This paper proposes the design of a canned picosatellite with an autogyro system capable of ensuring the integrity of an egg payload during both the flight and landing phases. The design of this satellite was based on the requirements outlined in the “Concurso Iberoamericano de Satélites Enlatados 2023” guidelines. The findings made in this paper hold implications for applications involving the transportation and safe landing of delicate payloads in space exploration missions. As a result of the implementation, the objective of deploying the secondary face of the primary was accomplished, and the weather parameters were transmitted. On the other hand, the autogyro mechanism managed a speed reduction efficiency of 84.21%.