The present invention proposes a reinforcement mechanism and a method of using the same for stacked flat-panel satellites, and belongs to the field of space product structure and mechanism design. The problem of poor mechanical properties of existing flat-panel
satellite assemblies is solved. It includes a first reinforcement mechanism and a second reinforcement mechanism, and the first reinforcement mechanism and the second reinforcement mechanism are alternately arranged around the outside of the
satellite assembly. The first reinforcement mechanism includes a first
recovery rod, a first
steel belt fixing seat and an elastic
steel belt. A plurality of first
steel belt fixing seats are arranged axially at intervals on the first
recovery rod, and two elastic steel belts are connected to both sides of each first steel belt fixing seat, respectively. A plurality of second steel belt fixing seats are arranged axially at intervals on the second
recovery rod, and the first steel belt fixing seat and the second steel belt fixing seat are alternately arranged in the vertical direction. One end of the elastic steel belt is connected to the first steel belt fixing seat, and the other end is connected to the second steel belt fixing seat through a fixing
rope. It is mainly used for the reinforcement of stacked flat-panel satellites.