The invention provides a spacecraft self-driven two-phase circulation heat control system. The spacecraft self-driven two-phase circulation heat control system comprises an expansion machine, a condenser and a liquid storage pot, wherein the expansion machine, the condenser and the liquid storage pot are sequentially connected with an evaporator. The expansion machine is coaxially connected with a pump. A liquid outlet pipeline of the condenser is connected to the liquid storage pot. A liquid outlet pipeline of the liquid storage pot is connected with the evaporator. The pump is arranged on the liquid outlet pipeline of the liquid storage pot. According to the spacecraft self-driven two-phase circulation heat control system provided by the invention, equipment waste heat is used for acting, fluid circulation is achieved without consuming electric energy, and thus energy can be saved; the system inherits the advantages of a two-phase fluid circulation heat control technology that temperature uniformity is good and heat exchange efficiency is high; and the expansion machine and the pump are integrally designed and sealed completely, no leakage problem exists, working media are available at each rotating position for lubrication, friction heat is taken away, and reliability is high.