The invention discloses a solar-sail spacecraft structure provided with distributed satellites for traction. The solar-sail spacecraft structure provided with the distributed satellites for traction is composed of a central spacecraft, the distributed satellites and a square solar sail film. The distributed satellites are fixedly connected with the central spacecraft through connection and separation devices, and the distributed satellites are ejected to be separated from the central spacecraft through the connection and separation devices, so that the relative speed is obtained; and tied ropes are pulled to be controlled at the same time, so that the solar sail film is pulled out and unfolded. After the solar sail film is unfolded in place, a system is made to spin up through active acting force of the distributed satellites, and tensile force for keeping the solar sail film flat is generated. The multiple distributed satellites are used for providing traction force in the unfolding process, providing centrifugal force in the on-orbit flight process and serving as a distributed effective loading platform when a detection task is carried out. A thin-film solar cell and a liquid crystal reflection device are pasted onto the solar sail film; and electric energy converted by the solar cell is stored in a power source management system, serves as electric energy required for operation of satellite-borne equipment and is used for achieving posture control of the central spacecraft.