Provided in the invention is a low-impact separation mechanism for a micro satellite. The low-impact separation mechanism comprises a bottom plate (1), a driving mechanism, and a plurality of separateunlocking components. The driving mechanism includes an unlocking driving gear (4) and a plurality of guiding gears (5); the unlocking driving gear (4) is mounted at the middle part of the bottom plate (1); all guide gears (5) are circumferentially distributed along the unlocking drive gear (4); all separate unlocking components are distributed around the unlocking drive gear (4) and are installed on the bottom plate (1). In a locking state, latch pins (12) are inserted into through holes formed in two sides of support cylinders (2) and connecting feet (3); and baffles (10) are used for limiting. Therefore, defects that the existing fire separation mechanism has the large impact, causes much pollution and can not be used repeatedly are overcome. On the basis of multi-point locking, single-point triggering and synchronous unlocking, a problem of single performance of the traditional separation mechanism is solved.