Parallel Tank Satellite Non-isobaric Gas Cushion Propellant Filling Capacity and Center of Mass Design

Previous work has determined that the initial center of mass at the launch of the parallel tank satellite is the initial center of mass of the orbit maneuvering process. And that did not consider the ability of the filling pressure of the tank gas cushion to adjust the propellant mass and the satellite center of mass. In this paper, a design method for non-isobaric gas cushion propellant filling capacity and satellite center of mass in parallel storage tank is proposed. Using the strategy of independently controlling the amount of propellant filling and gas cushion pressure of each tank in parallel tanks, and using the gas cushion as the driving force to adjust the distribution of propellant in different tanks, different satellite centers of mass are designed at the time of satellite launch and at the beginning of orbit maneuvering, so as to meet the requirements of the launch vehicle for the center of mass of the satellite launch state and the small orbit control interference torque during orbit maneuvering. The calculation results show that the engine interference torque can be reduced by about 60.3%. The work in this paper is helpful to improve the utilization efficiency of propellants and promote the application of parallel tank chemical propulsion system.