| With the rapid development of satellite to satellite tracking technology and satellite gravity gradiometry technology at the beginning of this century, it indicates that humanity has entered a new era of satellite gravity exploration. The successful implementation of CHAMP, GRACE and GOCE satellite missions has greatly encouraged the confidence of the domestic and foreign research institutions to carry out the following tasks and the next generation of satellite mission. In addition, CHAMP and GOCE satellite missions have completed its gravity field detection mission, and GRACE satellite mission has already extended service. So,it is a hot topic for many experts and scholars to look for a new generation of satellite gravity mission that with high efficiency and high precision.Based on the above context, in this dissertation, the parameters and configuration design of the next generation GRACE-type satellite formation are systematically studied, and the ability to detect the earth's gravity field by various satellite formation and satellite constellation is analyzed too, the main research work and achievements of this dissertation can be summarized as follows:(1) Analyzed the influence of different reference gravity field model in satellite trajectory simulation. It is considered that the reference model should choose the latest and the most accurate gravity field model;(2) Based on the technology of satellite to satellite tracking in low-low model, with the principle of energy conservation, which a strict mathematical model of the difference of kinetic energy between two satellites and the coefficient of the earth gravity field was established.Then systematically analyzes the influence of the orbital parameters(orbital altitude and orbital inclination) on gravity field recovery. Results show that the orbital altitude should fully consider the influence of atmospheric drag and the gravity field attenuation factor, try to choose an altitude with longer repeat period, meanwhile, considering the impact of orbital altitude on the satellite life that the orbital altitude index in 300-350km is more appropriate. And the choice of orbital inclination is best with a longer repeat period and reduce the influence of polar gaps, so the inclination of near polar orbit is suggested;(3) Under the premise of the basic orbital parameters have been determined, the accuracy of the inversion of the earth gravity field with different inter satellite range is analyzed. Results show that the large inter satellite range is helpful to improve the accuracy of the low order of the gravity field. But with the satellite spacing increases, the gravity field accuracy improvement is not obvious in high order. In addition, it's not conducive to recovery high order gravity field when the inter satellite range is lager because of the separation function values fluctuate greatly.Combined with the scientific objectives of the future satellite gravity missions is to get the gravity field with higher spatial resolution, so the distance should be set in the 100km;(4) Analyzed the effects of- different orbital error and the intersatellite range rate error on the accuracy of gravity field inversion. The experimental results show that when the gravity field is calculated only by using the orbit data, the precision of the gravity field in the mid long wave can be improved greatly after the orbit determination precision is improved. But the accuracy of the gravity field inversion is mainly dependent on the improvement of the measurement accuracy of the inter satellite range rate when the data of the inter satellite range rate is added.With the precision of inter satellite range rate increased, the gravity field recovery precision is changed at a quantity level. Combined with the current level of orbit determination, for the next generation of GRACE-type, its orbit determination accuracy is better in 1?3cm and the precision of inter satellite range rate should be set at about 10-8m/s;(5) Studied two kinds of satellite constellation models, which are composed of GRACE-type satellite formation. The first satellite constellation is with different mean anomaly between two GRACE-types and the other satellite constellation is with different right ascension of ascending nodes between two GRACE-types, then four simulation schemes are designed and compared. The results show that use satellite constellation model instead of the traditional single satellite formation mode can obtain the same accuracy of the gravity field model in a shorter period than that calculated from the satellite observations over a long period of time, so it can effectively improve' the spatial resolution of satellite gravity missions;... |
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