The invention discloses a spacecraft effective load impact reduction device. The spacecraft effective load impact reduction device is characterized by sequentially comprising an inner side ring, a supporting ring and an outer side ring; inner side ring threaded holes and inner side ring positioning holes are circumferentially and uniformly distributed on the inner side ring from inside to outside; the inner side ring threaded holes and the inner side ring positioning holes are distributed in a staggered mode; outer side ring positioning holes and outer side ring threaded holes are circumferentially and uniformly distributed on the outer side ring from inside to outside; the outer side ring positioning holes and the outer side ring threaded holes are distributed in a staggered mode; supporting ring inner side holes and supporting ring outer side holes are circumferentially and uniformly distributed on the supporting ring from inside to outside; and the supporting ring is fixedly connected with the inner side ring and the outer side ring. The spacecraft effective load impact reduction device is small in size, simple in structure, high in operability and capable of meeting the impact reduction requirements of effective loads in a spacecraft and can be used as an impact reduction measure for other equipment.