The present application relates to the technical field of
spacecraft propulsion
system, and more particularly to a micro-newton
hybrid mode propulsion
system and method based on gas working substance. The
system comprises a gas storage unit, a
gas supply unit, a thruster unit and a propulsion system driving and
control unit. The gas storage unit adopts symmetrically arranged high-pressure gas cylinders connected through high-pressure isolation valves, and in combination with the automatic balancing strategy of the
control unit, effectively solves the problem of on-
orbit centroid drift. The
gas supply unit includes parallel cold gas propulsion branches and electric propulsion branches, and each
branch adopts a
mechanical pressure reducer to eliminate vibration and
noise caused by
electromagnetic valve action from the source, realizing super-static operation of the system. The propulsion system driving and
control unit controls the micro-newton cold gas thruster and the micro-newton electric thruster to work alone or in cooperation according to the distribution strategy based on the thrust critical point, realizing the optimal comprehensive efficiency of high precision and high
specific impulse in the full thrust range, and being suitable for ultra-high precision space scientific exploration missions.