This invention provides a dual-mode propulsion
system in the field of space propulsion technology, combining
xenon propellant electric propulsion and cold gas propulsion. The
system comprises a gas storage module and a pressure regulation module connected in series, with an electric propulsion module and a cold gas propulsion module connected in parallel downstream. These modules are controlled by a control and
power module, which is shared by both electric and cold gas propulsion. Its advantages include solving the problem of insufficient
control torque compared to a single electric propulsion
system. Furthermore, because
xenon is used as the working
propellant, the
xenon required for cold gas propulsion and electric propulsion serves as a
backup for each other, resulting in high
system integration. This meets the stringent limitations of
satellite propulsion system size and control resources. Compared to an independent cold gas propulsion system, it achieves stable adjustment of the cold gas thruster's thrust over a wide range. Additionally, the system employs isentropic expansion decompression, reducing
energy loss during decompression and lowering the
power consumption required for
temperature control.