Abstract: The energy supply of CubeSat during the mission in orbit mainly relies on batteries or body-mounted solar arrays. With the development of micro spacecraft technology, the functional density of CubeSat is increasing, and the power demand of on-board payload is getting higher and higher, it is difficult for the traditional battery panel energy supply method to meet the future space mission requirements. In addition, the CubeSat has special application requirements for the stowage size and deployment mechanism of the battery array due to its unique size specifications and standards. Based on the above background and the structural characteristics of the CubeSat, this paper designs a one-dimensional shear-fork space deployable mechanism with simple deployment principle, good scalability and large folding ratio, and conducts processing and ground deployment tests of the principle prototype to verify the functional feasibility of the mechanism design and the rationality of the design parameters. The power generated by the array after deployment is three to five times higher than the conventional energy supply method, and the special geometry can provide the advantage of passive gravity gradient stabilization, which has important application value in enhancing the future CubeSat load capacity.