measured data with errors.