The research demonstrations on the implementation of the future CSGM satellite gravity mission in China were carried out, based on the preferable selection of satellite tracking modes, the optimal combination of key payloads, the preferred design of orbital parameters, the beforehand execution of simulated studies, and the optimum improvement of gravity recovery methods. Firstly, the Satellite-to-Satellite Tracking in the High-Low/Low-Low mode (SST-HL/LL) was used in the future CSGM satellite gravity mission due to the high-accuracy measurement of the Earth's gravitational field, the lower technical requirements and the successful experiences of the current twin GRACE satellites. Secondly, the space-borne instruments consisting of the interferometric laser intersatellite ranging system, the compound GPS receiver, the drag-free system, the center of mass trim assembly, etc. were developed in advance. Thirdly, the orbital altitude of 300～400 km and the intersatellite range of 100±50 km were designed in the unmeasurable area of the existing gravity satellites. Fourthly, the simulation techniques were applied to the holistic processes of the development and operation for CSGM, including scheme demonstration, system design, parts development, production test, practical application and malfunction analysis. Fifthly, the advantages and disadvantages of the satellite orbital perturbation, dynamic, energy conservation and semi-analytic methods were contrastively analyzed, and the new-type, high precision, high-efficiency and full-frequency satellite gravity recovery methods were investigated. Finally, the expected scientific objectives of the future CSGM satellite gravity mission showed that the cumulative geoid height error is 1～5 cm and the cumulative gravity anomaly error is 1～5 mGal at degree 300.